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EP2011965B1 - Method and device for clamping bladed rotor discs of a jet engine - Google Patents

Method and device for clamping bladed rotor discs of a jet engine Download PDF

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Publication number
EP2011965B1
EP2011965B1 EP08158102A EP08158102A EP2011965B1 EP 2011965 B1 EP2011965 B1 EP 2011965B1 EP 08158102 A EP08158102 A EP 08158102A EP 08158102 A EP08158102 A EP 08158102A EP 2011965 B1 EP2011965 B1 EP 2011965B1
Authority
EP
European Patent Office
Prior art keywords
blisks
tie
rod
rotor
arrangement
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
EP08158102A
Other languages
German (de)
French (fr)
Other versions
EP2011965A2 (en
EP2011965A3 (en
Inventor
Sacha Pichel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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Filing date
Publication date
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2011965A2 publication Critical patent/EP2011965A2/en
Publication of EP2011965A3 publication Critical patent/EP2011965A3/en
Application granted granted Critical
Publication of EP2011965B1 publication Critical patent/EP2011965B1/en
Ceased legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02Blade-carrying members, e.g. rotors
    • F01D5/025Fixing blade carrying members on shafts
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02Blade-carrying members, e.g. rotors
    • F01D5/06Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps

Definitions

  • the invention relates to a jet engine with a device for clamping bladed rotor disks and a method for clamping bladed rotor disks with the device in a jet engine.
  • the turbine and compressor are usually arranged on a shaft.
  • the compressor consists of several rotor discs, each carrying a row of blades and are welded or bolted together.
  • the US 6,267,553 B1 discloses a gas turbine with a high pressure compressor in which there are a plurality of tubular tie rods.
  • the tie rods are guided through openings in the rotor disks, which are arranged radially around the center of the disk.
  • the bracing is done by screws, which are screwed into the internal thread of the tie rods.
  • the US 5,537,814 describes a tie rod for a gas turbine engine that clamps not only the rotor disks of the compressor but also those of the turbine.
  • the tie rod here is a hollow shaft, which is bolted to the blisk in the first stage. Downstream of a radial compressor impeller, a nut is threaded onto a thread of the tie rod to tension the tie rod.
  • the DE 10 2005 052 819 A1 discloses a compressor rotor of a jet engine with all features of the preamble of Anprüche 1 and 9, wherein the compressor rotor is composed of Blisks and braced by a central tie rod.
  • An undivided shaft also allows no separate modular design of compressor and turbine.
  • the air passage of a possibly existing vortex rectifier is difficult.
  • the length of the tie rod and various materials and expansion coefficients of the discs complicate the thermal balance between the shaft and rotor and thus maintaining a uniform biasing force.
  • the variable during operation biasing force and the length of the tie rod deteriorate the rigidity of the rotor.
  • the temperature gradient along the disk should be relatively low.
  • the uniform temperature inside the rotor leads to considerable temperature gradients for individual disks.
  • the invention is therefore an object of the invention to provide a device for clamping bladed rotor discs in a jet engine, which is easy to assemble and disassemble.
  • the clamping of the blisks with the help of a tie rod allows easy assembly and disassembly both during installation and during maintenance or in case of damage.
  • the blisks can be easily installed or removed without, e.g. multiple glands must be solved.
  • the tie rod is substantially tubular, disposed within central apertures in the blisk-formed rotor discs, and fixedly connected to a shaft which is driven by at least one turbine section.
  • the existing in the blisks anyway central openings can be used well for mounting and dismounting of the tie rod, and there are no additional holes in the discs required.
  • the tie rod is not passed through the rotor discs following in the flow direction on the Blisks, so that the disc diameter of these rotor discs need not be increased.
  • the blisks are by means of the tie rod between at least a first arrangement, which is upstream of the Blisks, and at least one second arrangement, downstream of the Blisks is located and connected to a rotor disk which is adjacent to the Blisks, clamped. In this way it is ensured that the blisks can be clamped independently of the connection between the other rotor disks.
  • the first arrangement comprises a stop arrangement and the second arrangement comprises a clamping arrangement. Due to the clamping arrangement, the blisks can be clamped in a simple manner relative to the stop arrangement.
  • the stop assembly includes upstream of the blisk an extension of a blisk of the first stage adjacent to a stop on the tie rod. This represents a simple embodiment of a stop arrangement.
  • the tensioning arrangement preferably comprises at least one tensioning element which serves to transmit power between the tensioning armature and the rotor disk.
  • the tensioning element is substantially annular and has a flange-shaped, radially outwardly directed attachment portion, an axial tubular center portion and a radially inwardly directed tension portion.
  • the radially outwardly directed attachment portion of the tension member is secured to a portion of the rotor disc which is adjacent to the blisks downstream. As a result, the voltage generated in the clamping element and in the tie rod is transmitted to the rotor disk.
  • the radially outwardly directed attachment portion of the clamping element is located on a radially inner portion attached to the rotor disk, which is adjacent to the Blisks downstream.
  • the attachment portion of the tensioning element is attached to a radially inner portion of the rotor disc, which is adjacent to the Blisks downstream.
  • the power transmission takes place in this case without major deflections.
  • the tie rod has at its downstream end a shoulder whose outer diameter is smaller than the outer diameter of an upstream adjacent portion of the tie rod, and the radially inwardly directed clamping portion of the clamping element enclosing the shoulder radially, wherein the radially inwardly directed clamping portion of the clamping element axially displaceable relative to the shoulder and spaced from an axial boundary of the shoulder in operation and adjacent to the clamping means.
  • This arrangement offers the advantage of a low construction cost and good mounting and dismounting.
  • the tensioning means may in particular be a tie-rod nut, which can be screwed onto an external thread on the shoulder of the tie rod. Due to the tie rod nut, the tension between the blisks is easily adjustable.
  • the first arrangement upstream of the blisk comprises a tensioning arrangement with a tensioning means and the second arrangement downstream of the blisk comprises at least one screw connection between the tensioning bolt and the rotor disk.
  • the upstream end of the tie rod radially adjoins from the inside to a tubular upstream Prolonging the first level blisk.
  • the tensioning means is axially adjacent to the extension and radially to the tensioning ring adjacent to the upstream end of the tie rod, and the tension anchor has a flange at its downstream end which attaches to the rotor disc which is adjacent to the blisk downstream is.
  • the first arrangement serves to generate a voltage with respect to the rotor disk, which is adjacent to the Blisks downstream, and has a very low construction costs.
  • the clamping device is easily accessible from the compressor inlet side.
  • the tie rod has a conical extension in the flow direction, and the flange of the tie rod is attached to a radially outer portion of the rotor disc, which is adjacent to the Blisks downstream. This allows for clamping of the blisks near the blade and good sealing between the blisks. When attached to the radially outer portion of the rotor disc, which is adjacent to the Blisks downstream, occurs a low bending stress of the rotor disc during tensioning of the tie rod.
  • the upstream end of the tie rod is fastened to the tie rod ring with at least one screw connection, which has an external thread, and the tensioning means is a tie nut, which is screwed onto the external thread of the Glasankerrings.
  • the tie-rod nut makes it easy to adjust the tension in the tie rod ring, in the screw connections and in the tie rod.
  • the clamping means simultaneously clamps a radially inner bearing ring of a Switzerlandankerlagers.
  • the clamping means simultaneously clamps a radially inner bearing ring of a Switzerlandankerlagers.
  • At least one tube-type vortex rectifier may be attached to the rotor disc adjacent the blisks downstream.
  • the vortex rectifier flows compressed, heated air in the radial direction from outside to inside and is passed to the turbine for cooling.
  • By placing the vortex rectifier outside the blisks local heating in the disk area of the blisks is avoided. Also, the attachment of the vortex rectifier outside the blisks is easier.
  • the object is achieved by a method for clamping blisks using the jet engine described above, in which the blisks are releasably clamped by means of the tie rod and the other rotor discs are connected separately and independently of the tie rod firmly together.
  • the separate clamping of the blisks allows for easy assembly and disassembly of the blisks.
  • the blisks are clamped by means of the tie rod between an assembly located upstream of the blisk and an assembly located downstream of the blisk and connected to a rotor disc adjacent the blisks downstream.
  • the tie rod is tensioned by the second arrangement located downstream of the blisks.
  • the tie rod can be stretched from the first arrangement located upstream of the blisk.
  • a good accessibility of the arrangement is given.
  • a rotor 1 of a nine-stage axial compressor which has six rotor disks formed as blisks 6, three rotor disks 4, 9 with rotor blades 5, and at least one vortex rectifier 38.
  • the rotor 1 has a first device 3 of the jet engine according to the invention for clamping the blisks 6.
  • the first six bladed rotor disks 6 in the flow direction 40 are designed as blisks 6.
  • the blisks 6 are bladed rotor disks in which one disk is integrally formed with the associated blades.
  • On the Blisks 6 follow in the flow direction 40 three bladed Rotor disks 4, 9, the blades 5 are releasably attached.
  • the rotor disk 9 adjoins the last blisk 6 in the flow direction 40.
  • Each blisk 6 has close to the rotor blades 5 at least one axial extension 44, which abuts at least one adjacent blisk 6 respectively.
  • the rotor disk 9 abuts close to the rotor blades 5 with an axial extension 43 to the last in the flow direction 40 Blisk 6.
  • first embodiment of the device 3 comprises a tie rod 12, a stop assembly 27 and a clamping assembly 28, which in Fig. 2 is shown enlarged.
  • the tie rod 12 is tubular and has at its upstream end 21 a radially inwardly recessed shoulder 42 with a stop 16. At its downstream end 14 (FIG. Fig. 2 ), a shoulder 15 is provided, which is set back radially inwardly relative to an axial section 19 of the tie rod 12 and is limited by an axial boundary 17 against the flow direction 40.
  • the shoulder 15 may also have a sprocket.
  • the tie rod 12 is disposed centrally within openings 8 in the blisks 6. It adjoins at its upstream end 21 in the stop assembly 27 to a blisk 6 of the first stage of the compressor. At its downstream end 14 of the tie rod 12 is connected via the clamping assembly 28 with the downstream of the Blisks 6 rotor disk 9.
  • the stop assembly 27 is located at the upstream end 21 of the tie rod 12 and is formed by a stop 16, a shoulder 42 and an extension 7 of the blisk 6 of the first stage of the compressor.
  • the stop 16 forms an axial boundary of the shoulder 42 in the flow direction 40.
  • the extension 7 of the blisk 6 of the first stage of the compressor extends axially against the flow direction 40 to the stop 16. It encloses the shoulder 16 radially, but it is axially displaceable ,
  • enlarged clamping arrangement 28 includes the shoulder 15 of the tie rod 12, a clamping element 33, a tie nut 37, a plurality of screw 29 and adjoins the rotor disc 9, which is adjacent to the Blisks downstream, at.
  • the clamping element 33 comprises a, a flange forming, radial mounting portion 34, a center portion 35 and a clamping portion 36th
  • the center portion 35 of the clamping element 33 is tubular and extends in the mounted state axially and parallel to the tie rod 12.
  • the flange-like mounting portion 34 is directed from the downstream end of the clamping element 33 from radially outward.
  • the clamping portion 36 is directed radially inward from the upstream end of the clamping element 33 and may have a toothed ring.
  • the clamping element 33 is fastened with its fastening section 34 by means of screw connections 29 to an inner section 10 of the rotor disk 9.
  • the clamping portion 36 protrudes in the assembled state of the clamping device 28 parallel to the axial boundary 17 and in the axial direction of this radially inwardly and surrounds the shoulder 15, wherein the clamping portion 36 but against the shoulder 15 is axially displaceable. If sprockets are present on the shoulder 15 and on the tensioning section 36, the toothing of the tensioning section 36 engages in the toothing of the shoulder 15. In the flow direction 40, the tie rod nut 37, which is screwed onto the external thread 18, adjoins the tensioning section 36.
  • the radially outwardly directed fastening section 34 of the clamping element 33 designed as a flange is first fastened by means of a plurality of circumferentially distributed screw connections 29 on the inner section 10 of the rotor disk 9, which adjoins the blisk downstream.
  • the blisks 6 are pushed onto the tie rod 12.
  • the tie rod 12 is then inserted with the shoulder 15 in the annular clamping element 33.
  • the tie nut 37 is screwed onto the external thread 18 of the tie rod 12 and tightened.
  • the tensile force in the clamping element 33 is transmitted from the radially inwardly directed clamping section 36 via the axial center section 35, the radially outwardly directed fastening section 34 and the screw connections 29 to the radially inner section 10 of the rotor disk 9. From there, the force in the rotor disk 9, which is adjacent to the Blisks downstream, in the radial direction outward into the axial extension 43rd the rotor disk 9 forwarded.
  • the tensile force in the tie rod 12 is transmitted along the tie rod 12 on the shoulder 16.
  • the two tensile forces cause compressive forces between the axial extension 43 of the rotor disk 9, the abutting blisks 6 and the abutment 16 of the upstream abutment arrangement 27 via the extensions 44. These compressive forces press the blisks 6 against the extensions 44 of the blisks 6 near the blades 5 axially together and cause the restraint.
  • the compressive forces must be large enough to hold the blisks 6 together. But they must also not be too large, so that the tensile stressed components of the device 3, namely the tie rod 12, the external thread 18 on the tie rod 12, the clamping element 33, the screw 29 or the internal thread of the tie nut 37 are not overloaded during operation.
  • FIG. 3 and 4 shows the second and alternative embodiment of the device 3 of the jet engine according to the invention, in which the rotor 1 of the compressor is constructed the same as in Fig. 1 ,
  • the second embodiment of the device 3 comprises a tie rod 47, a plurality of screw connections 41 and a clamping arrangement 30, which in Fig. 4 is shown enlarged.
  • the tie rod 47 has a conical enlargement 20 in the flow direction 40. At its upstream end 21 of the tie rod 47 has a radially inwardly directed flange 45. The conical extension points its downstream end a flange 13 which is directed radially outward.
  • the tie rod 47 is arranged centrally within openings 8 in the blisks 6. It adjoins at its upstream end 21 radially from the inside to an axial extension 7 of the blisk 6 of the first stage of the compressor. At its downstream end, the tie rod 47 is connected via a plurality of screw connections 41 distributed over the circumference to the rotor disk 9 adjoining the blisks 6 and adjoining the blisks downstream.
  • the screw connections 41 are distributed in the circumferential direction on a radially outer section 11 of the rotor disk 9, which adjoins the blisks downstream.
  • the flange 13 is fastened to the rotor disk 9 at the end of the conical enlargement 20 of the tie rod 47.
  • the upstream tensioning assembly 30 is in Fig. 4 shown enlarged and includes a Glasankerring 24, a plurality of screw connections 32, a first spacer ring 31, a second spacer ring 39, a Switzerlandankerlager 25 and a Switzerlandankermutter 37th
  • the Buchankerring 24 is annular and has the same outer diameter as the tie rod 47.
  • the Buchankerring 24 has at its adjacent to the tie rod 47 end a radially inwardly directed flange 46.
  • the Buchankerring 24 also has a shoulder 23 whose outer diameter is smaller than the diameter of the upstream end 21 of the tie rod 47.
  • At the upstream end of Buchankerrings 24 is an external thread 22 whose diameter is smaller than that of the paragraph 23rd
  • the first spacer ring 31 is annular and has substantially the same inner diameter as the axial extension 7 of the blisk 6 of the first stage of the compressor.
  • the second spacer ring 39 is also annular.
  • the tie rod bearing 25 is a ball bearing with a radially inner bearing ring 26th
  • the Buchankerring 24 abuts in the axial direction of the upstream end 21 of the tie rod 47 and forms an axial extension of the tie rod 47 against the flow direction 40.
  • the Buchankerring 24 is secured by means of several screw 32 on the flange 45 of the tie rod 47. In the radial direction, the Glasankerring 24 abuts the first spacer ring 31 from the inside.
  • the extension 7 encloses the tie rod 47 in the radial direction, wherein the extension 7 is displaceable relative to the tie rod 47.
  • the first spacer ring 31 encloses the tie rod 47 in the region of the flange 45 and the Wernerring 24, but with a displacement in the axial direction is given.
  • the first spacer ring 31 adjoins the extension 7 of the blisk 6 of the first stage of the compressor at its downstream end. At its upstream end of the spacer ring surrounds the shoulder 23 of the Werankerrings 24 in the radial direction, but with a displacement in the axial direction is given.
  • the inner bearing ring 26 of the Buchankerlagers 25 is arranged displaceably in the axial direction on the shoulder 23 of the Buchankerrings 24.
  • the inner bearing ring 26 adjoins the first spacer ring 31 downstream and to the second spacer ring 39 upstream.
  • the second spacer ring 39 also encloses the shoulder 23 of the Buchankerrings 24.
  • the second spacer ring 39 protrudes beyond the upstream end of the paragraph 23 out.
  • the flange 13 is first attached to the downstream end of the tie rod 47 on the rotor disk 9, which adjoins the Blisks downstream. This is done by means of the screw 41.
  • the Blisks 6 are pushed onto the tie rod 47.
  • the Switzerlandankerring 24 is then attached by means of the screw 32 on the tie rod 47.
  • the first spacer ring 31, the inner bearing ring 26 and the second spacer ring 39 are pushed over the Ceiankerring 24.
  • the tie rod nut 37 is screwed onto the external thread 22 of the Ceiankerrings 24 and tightened.
  • the compressive forces must be large enough to hold the blisks 6 together. But you must not too big be so that the claimed to train components of the device 3, namely the Glasankerring 24, the external thread 22 on the tie rod 24 or the internal thread of the tie nut 37, the tie rod 47, the screw 32 and the screw 41 are not overloaded during operation.
  • the vortex rectifier 38 is mounted on the downstream side of the rotor disk 9 adjacent to the blisks in both the first and second embodiments so as to be located between the rotor disk 9 and a rotor disk 4 adjacent to this rotor disk 9 ,
  • thermally and mechanically highly resilient materials are used as materials for the components of the device for clamping rotor disks of a jet engine.
  • the materials of the loaded on train components must have a high tensile strength.
  • the tie rod 12, 47 and the rotor disc 9 must also have a high bending stiffness.
  • the pressure-loaded components must accordingly have a high compressive strength. All components of the devices must also have a high fatigue strength.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Die Erfindung betrifft ein Strahltriebwerk mit einer Vorrichtung zum Einspannen von beschaufelten Rotorscheiben und ein Verfahren zum Einspannen von beschaufelten Rotorscheiben mit der Vorrichtung in einem Strahltriebwerk.The invention relates to a jet engine with a device for clamping bladed rotor disks and a method for clamping bladed rotor disks with the device in a jet engine.

In Turbinentriebwerken werden die Turbine und der Verdichter üblicherweise auf einer Welle angeordnet. Insbesondere bei axial durchströmter Bauweise besteht der Verdichter hierbei aus mehreren Rotorscheiben, die jeweils eine Schaufelreihe tragen und untereinander verschweißt oder verschraubt sind.In turbine engines, the turbine and compressor are usually arranged on a shaft. In particular, in axial flow design, the compressor consists of several rotor discs, each carrying a row of blades and are welded or bolted together.

Bei einigen Verdichtern besteht nur ein Teil des Verdichters auf der Eintrittsseite aus Blisks (bladed disks), bei denen jeweils eine Scheibe mit den zugehörigen Schaufeln integral geformt ist. Speziell im vorderen Teil der Trommel lassen sich dadurch erhebliche Gewichtseinsparungen erzielen. Zur besseren Austauschbarkeit und Reparatur werden diese meist recht teuren Einzelkomponenten bevorzugt verschraubt statt verschweißt ausgeführt. Hierzu kommen einzelne Flansche in Frage, die jedoch Gewicht hinzufügen und das rotordynamische Verhalten verschlechtern.In some compressors, only part of the compressor on the inlet side consists of blisks, each having a disk integrally formed with the associated blades. Significant weight savings can be achieved especially in the front part of the drum. For better interchangeability and repair these usually quite expensive individual components are preferably screwed instead of welded. For this single flanges come into question, but add weight and worsen the rotor dynamic behavior.

Des weiteren sind auch Anordnungen bekannt, bei denen sämtliche Rotorscheiben des Verdichters oder des gesamten Rotors über Zuganker eingespannt sind.Furthermore, arrangements are also known in which all the rotor disks of the compressor or the entire rotor are clamped by tie rods.

Beim Einspannen einer größeren Anzahl von Scheiben tritt jedoch das Problem auf, dass eine ausreichend große Vorspannkraft über den gesamten Betriebsbereich aufrecht erhalten werden muss, was eine gute Abstimmung des thermischen Verhaltens von Rotor und Zuganker erfordert. Außerdem muss der Zuganker eine gute Steifigkeit aufweisen.When clamping a larger number of disks, however, the problem arises that a sufficiently large biasing force over the entire operating range must be maintained, which requires a good coordination of the thermal behavior of the rotor and tie rods. In addition, the tie rod must have good rigidity.

Bei einer Verwendung von Zugankern ergeben sich außerdem Probleme bei der Demontage der Blisks im Schadensfall. Es muss immer der gesamte Rotor oder zumindest der gesamte Verdichter demontiert werden, um die Blisks austauschen zu können. Außerdem können vorhandene Wirbelgleichrichter, z.B. in Röhrenbauweise, nur schwer ein- und ausgebaut werden.When using tie rods also arise problems in disassembly of the blisks in case of damage. It is always necessary to disassemble the entire rotor or at least the entire compressor in order to exchange the blisks. In addition, existing vortex rectifiers, e.g. in tubular construction, difficult to install and remove.

Die US 6,267,553 B1 offenbart eine Gasturbine mit einen Hochdruckverdichter, bei dem mehrere rohrförmige Zuganker vorhanden sind. Die Zuganker sind durch Öffnungen in den Rotorscheiben geführt, die radial um die Scheibenmitte angeordnet sind. Das Verspannen erfolgt über Schrauben, die in die Innengewinde der Zuganker eingeschraubt sind.The US 6,267,553 B1 discloses a gas turbine with a high pressure compressor in which there are a plurality of tubular tie rods. The tie rods are guided through openings in the rotor disks, which are arranged radially around the center of the disk. The bracing is done by screws, which are screwed into the internal thread of the tie rods.

Die US 5,537,814 beschreibt einen Zuganker für einen Gasturbinenantrieb, der nicht nur die Rotorscheiben des Verdichters, sondern auch die der Turbine einspannt. Der Zuganker ist hier eine Hohlwelle, die mit der Blisk in der ersten Stufe verschraubt ist. Stromab eines radialen Verdichterlaufrades ist eine Mutter auf ein Gewinde des Zugankers aufgeschraubt, um den Zuganker zu spannen.The US 5,537,814 describes a tie rod for a gas turbine engine that clamps not only the rotor disks of the compressor but also those of the turbine. The tie rod here is a hollow shaft, which is bolted to the blisk in the first stage. Downstream of a radial compressor impeller, a nut is threaded onto a thread of the tie rod to tension the tie rod.

Die DE 10 2005 052 819 A1 offenbart einen Verdichterrotor eines Strahltriebwerks mit allen Merkmalen des Oberbegriffs der Anprüche 1 und 9, wobei der Verdichterrotor aus Blisks zusammengesetzt und mittels eines zentralen Zugankers verspannt ist.The DE 10 2005 052 819 A1 discloses a compressor rotor of a jet engine with all features of the preamble of Anprüche 1 and 9, wherein the compressor rotor is composed of Blisks and braced by a central tie rod.

Die Durchführung eines Zugankers durch die Scheiben erfordert zusätzliche Bohrungen in den Scheiben oder vergrößerte Scheibeninnendurchmesser, wodurch sich das Scheibengewicht erhöht.The passage of a tie rod through the discs requires additional holes in the discs or increased disc inside diameter, which increases the weight of the disc.

Eine ungeteilte Welle erlaubt außerdem keinen separaten modularen Aufbau von Verdichter und Turbine. Die Luftdurchführung eines ggf. vorhandenen Wirbelgleichrichters ist erschwert.An undivided shaft also allows no separate modular design of compressor and turbine. The air passage of a possibly existing vortex rectifier is difficult.

Die Länge des Zugankers sowie verschiedene Materialien und Ausdehnungskoeffizienten der Scheiben erschweren die thermische Abstimmung zwischen Welle und Rotor und damit den Erhalt einer gleichmäßigen Vorspannkraft. Die während des Betriebs variable Vorspannkraft und die Länge des Zugankers verschlechtern die Steifigkeit des Rotors.The length of the tie rod and various materials and expansion coefficients of the discs complicate the thermal balance between the shaft and rotor and thus maintaining a uniform biasing force. The variable during operation biasing force and the length of the tie rod deteriorate the rigidity of the rotor.

Für eine möglichst geringe thermische Beanspruchung und daher geringes Gewicht der Scheiben sollte der Temperaturgradient entlang der Scheibe relativ gering sein. Da die Temperatur am Rotoraußendurchmesser von Stufe zu Stufe zunimmt, führt die gleichmäßige Temperatur im Rotorinnern jedoch bei einzelnen Scheiben zu erheblichen Temperaturgradienten.For the lowest possible thermal stress and therefore low weight of the disks, the temperature gradient along the disk should be relatively low. However, since the temperature at the rotor outer diameter increases from stage to stage, the uniform temperature inside the rotor leads to considerable temperature gradients for individual disks.

Der Erfindung liegt daher die Aufgabe zugrunde, in einem Strahltriebwerk eine Vorrichtung zum Einspannen von beschaufelten Rotorscheiben zu schaffen, die leicht montierbar und demontierbar ist.The invention is therefore an object of the invention to provide a device for clamping bladed rotor discs in a jet engine, which is easy to assemble and disassemble.

Diese Aufgabe wird durch ein Strahltriebwerk mit einer Vorrichtung zum Einspannen von beschaufelten Rotorscheiben sowhol mit den Merkmalen des Anspruchs 1 als auch alternativ hierzu mit den Merkmalen des Anspruchs 9 gelöst. Weiterhin wird die Aufgabe durch ein Verfahren zum Einspannen von beschaufelten Rotorscheiben mit den Merkmalen des Anspruchs 15 gelöst. Die Unteransprüche enthalten vorteilhafte Weiterbildungen der Erfindung.This object is achieved by a jet engine with a device for clamping bladed rotor disks sowhol with the features of claim 1 and, alternatively, this with the features of claim 9. Furthermore, the object is achieved by a method for clamping bladed rotor disks having the features of claim 15. The dependent claims contain advantageous developments of the invention.

Das Einspannen der Blisks mit Hilfe eines Zugankers ermöglicht eine einfache Montage und Demontage sowohl beim Einbau als auch bei der Wartung oder im Schadensfall. Die Blisks können dabei einfach ein- bzw. ausgebaut werden, ohne dass z.B. mehrfache Verschraubungen gelöst werden müssen. Dadurch, dass die Blisks getrennt von den übrigen Rotorscheiben eingespannt sind, ergeben sich für den Zuganker eine kurze Baulänge und damit eine gute Steifigkeit.The clamping of the blisks with the help of a tie rod allows easy assembly and disassembly both during installation and during maintenance or in case of damage. The blisks can be easily installed or removed without, e.g. multiple glands must be solved. The fact that the blisks are clamped separately from the other rotor discs, resulting in the tie rod a short overall length and thus good rigidity.

Der Zuganker ist im Wesentlichen rohrförmig ausgebildet, innerhalb von zentralen Öffnungen in den als Blisks ausgebildeten Rotorscheiben angeordnet und fest mit einer Welle verbunden, die durch mindestens einen Turbinenabschnitt angetrieben wird. Die ohnehin in den Blisks vorhandenen zentralen Öffnungen können gut zur Montage und Demontage des Zugankers verwendet werden, und es sind keine zusätzlichen Bohrungen in den Scheiben erforderlich. Der Zuganker wird nicht durch die in Strömungsrichtung auf die Blisks folgenden Rotorscheiben hindurchgeführt, so dass die Scheibendurchmesser dieser Rotorscheiben nicht vergrößert werden müssen.The tie rod is substantially tubular, disposed within central apertures in the blisk-formed rotor discs, and fixedly connected to a shaft which is driven by at least one turbine section. The existing in the blisks anyway central openings can be used well for mounting and dismounting of the tie rod, and there are no additional holes in the discs required. The tie rod is not passed through the rotor discs following in the flow direction on the Blisks, so that the disc diameter of these rotor discs need not be increased.

Die Blisks sind mittels des Zugankers zwischen mindestens einer ersten Anordnung, die stromauf der Blisks liegt, und mindestens einer zweiten Anordnung, die stromab der Blisks liegt und mit einer Rotorscheibe verbunden ist, die stromab an die Blisks angrenzt, eingespannt. Auf diese Weise wird bewirkt, dass die Blisks unabhängig von der Verbindung zwischen den übrigen Rotorscheiben eingespannt werden können.The blisks are by means of the tie rod between at least a first arrangement, which is upstream of the Blisks, and at least one second arrangement, downstream of the Blisks is located and connected to a rotor disk which is adjacent to the Blisks, clamped. In this way it is ensured that the blisks can be clamped independently of the connection between the other rotor disks.

Dabei umfasst die erste Anordnung eine Anschlaganordnung und die zweite Anordnung eine Spannanordnung. Durch die Spannanordnung können die Blisks gegenüber der Anschlaganordnung auf einfache Weise verspannt werden.In this case, the first arrangement comprises a stop arrangement and the second arrangement comprises a clamping arrangement. Due to the clamping arrangement, the blisks can be clamped in a simple manner relative to the stop arrangement.

Die Anschlaganordnung umfasst stromauf der Blisks eine Verlängerung einer Blisk der ersten Stufe, die an einen Anschlag am Zuganker angrenzt. Dies stellt eine einfache Ausführungsform einer Anschlaganordnung dar.The stop assembly includes upstream of the blisk an extension of a blisk of the first stage adjacent to a stop on the tie rod. This represents a simple embodiment of a stop arrangement.

Die Spannanordnung umfasst vorzugsweise mindestens ein Spannelement, das zur Kraftübertragung zwischen dem Zuganker und der Rotorscheibe dient.The tensioning arrangement preferably comprises at least one tensioning element which serves to transmit power between the tensioning armature and the rotor disk.

Das Spannelement ist im Wesentlichen ringförmig und weist einen flanschförmigen, radial nach außen gerichteten Befestigungsabschnitt, einen axialen rohrförmigen Mittenabschnitt und einen radial nach innen gerichteten Spannabschnitt auf. Dadurch ist eine Kraftübertragung möglich, die gleichmäßig über den Umfang erfolgt.The tensioning element is substantially annular and has a flange-shaped, radially outwardly directed attachment portion, an axial tubular center portion and a radially inwardly directed tension portion. As a result, a power transmission is possible, which takes place uniformly over the circumference.

Der radial nach außen gerichtete Befestigungsabschnitt des Spannelements ist an einem Abschnitt der Rotorscheibe, die stromab an die Blisks angrenzt, befestigt. Dadurch wird die im Spannelement und im Zuganker erzeugte Spannung auf die Rotorscheibe übertragen.The radially outwardly directed attachment portion of the tension member is secured to a portion of the rotor disc which is adjacent to the blisks downstream. As a result, the voltage generated in the clamping element and in the tie rod is transmitted to the rotor disk.

Der radial nach außen gerichtete Befestigungsabschnitt des Spannelements ist an einem radial innen liegenden Abschnitt der Rotorscheibe, die stromab an die Blisks angrenzt, befestigt.The radially outwardly directed attachment portion of the clamping element is located on a radially inner portion attached to the rotor disk, which is adjacent to the Blisks downstream.

Vorteilhaft ist der Befestigungsabschnitt des Spannelements an einem radial innen liegenden Abschnitt der Rotorscheibe, die stromab an die Blisks angrenzt, befestigt. Die Kraftübertragung erfolgt in diesem Fall ohne größere Umlenkungen.Advantageously, the attachment portion of the tensioning element is attached to a radially inner portion of the rotor disc, which is adjacent to the Blisks downstream. The power transmission takes place in this case without major deflections.

Vorzugsweise weist der Zuganker an seinem stromab liegenden Ende einen Absatz auf, dessen Außendurchmesser kleiner ist als der Außendurchmesser eines stromauf angrenzenden Abschnittes des Zugankers, und der radial nach innen gerichtete Spannabschnitt des Spannelements umschließt den Absatz radial, wobei der radial nach innen gerichtete Spannabschnitt des Spannelements gegenüber dem Absatz axial verschiebbar und im Betrieb von einer axialen Begrenzung des Absatzes beabstandet ist und an das Spannmittel angrenzt. Diese Anordnung bietet den Vorteil eines geringen Bauaufwands und guter Montier- und Demontierbarkeit.Preferably, the tie rod has at its downstream end a shoulder whose outer diameter is smaller than the outer diameter of an upstream adjacent portion of the tie rod, and the radially inwardly directed clamping portion of the clamping element enclosing the shoulder radially, wherein the radially inwardly directed clamping portion of the clamping element axially displaceable relative to the shoulder and spaced from an axial boundary of the shoulder in operation and adjacent to the clamping means. This arrangement offers the advantage of a low construction cost and good mounting and dismounting.

Das Spannmittel kann insbesondere eine Zugankermutter sein, die auf ein Außengewinde am Absatz des Zugankers aufschraubbar ist. Durch die Zugankermutter ist die Spannung zwischen den Blisks gut einstellbar.The tensioning means may in particular be a tie-rod nut, which can be screwed onto an external thread on the shoulder of the tie rod. Due to the tie rod nut, the tension between the blisks is easily adjustable.

Alternativ umfassen die erste Anordnung stromauf der Blisks eine Spannanordnung mit einem Spannmittel und die zweite Anordnung stromab der Blisks mindestens eine Schraubenverbindung zwischen dem Zuganker und der Rotorscheibe. Diese Alternative bietet eine gute Zugänglichkeit zum Spannmittel.Alternatively, the first arrangement upstream of the blisk comprises a tensioning arrangement with a tensioning means and the second arrangement downstream of the blisk comprises at least one screw connection between the tensioning bolt and the rotor disk. This alternative offers good accessibility to the clamping device.

Vorzugsweise grenzt das stromauf liegende Ende des Zugankers radial von innen an eine rohrförmige stromauf gerichtete Verlängerung der Blisk der ersten Stufe an. Das Spannmittel grenzt axial an die Verlängerung und radial an den Zugankerring an, der an das stromauf liegende Ende des Zugankers angrenzt, und der Zuganker weist an seinem stromab liegenden Ende einen Flansch auf, der an der Rotorscheibe, die stromab an die Blisks angrenzt, angebracht ist. Hier dient die erste Anordnung zum Erzeugen einer Spannung gegenüber der Rotorscheibe, die stromab an die Blisks angrenzt, und weist einen sehr geringen Bauaufwand auf. Das Spannmittel ist von der Verdichtereintrittsseite gut zugänglich.Preferably, the upstream end of the tie rod radially adjoins from the inside to a tubular upstream Prolonging the first level blisk. The tensioning means is axially adjacent to the extension and radially to the tensioning ring adjacent to the upstream end of the tie rod, and the tension anchor has a flange at its downstream end which attaches to the rotor disc which is adjacent to the blisk downstream is. Here, the first arrangement serves to generate a voltage with respect to the rotor disk, which is adjacent to the Blisks downstream, and has a very low construction costs. The clamping device is easily accessible from the compressor inlet side.

Der Zuganker weist in Strömungsrichtung eine konische Erweiterung auf, und der Flansch des Zugankers ist an einem radial außen liegenden Abschnitt der Rotorscheibe, die stromab an die Blisks angrenzt, befestigt. Dadurch wird ein Spannen der Blisks nahe der Schaufel ermöglicht, und es wird eine gute Abdichtung zwischen den Blisks erreicht. Bei einer Befestigung am radial außen liegenden Abschnitt der Rotorscheibe, die stromab an die Blisks angrenzt, tritt eine geringe Biegebeanspruchung der Rotorscheibe beim Spannen des Zugankers auf.The tie rod has a conical extension in the flow direction, and the flange of the tie rod is attached to a radially outer portion of the rotor disc, which is adjacent to the Blisks downstream. This allows for clamping of the blisks near the blade and good sealing between the blisks. When attached to the radially outer portion of the rotor disc, which is adjacent to the Blisks downstream, occurs a low bending stress of the rotor disc during tensioning of the tie rod.

Das stromauf liegende Ende des Zugankers ist mit mindestens einer Schraubenverbindungen an dem Zugankerring befestigt, der ein Außengewinde aufweist, und das Spannmittel ist eine Zugankermutter, die auf das Außengewinde des Zugankerrings aufschraubbar ist. Durch die Zugankermutter ist die Spannung im Zugankerring, in den Schraubenverbindungen und im Zuganker gut einstellbar.The upstream end of the tie rod is fastened to the tie rod ring with at least one screw connection, which has an external thread, and the tensioning means is a tie nut, which is screwed onto the external thread of the Zugankerrings. The tie-rod nut makes it easy to adjust the tension in the tie rod ring, in the screw connections and in the tie rod.

Vorzugsweise spannt das Spannmittel gleichzeitig einen radial innen liegenden Lagerring eines Zugankerlagers ein. Dadurch sind keine zusätzlichen Bauteile zur Befestigung des Lagerrings erforderlich.Preferably, the clamping means simultaneously clamps a radially inner bearing ring of a Zugankerlagers. As a result, no additional components for mounting the bearing ring are required.

Mindestens ein Wirbelgleichrichter in Röhrenbauweise kann an der Rotorscheibe, die stromab an die Blisks angrenzt, befestigt sein. Durch den Wirbelgleichrichter strömt komprimierte, erwärmte Luft in radialer Richtung von außen nach innen und wird zur Kühlung zur Turbine geleitet. Durch Anordnung des Wirbelgleichrichters außerhalb der Blisks wird eine lokale Erwärmung im Scheibenbereich der Blisks vermieden. Auch ist die Befestigung der Wirbelgleichrichter außerhalb der Blisks leichter möglich.At least one tube-type vortex rectifier may be attached to the rotor disc adjacent the blisks downstream. The vortex rectifier flows compressed, heated air in the radial direction from outside to inside and is passed to the turbine for cooling. By placing the vortex rectifier outside the blisks, local heating in the disk area of the blisks is avoided. Also, the attachment of the vortex rectifier outside the blisks is easier.

Außerdem wird die Aufgabe durch ein Verfahren zum Einspannen von Blisks unter Verwendung des oben beschriebenen Strahltriebwerks gelöst, bei dem die Blisks mittels des Zugankers lösbar eingespannt und die anderen Rotorscheiben separat und unabhängig vom Zuganker fest miteinander verbunden werden. Das separate Einspannen der Blisks ermöglicht eine einfache Montage und Demontage der Blisks.In addition, the object is achieved by a method for clamping blisks using the jet engine described above, in which the blisks are releasably clamped by means of the tie rod and the other rotor discs are connected separately and independently of the tie rod firmly together. The separate clamping of the blisks allows for easy assembly and disassembly of the blisks.

Insbesondere werden die Blisks mittels des Zugankers zwischen einer Anordnung, die stromauf der Blisks liegt, und einer Anordnung, die stromab der Blisks liegt und mit einer Rotorscheibe verbunden ist, die stromab an die Blisks angrenzt, eingespannt. Durch die beiden Anordnungen wird das Aufbringen einer Kraft auf den Zuganker ermöglicht.In particular, the blisks are clamped by means of the tie rod between an assembly located upstream of the blisk and an assembly located downstream of the blisk and connected to a rotor disc adjacent the blisks downstream. By the two arrangements, the application of a force on the tie rod is made possible.

Der Zuganker wird von der stromab der Blisks liegenden zweiten Anordnung aus gespannt.The tie rod is tensioned by the second arrangement located downstream of the blisks.

Alternativ kann der Zuganker von der stromauf der Blisks liegenden ersten Anordnung aus gespannt werden. Hierbei ist eine gute Zugänglichkeit der Anordnung gegeben.Alternatively, the tie rod can be stretched from the first arrangement located upstream of the blisk. Here, a good accessibility of the arrangement is given.

Zwei Alternativ beispiele des erfindungsgemäßen Strahltriebwerks mit einer Vorrichtung zum Einspannen von beschaufelten Rotorscheiben werden anhand der Figuren 1 bis 4 näher erläutert. Es zeigt:

Fig. 1
die erste Ausführungsform mit einer ersten Vorrichtung, bei der der Zuganker von der stromab der Blisks liegenden Seite gespannt wird,
Fig. 2
eine Detailansicht der Spannvorrichtung der ersten Ausführungsform,
Fig. 3
die zweite und alternative Ausführungsform mit einer zweiten Vorrichtung, bei der der Zuganker von der stromauf der Blisks liegenden Seite gespannt wird, und
Fig. 4
eine Detailansicht der Spannanordnung der zweiten Ausführungsform.
Two alternative examples of the jet engine according to the invention with a device for clamping bladed rotor disks are based on the FIGS. 1 to 4 explained in more detail. It shows:
Fig. 1
the first embodiment with a first device in which the tie rod is tensioned by the side lying downstream of the blisk,
Fig. 2
a detailed view of the clamping device of the first embodiment,
Fig. 3
the second and alternative embodiment with a second device in which the tie rod is stretched from the side lying upstream of the Blisks, and
Fig. 4
a detailed view of the clamping arrangement of the second embodiment.

In Fig. 1 ist ein Rotor 1 eines axialen Verdichters mit neun Stufen dargestellt, der sechs als Blisks 6 ausgebildete Rotorscheiben, drei Rotorscheiben 4, 9 mit Laufschaufeln 5, und mindestens einen Wirbelgleichrichter 38 aufweist. Außerdem weist der Rotor 1 eine erste Vorrichtung 3 des erfindungsgemäßen Strahltriebwerks zum Einspannen der Blisks 6 auf.In Fig. 1 1, a rotor 1 of a nine-stage axial compressor is shown, which has six rotor disks formed as blisks 6, three rotor disks 4, 9 with rotor blades 5, and at least one vortex rectifier 38. In addition, the rotor 1 has a first device 3 of the jet engine according to the invention for clamping the blisks 6.

Auf dem Rotor 1 des Verdichters sind die in Strömungsrichtung 40 ersten sechs beschaufelten Rotorscheiben 6 als Blisks 6 ausgeführt. Die Blisks (bladed disks) 6 sind beschaufelte Rotorscheiben, bei denen jeweils eine Scheibe mit den zugehörigen Schaufeln integral geformt ist. Auf die Blisks 6 folgen in Strömungsrichtung 40 drei beschaufelte Rotorscheiben 4, 9, deren Laufschaufeln 5 lösbar angebracht sind. Die Rotorscheibe 9 grenzt an die in Strömungsrichtung 40 letzte Blisk 6 an. Es kann jedoch auch eine andere Anzahl von Blisks 6 und Rotorscheiben 4, 9 verwendet werden. Auch die Anzahl der Stufen ist variabel. Jede Blisk 6 weist nahe den Laufschaufeln 5 mindestens eine axiale Verlängerung 44 auf, die jeweils an mindestens eine benachbarte Blisk 6 anstößt. Die Rotorscheibe 9 stößt nahe den Laufschaufeln 5 mit einer axialen Verlängerung 43 an die in Strömungsrichtung 40 letzte Blisk 6 an.On the rotor 1 of the compressor, the first six bladed rotor disks 6 in the flow direction 40 are designed as blisks 6. The blisks 6 are bladed rotor disks in which one disk is integrally formed with the associated blades. On the Blisks 6 follow in the flow direction 40 three bladed Rotor disks 4, 9, the blades 5 are releasably attached. The rotor disk 9 adjoins the last blisk 6 in the flow direction 40. However, it is also possible to use a different number of blisks 6 and rotor disks 4, 9. The number of levels is variable. Each blisk 6 has close to the rotor blades 5 at least one axial extension 44, which abuts at least one adjacent blisk 6 respectively. The rotor disk 9 abuts close to the rotor blades 5 with an axial extension 43 to the last in the flow direction 40 Blisk 6.

Die in Fig. 1 und Fig. 2 dargestellte erste Ausführungsform der Vorrichtung 3 umfasst einen Zuganker 12, eine Anschlaganordnung 27 und eine Spannanordnung 28, die in Fig. 2 vergrößert dargestellt ist.In the Fig. 1 and Fig. 2 illustrated first embodiment of the device 3 comprises a tie rod 12, a stop assembly 27 and a clamping assembly 28, which in Fig. 2 is shown enlarged.

Der Zuganker 12 ist rohrförmig ausgebildet und weist an seinem stromauf liegenden Ende 21 einen radial nach innen zurückgesetzten Absatz 42 mit einem Anschlag 16 auf. An seinem stromab liegenden Ende 14 (Fig. 2) ist ein Absatz 15 vorgesehen, der gegenüber einem axialen Abschnitt 19 des Zugankers 12 radial nach innen zurückgesetzt ist und durch eine axiale Begrenzung 17 entgegen der Strömungsrichtung 40 begrenzt ist. Der Absatz 15 kann außerdem einen Zahnkranz aufweisen. An den Absatz 15 grenzt stromab ein Außengewinde 18 an, dessen Außendurchmesser kleiner ist als der Außendurchmesser des Absatzes 15.The tie rod 12 is tubular and has at its upstream end 21 a radially inwardly recessed shoulder 42 with a stop 16. At its downstream end 14 (FIG. Fig. 2 ), a shoulder 15 is provided, which is set back radially inwardly relative to an axial section 19 of the tie rod 12 and is limited by an axial boundary 17 against the flow direction 40. The shoulder 15 may also have a sprocket. An external thread 18, whose outside diameter is smaller than the outside diameter of the shoulder 15, adjoins the shoulder 15 downstream.

Der Zuganker 12 ist innerhalb von Öffnungen 8 in den Blisks 6 mittig angeordnet. Er grenzt an seinem stromauf liegenden Ende 21 in der Anschlaganordnung 27 an eine Blisk 6 der ersten Stufe des Verdichters an. An seinem stromab liegenden Ende 14 ist der Zuganker 12 über die Spannanordnung 28 mit der stromab an die Blisks 6 angrenzende Rotorscheibe 9 verbunden.The tie rod 12 is disposed centrally within openings 8 in the blisks 6. It adjoins at its upstream end 21 in the stop assembly 27 to a blisk 6 of the first stage of the compressor. At its downstream end 14 of the tie rod 12 is connected via the clamping assembly 28 with the downstream of the Blisks 6 rotor disk 9.

Die Anschlaganordnung 27 befindet sich an dem stromauf liegenden Ende 21 des Zugankers 12 und wird durch einen Anschlag 16, einen Absatz 42 und eine Verlängerung 7 der Blisk 6 der ersten Stufe des Verdichters gebildet.The stop assembly 27 is located at the upstream end 21 of the tie rod 12 and is formed by a stop 16, a shoulder 42 and an extension 7 of the blisk 6 of the first stage of the compressor.

Der Anschlag 16 bildet eine axiale Begrenzung des Absatzes 42 in Strömungsrichtung 40. Die Verlängerung 7 der Blisk 6 der ersten Stufe des Verdichters erstreckt sich axial entgegen der Strömungsrichtung 40 bis zum Anschlag 16. Sie umschließt den Absatz 16 radial, wobei sie aber axial verschiebbar ist.The stop 16 forms an axial boundary of the shoulder 42 in the flow direction 40. The extension 7 of the blisk 6 of the first stage of the compressor extends axially against the flow direction 40 to the stop 16. It encloses the shoulder 16 radially, but it is axially displaceable ,

Die in Fig. 2 vergrößert dargestellte Spannanordnung 28 umfasst den Absatz 15 des Zugankers 12, ein Spannelement 33, eine Zugankermutter 37, mehrere Schraubenverbindungen 29 und grenzt an die Rotorscheibe 9, die stromab an die Blisks angrenzt, an.In the Fig. 2 enlarged clamping arrangement 28 includes the shoulder 15 of the tie rod 12, a clamping element 33, a tie nut 37, a plurality of screw 29 and adjoins the rotor disc 9, which is adjacent to the Blisks downstream, at.

Das Spannelement 33 umfasst einen, einen Flansch bildenden, radialen Befestigungsabschnitt 34, einen Mittenabschnitt 35 und einen Spannabschnitt 36.The clamping element 33 comprises a, a flange forming, radial mounting portion 34, a center portion 35 and a clamping portion 36th

Der Mittenabschnitt 35 des Spannelements 33 ist rohrförmig und verläuft im montierten Zustand axial und parallel zum Zuganker 12. Der flanschartige Befestigungsabschnitt 34 ist vom stromab liegenden Ende des Spannelements 33 aus radial nach außen gerichtet. Der Spannabschnitt 36 ist vom stromauf liegenden Ende des Spannelements 33 aus radial nach innen gerichtet und kann einen Zahnkranz aufweisen.The center portion 35 of the clamping element 33 is tubular and extends in the mounted state axially and parallel to the tie rod 12. The flange-like mounting portion 34 is directed from the downstream end of the clamping element 33 from radially outward. The clamping portion 36 is directed radially inward from the upstream end of the clamping element 33 and may have a toothed ring.

Das Spannelement 33 ist mit seinem Befestigungsabschnitt 34 mittels Schraubenverbindungen 29 an einem inneren Abschnitt 10 der Rotorscheibe 9 befestigt. Der Spannabschnitt 36 ragt im zusammengebauten Zustand der Spannvorrichtung 28 parallel zur axialen Begrenzung 17 und in axialer Richtung von dieser beabstandet radial nach innen und umschließt den Absatz 15, wobei der Spannabschnitt 36 aber gegenüber dem Absatz 15 axial verschiebbar ist. Wenn am Absatz 15 und am Spannabschnitt 36 Zahnkränze vorhanden sind, greift die Verzahnung des Spannabschnitts 36 in die Verzahnung des Absatzes 15 ein. In Strömungsrichtung 40 grenzt die Zugankermutter 37, die auf das Außengewinde 18 aufgeschraubt ist, an den Spannabschnitt 36 an.The clamping element 33 is fastened with its fastening section 34 by means of screw connections 29 to an inner section 10 of the rotor disk 9. The clamping portion 36 protrudes in the assembled state of the clamping device 28 parallel to the axial boundary 17 and in the axial direction of this radially inwardly and surrounds the shoulder 15, wherein the clamping portion 36 but against the shoulder 15 is axially displaceable. If sprockets are present on the shoulder 15 and on the tensioning section 36, the toothing of the tensioning section 36 engages in the toothing of the shoulder 15. In the flow direction 40, the tie rod nut 37, which is screwed onto the external thread 18, adjoins the tensioning section 36.

Zum Einspannen der Blisks 6 wird zunächst der als Flansch ausgebildete radial nach außen gerichtete Befestigungsabschnitt 34 des Spannelements 33 mittels mehrerer in Umfangsrichtung verteilter Schraubenverbindungen 29 am inneren Abschnitt 10 der Rotorscheibe 9, die stromab an die Blisks angrenzt, befestigt. Als nächstes werden die Blisks 6 auf den Zuganker 12 aufgeschoben. Der Zuganker 12 wird dann mit dem Absatz 15 in das ringförmige Spannelement 33 eingeführt. Zum Schluss wird die Zugankermutter 37 auf das Außengewinde 18 des Zugankers 12 aufgeschraubt und angezogen.For clamping the blisks 6, the radially outwardly directed fastening section 34 of the clamping element 33 designed as a flange is first fastened by means of a plurality of circumferentially distributed screw connections 29 on the inner section 10 of the rotor disk 9, which adjoins the blisk downstream. Next, the blisks 6 are pushed onto the tie rod 12. The tie rod 12 is then inserted with the shoulder 15 in the annular clamping element 33. Finally, the tie nut 37 is screwed onto the external thread 18 of the tie rod 12 and tightened.

Beim Anziehen der Zugankermutter 37 wird über den radial nach innen gerichteten Spannabschnitt 36 eine Zugkraft im Spannelement 33 erzeugt. Gleichzeitig erzeugt die Zugankermutter 37 über das Außengewinde 18 eine Zugkraft im Zuganker 12.When tightening the tie rod nut 37, a tensile force in the clamping element 33 is generated via the radially inwardly directed clamping portion 36. At the same time, the tie rod nut 37 generates a tensile force in the tie rod 12 via the external thread 18.

Die Zugkraft im Spannelement 33 wird vom radial nach innen gerichteten Spannabschnitt 36 über den axialen Mittenabschnitt 35, den radial nach außen gerichteten Befestigungsabschnitt 34 und die Schraubenverbindungen 29 auf den radial innen liegenden Abschnitt 10 der Rotorscheibe 9 übertragen. Von dort aus wird die Kraft in der Rotorscheibe 9, die stromab an die Blisks angrenzt, in radialer Richtung nach außen bis in die axiale Verlängerung 43 der Rotorscheibe 9 weitergeleitet. Die Zugkraft im Zuganker 12 wird entlang des Zugankers 12 auf den Absatz 16 übertragen.The tensile force in the clamping element 33 is transmitted from the radially inwardly directed clamping section 36 via the axial center section 35, the radially outwardly directed fastening section 34 and the screw connections 29 to the radially inner section 10 of the rotor disk 9. From there, the force in the rotor disk 9, which is adjacent to the Blisks downstream, in the radial direction outward into the axial extension 43rd the rotor disk 9 forwarded. The tensile force in the tie rod 12 is transmitted along the tie rod 12 on the shoulder 16.

Die beiden Zugkräfte bewirken Druckkräfte zwischen der axialen Verlängerung 43 der Rotorscheibe 9, den über die Verlängerungen 44 aneinander stoßenden Blisks 6 und dem Anschlag 16 der stromauf liegenden Anschlaganordnung 27. Diese Druckkräfte drücken die Blisks 6 an den Verlängerungen 44 der Blisks 6 nahe den Schaufeln 5 axial aneinander und bewirken so die Einspannung.The two tensile forces cause compressive forces between the axial extension 43 of the rotor disk 9, the abutting blisks 6 and the abutment 16 of the upstream abutment arrangement 27 via the extensions 44. These compressive forces press the blisks 6 against the extensions 44 of the blisks 6 near the blades 5 axially together and cause the restraint.

Die Druckkräfte müssen groß genug sein, um die Blisks 6 zusammenzuhalten. Sie dürfen aber auch nicht zu groß sein, damit die auf Zug beanspruchten Bauelemente der Vorrichtung 3, nämlich der Zuganker 12, das Außengewinde 18 am Zuganker 12, das Spannelement 33, die Schraubenverbindungen 29 oder das Innengewinde der Zugankermutter 37 im Betrieb nicht überlastet werden.The compressive forces must be large enough to hold the blisks 6 together. But they must also not be too large, so that the tensile stressed components of the device 3, namely the tie rod 12, the external thread 18 on the tie rod 12, the clamping element 33, the screw 29 or the internal thread of the tie nut 37 are not overloaded during operation.

In den Fig. 3 und 4 ist die zweite und alternative Ausführungsform der Vorrichtung 3 des erfindungsgemäßen Strahltriebwerks dargestellt, bei der der Rotor 1 des Verdichters genauso aufgebaut ist wie in Fig. 1.In the Fig. 3 and 4 shows the second and alternative embodiment of the device 3 of the jet engine according to the invention, in which the rotor 1 of the compressor is constructed the same as in Fig. 1 ,

Die zweite Ausführungsform der Vorrichtung 3 umfasst einen Zuganker 47, mehrere Schraubenverbindungen 41 und eine Spannanordnung 30, die in Fig. 4 vergrößert dargestellt ist.The second embodiment of the device 3 comprises a tie rod 47, a plurality of screw connections 41 and a clamping arrangement 30, which in Fig. 4 is shown enlarged.

Der Zuganker 47 weist im Gegensatz zum Zuganker 12 der ersten Ausführungsform in Strömungsrichtung 40 eine konische Erweiterung 20 auf. An seinem stromauf liegenden Ende 21 besitzt der Zuganker 47 einen radial nach innen gerichteten Flansch 45. Die konische Erweiterung weist an ihrem stromab liegenden Ende einen Flansch 13 auf, der radial nach außen gerichtet ist.In contrast to the tie rod 12 of the first embodiment, the tie rod 47 has a conical enlargement 20 in the flow direction 40. At its upstream end 21 of the tie rod 47 has a radially inwardly directed flange 45. The conical extension points its downstream end a flange 13 which is directed radially outward.

Der Zuganker 47 ist mittig innerhalb von Öffnungen 8 in den Blisks 6 angeordnet. Er grenzt an seinem stromauf liegenden Ende 21 radial von innen an eine axiale Verlängerung 7 der Blisk 6 der ersten Stufe des Verdichters an. An seinem stromab liegenden Ende ist der Zuganker 47 über mehrere über den Umfang verteilte Schraubenverbindungen 41 mit der an die Blisks 6 angrenzende Rotorscheibe 9, die stromab an die Blisks angrenzt, verbunden.The tie rod 47 is arranged centrally within openings 8 in the blisks 6. It adjoins at its upstream end 21 radially from the inside to an axial extension 7 of the blisk 6 of the first stage of the compressor. At its downstream end, the tie rod 47 is connected via a plurality of screw connections 41 distributed over the circumference to the rotor disk 9 adjoining the blisks 6 and adjoining the blisks downstream.

Die Schraubenverbindungen 41 sind an einem radial außen liegenden Abschnitt 11 der Rotorscheibe 9, die stromab an die Blisks angrenzt, in Umfangsrichtung verteilt. Mittels der Schraubenverbindungen 41 ist der Flansch 13 am Ende der konischen Erweiterung 20 des Zugankers 47 an der Rotorscheibe 9 befestigt.The screw connections 41 are distributed in the circumferential direction on a radially outer section 11 of the rotor disk 9, which adjoins the blisks downstream. By means of the screw connections 41, the flange 13 is fastened to the rotor disk 9 at the end of the conical enlargement 20 of the tie rod 47.

Die stromauf liegende Spannanordnung 30 ist in Fig. 4 vergrößert dargestellt und umfasst einen Zugankerring 24, mehrere Schraubenverbindungen 32, einen ersten Abstandsring 31, einen zweiten Abstandsring 39, ein Zugankerlager 25 und eine Zugankermutter 37.The upstream tensioning assembly 30 is in Fig. 4 shown enlarged and includes a Zugankerring 24, a plurality of screw connections 32, a first spacer ring 31, a second spacer ring 39, a Zugankerlager 25 and a Zugankermutter 37th

Der Zugankerring 24 ist ringförmig ausgebildet und weist den gleichen Außendurchmesser auf wie der Zuganker 47. Der Zugankerring 24 weist an seinem an den Zuganker 47 angrenzenden Ende einen radial nach innen gerichteten Flansch 46 auf. Der Zugankerring 24 weist außerdem einen Absatz 23 auf, dessen Außendurchmesser kleiner ist als der Durchmesser des stromauf liegenden Endes 21 des Zugankers 47. Am stromauf liegenden Ende des Zugankerrings 24 befindet sich ein Außengewinde 22, dessen Durchmesser kleiner ist als der des Absatzes 23.The Zugankerring 24 is annular and has the same outer diameter as the tie rod 47. The Zugankerring 24 has at its adjacent to the tie rod 47 end a radially inwardly directed flange 46. The Zugankerring 24 also has a shoulder 23 whose outer diameter is smaller than the diameter of the upstream end 21 of the tie rod 47. At the upstream end of Zugankerrings 24 is an external thread 22 whose diameter is smaller than that of the paragraph 23rd

Der erste Abstandsring 31 ist ringförmig ausgebildet und weist weitgehend den gleichen Innendurchmesser auf wie die axiale Verlängerung 7 der Blisk 6 der ersten Stufe des Verdichters. Der zweite Abstandsring 39 ist ebenfalls ringförmig ausgebildet.The first spacer ring 31 is annular and has substantially the same inner diameter as the axial extension 7 of the blisk 6 of the first stage of the compressor. The second spacer ring 39 is also annular.

Das Zugankerlager 25 ist ein Kugellager mit einem radial innen liegenden Lagerring 26.The tie rod bearing 25 is a ball bearing with a radially inner bearing ring 26th

Der Zugankerring 24 grenzt in axialer Richtung an das stromauf liegende Ende 21 des Zugankers 47 an und bildet eine axiale Verlängerung des Zugankers 47 entgegen der Strömungsrichtung 40. Der Zugankerring 24 ist mittels mehrerer Schraubenverbindungen 32 am Flansch 45 des Zugankers 47 befestigt. In radialer Richtung grenzt der Zugankerring 24 von innen an den ersten Abstandsring 31 an.The Zugankerring 24 abuts in the axial direction of the upstream end 21 of the tie rod 47 and forms an axial extension of the tie rod 47 against the flow direction 40. The Zugankerring 24 is secured by means of several screw 32 on the flange 45 of the tie rod 47. In the radial direction, the Zugankerring 24 abuts the first spacer ring 31 from the inside.

Die Verlängerung 7 umschließt den Zuganker 47 in radialer Richtung, wobei die Verlängerung 7 verschiebbar gegenüber dem Zuganker 47 ist.The extension 7 encloses the tie rod 47 in the radial direction, wherein the extension 7 is displaceable relative to the tie rod 47.

Der erste Abstandsring 31 umschließt den Zuganker 47 im Bereich des Flansches 45 und den Zugankerring 24, wobei aber eine Verschiebbarkeit in axialer Richtung gegeben ist. Der erste Abstandsring 31 grenzt an seinem stromab liegenden Ende an die Verlängerung 7 der Blisk 6 der ersten Stufe des Verdichters an. An seinem stromauf liegenden Ende umschließt der Abstandsring den Absatz 23 des Zugankerrings 24 in radialer Richtung, wobei aber eine Verschiebbarkeit in axialer Richtung gegeben ist.The first spacer ring 31 encloses the tie rod 47 in the region of the flange 45 and the Zugankerring 24, but with a displacement in the axial direction is given. The first spacer ring 31 adjoins the extension 7 of the blisk 6 of the first stage of the compressor at its downstream end. At its upstream end of the spacer ring surrounds the shoulder 23 of the Zugankerrings 24 in the radial direction, but with a displacement in the axial direction is given.

Der innere Lagerring 26 des Zugankerlagers 25 ist in axialer Richtung verschiebbar auf dem Absatz 23 des Zugankerrings 24 angeordnet. Der innere Lagerring 26 grenzt stromab an den ersten Abstandsring 31 und stromauf an den zweiten Abstandsring 39 an.The inner bearing ring 26 of the Zugankerlagers 25 is arranged displaceably in the axial direction on the shoulder 23 of the Zugankerrings 24. The inner bearing ring 26 adjoins the first spacer ring 31 downstream and to the second spacer ring 39 upstream.

Der zweite Abstandsring 39 umschließt ebenfalls den Absatz 23 des Zugankerrings 24. Der zweite Abstandsring 39 ragt dabei über das stromauf liegende Ende des Absatzes 23 hinaus.The second spacer ring 39 also encloses the shoulder 23 of the Zugankerrings 24. The second spacer ring 39 protrudes beyond the upstream end of the paragraph 23 out.

An den zweiten Abstandsring 39 grenzt die Spannmutter 37 an, die auf das Außengewinde 22 des Zugankerrings 24 aufgeschraubt ist.Adjacent to the second spacer ring 39, the clamping nut 37, which is screwed onto the external thread 22 of the Zugankerrings 24.

Zum Einspannen der Blisks 6 wird zunächst der Flansch 13 am stromab liegenden Ende des Zugankers 47 an der Rotorscheibe 9, die stromab an die Blisks angrenzt, befestigt. Dies erfolgt mittels der Schraubenverbindungen 41. Als Nächstes werden die Blisks 6 auf den Zuganker 47 aufgeschoben. Der Zugankerring 24 wird dann mittels der Schraubenverbindungen 32 am Zuganker 47 befestigt. Dann werden der erste Abstandsring 31, der innere Lagerring 26 und der zweite Abstandsring 39 über den Zugankerring 24 geschoben. Zuletzt wird die Zugankermutter 37 auf das Außengewinde 22 des Zugankerrings 24 aufgeschraubt und angezogen.To clamp the blisks 6, the flange 13 is first attached to the downstream end of the tie rod 47 on the rotor disk 9, which adjoins the Blisks downstream. This is done by means of the screw 41. Next, the Blisks 6 are pushed onto the tie rod 47. The Zugankerring 24 is then attached by means of the screw 32 on the tie rod 47. Then, the first spacer ring 31, the inner bearing ring 26 and the second spacer ring 39 are pushed over the Zugankerring 24. Finally, the tie rod nut 37 is screwed onto the external thread 22 of the Zugankerrings 24 and tightened.

Beim Anziehen der Zugankermutter 37 werden im Zuganker 47, im Zugankerring 24 und in den Schraubenverbindungen 41 Zugkräfte erzeugt. Die Zugkräfte werden von den Schraubenverbindungen 41 auf die Rotorscheibe 9 übertragen.When tightening the tie rod nut 37 41 tensile forces are generated in the tie rod 47, in Zugankerring 24 and in the screw 41. The tensile forces are transmitted from the screw 41 to the rotor disk 9.

Gleichzeitig entstehen im zweiten Abstandsring 39, im inneren Lagerring 26, im ersten Abstandsring 31 und in den Verlängerungen 44 der Blisks 6 nahe den Laufschaufeln 5 Druckkräfte, die die Blisks 6 einspannen.At the same time arise in the second spacer ring 39, the inner bearing ring 26, the first spacer ring 31 and the extensions 44 of the Blisks 6 near the blades 5 pressure forces that clamp the Blisks 6.

Die Druckkräfte müssen groß genug sein, um die Blisks 6 zusammenzuhalten. Sie dürfen aber auch nicht zu groß sein, damit die auf Zug beanspruchten Bauelemente der Vorrichtung 3, nämlich der Zugankerring 24, das Außengewinde 22 am Zugankerring 24 oder das Innengewinde der Zugankermutter 37, der Zuganker 47, die Schraubenverbindungen 32 und die Schraubenverbindungen 41 im Betrieb nicht überlastet werden.The compressive forces must be large enough to hold the blisks 6 together. But you must not too big be so that the claimed to train components of the device 3, namely the Zugankerring 24, the external thread 22 on the tie rod 24 or the internal thread of the tie nut 37, the tie rod 47, the screw 32 and the screw 41 are not overloaded during operation.

Der Wirbelgleichrichter 38 ist sowohl in der ersten als auch in der zweiten Ausführungsform an der stromab liegenden Seite der Rotorscheibe 9, die stromab an die Blisks angrenzt, angebracht, so dass er sich zwischen der Rotorscheibe 9 und einer an diese Rotorscheibe 9 angrenzenden Rotorscheibe 4 befindet.The vortex rectifier 38 is mounted on the downstream side of the rotor disk 9 adjacent to the blisks in both the first and second embodiments so as to be located between the rotor disk 9 and a rotor disk 4 adjacent to this rotor disk 9 ,

Als Werkstoffe für die Bauelemente der Vorrichtung zum Einspannen von Rotorscheiben eines Strahltriebwerks werden thermisch und mechanisch hoch belastbare Werkstoffe verwendet. Die Werkstoffe der auf Zug belasteten Bauelemente müssen eine hohe Zugfestigkeit aufweisen. Insbesondere der Zuganker 12, 47 und die Rotorscheibe 9 müssen außerdem eine hohe Biegesteifigkeit aufweisen. Die auf Druck belasteten Bauelemente müssen entsprechend eine hohe Druckfestigkeit aufweisen. Alle Bauelemente der Vorrichtungen müssen außerdem eine hohe Dauerfestigkeit aufweisen.As materials for the components of the device for clamping rotor disks of a jet engine thermally and mechanically highly resilient materials are used. The materials of the loaded on train components must have a high tensile strength. In particular, the tie rod 12, 47 and the rotor disc 9 must also have a high bending stiffness. The pressure-loaded components must accordingly have a high compressive strength. All components of the devices must also have a high fatigue strength.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Rotorrotor
33
Vorrichtungcontraption
44
Rotorscheiberotor disc
55
Laufschaufelblade
66
Rotorscheibe (Blisk)Rotor disk (blisk)
77
Verlängerungrenewal
88th
Öffnungopening
99
Rotorscheiberotor disc
1010
Abschnittsection
1111
Abschnittsection
1212
Zugankertie rods
1313
Flanschflange
1414
Ende des Zugankers (stromab)End of tie rod (downstream)
1515
Absatzparagraph
1616
Anschlagattack
1717
axiale Begrenzungaxial limitation
1818
Außengewindeexternal thread
1919
Abschnittsection
2020
Erweiterungextension
2121
Ende des Zugankers (stromauf)End of tie rod (upstream)
2222
Außengewindeexternal thread
2323
Absatzparagraph
2424
ZugankerringZugankerring
2525
ZugankerlagerZugankerlager
2626
Lagerringbearing ring
2727
Anschlaganordnungstop assembly
2828
Spannanordnungtensioning assembly
2929
Schraubenverbindungscrew connection
3030
Spannanordnungtensioning assembly
3131
Abstandsringspacer ring
3232
Schraubenverbindungscrew connection
3333
Spannelementclamping element
3434
Befestigungsabschnitt (Flansch)Fixing section (flange)
3535
Mittenabschnittmid section
3636
Spannabschnittclamping section
3737
ZugankermutterZugankermutter
3838
WirbelgleichrichterVortex reducer
3939
Abstandsringspacer ring
4040
Strömungsrichtungflow direction
4141
Schraubenverbindungscrew connection
4242
Absatzparagraph
4343
Verlängerungrenewal
4444
Verlängerungrenewal
4545
Flanschflange
4646
Flanschflange
4747
Zugankertie rods

Claims (18)

  1. Jet engine with an apparatus (3) for retaining bladed rotor disks (4, 6, 9), with the jet engine essentially including an axial compressor with a rotor (1) which has several bladed rotor disks (4, 6, 9), at least one turbine section, at least one shaft and at least one tie-rod, with at least two bladed rotor disks at the compressor inlet side (2) being designed as blisks (6), each forming a one-piece assembly, integrally combining a rotor disk with circumferentially distributed rotor blades (5),
    characterized in that
    the blisks (6) are releasably retained via a tie-rod (12) and in that the other rotor disks (4, 9) of the compressor rotor (1), the rotor blades (5) of which being releasably attached, are firmly connected to each other, separately and independently of the tie-rod (12), in that the tie rod (12) is essentially tubular, disposed within central apertures (8) in the rotor disks designed as blisks (6) and firmly attached to a shaft driven by at least one turbine section, that the blisks (6) are retained by means of the tie rod (12) between at least one first arrangement (27) disposed upstream of the blisks and at least one second arrangement (28) disposed downstream of the blisks (6) and connected to the rotor disk (9) provided with releasable rotor blades (5), with the rotor disk (9) adjoining the blisks (6) on the downstream side, and in that the first arrangement includes a stopper arrangement (27) and the second arrangement a tensioning arrangement (28), with the stopper arrangement (27) including, upstream of the blisks (6), a protrusion (7) of a blisk (6) of the first compressor stage which adjoins a stopper (16) on the tie-rod (12).
  2. Jet engine in accordance with Claim 1, characterized in that the tensioning arrangement (28) includes at least one tensioning element (33).
  3. Jet engine in accordance with Claim 2, characterized in that the tensioning element (33) is essentially annular and features a flange-type radially outward-extending attaching portion (34), an axial tubular center portion (35), and a radially inward-extending tensioning portion (36).
  4. Jet engine in accordance with Claim 3, characterized in that the radially outward-extending attaching portion (34) of the tensioning element (33) is attached to a portion of the rotor disk (9) provided with releasable rotor blades (5) and adjoining the blisks (6) on the downstream side.
  5. Jet engine in accordance with Claim 4, characterized in that the radially outward-extending attaching portion (34) of the tensioning element (33) is attached to a radially inner portion (10) of the rotor disk (9) provided with releasable rotor blades (5) and adjoining the blisks (6) on the downstream side.
  6. Jet engine in accordance with one of the Claims 2 to 4, characterized in that the tensioning element (33) can be retained by means of at least one tensioning means (37).
  7. Jet engine in accordance with Claim 6, characterized in that the tie-rod (12) is provided at its downstream end (14) with a step (15), whose outer diameter is smaller than the outer diameter of an upstream-adjoining portion (19) of the tie-rod (12), and that the radially inward-extending tensioning portion (36) of the tensioning element (33) radially embraces the step (15), with the radially inward-extending tensioning portion (36) of the tensioning element (33) being axially moveable relative to the step (15) and, in operation, remote from an axial limitation (17) of the step (15) and adjoining the tensioning means (37).
  8. Jet engine in accordance with Claim 6 or 7, characterized in that the tensioning means (37) is a tie-rod nut (37) which can be screwed on an external thread (18) adjoining the step (15) of the tie-rod (12).
  9. Jet engine with an apparatus (3) for retaining bladed rotor disks (4, 6, 9), with the jet engine essentially including an axial compressor with a rotor (1) which has several bladed rotor disks (4, 6, 9), at least one turbine section, at least one shaft and at least one tie-rod, with at least two bladed rotor disks at the compressor inlet side (2) being designed as blisks (6), each forming a one-piece assembly integrally combining a rotor disk with circumferentially distributed rotor blades (5),
    characterized in that
    the blisks (6) are releasably retained via a tie-rod (47) and in that the other rotor disks (4, 9) of the compressor rotor (1), the rotor blades (5) of which being releasably attached, are firmly connected to each other, separately and independently of the tie-rod (47), and in that the tie rod (47) is essentially tubular, disposed within central apertures (8) in the rotor disks designed as blisks (6) and firmly attached to a shaft driven by at least one turbine section, and in that the blisks (6) are retained by means of the tie rod (47) between at least one first arrangement (30) disposed upstream of the blisks and at least one second arrangement (41) disposed downstream of the blisks (6) and connected to the rotor disk (9) provided with releasable rotor blades (5), with the rotor disk (9) adjoining the blisks (6) on the downstream side, and in that the first arrangement, upstream of the blisks (6), includes a tensioning arrangement (30) with a tensioning means (37), and the second arrangement, downstream of the blisks (6), includes at least one bolted connection (41) between the tie-rod (47) and the rotor disk (9) provided with releasable rotor blades (5).
  10. Jet engine in accordance with Claim 9, characterized in that the upstream end (21) of the tie-rod (47) adjoins radially from the inside a tubular, upstream-extending protrusion (7) of the blisk (6) of the first stage, that the tensioning means (37) axially adjoins the protrusion (7) and radially a tie-rod ring (24) next to the upstream end of the tie-rod (47) and that the tie-rod (47) is, at its downstream end, provided with a flange (13) attaching to the rotor disk (9) provided with releasable rotor blades (5) and adjoining the blisks on the downstream side.
  11. Jet engine in accordance with Claim 10, characterized in that the tie-rod (47) is provided with a taper (20) in the direction of flow (40), and the flange (13) of the tie-rod (47) is attached to a radially outward-extending portion (11) of the rotor disk (9) provided with releasable rotor blades (5) and adjoining the blisks (6) on the downstream side.
  12. Jet engine in accordance with Claim 9, characterized in that the upstream end (21) of the tie-rod (47) is attached to a tie-rod ring (24), which is provided with an external thread (22), by means of at least one bolted connection (32), and that the tensioning means (37) is a tie-rod nut (37), which can be screwed on the external thread (22) of the tie-rod ring (24).
  13. Jet engine in accordance with Claim 10 or 12, characterized in that the tensioning means (37) simultaneously retains a radially inner bearing ring (26) of a tie-rod bearing (25).
  14. Jet engine in accordance with one of the Claims 1 to 13, characterized in that at least one vortex reducer (38) of the tubular type is attached to the rotor disk (9) provided with releasable rotor blades (5) and adjoining the blisks (6) on the downstream side.
  15. Method for the retention of bladed rotor disks (4, 6, 9) by means of a jet engine in accordance with one of the Claims 1 to 8 or 9 to 14, with the blisks (6) being releasably retained by means of the tie-rod (12, 47), and the rotor disks (4, 9) provided with releasable rotor blades (5) being firmly connected to each other, separately and independently of the tie-rod (12, 47).
  16. Method in accordance with Claim 15, characterized in that the blisks (6) are retained by means of the tie-rod (12, 47) between a first arrangement (27, 30) disposed upstream of the blisks (6) and a second arrangement (28, 32) disposed downstream of the blisks (6) and connected to the rotor disk (9) provided with releasable rotor blades (5), with the rotor disk (9) adjoining the blisks (6) on the downstream side.
  17. Method in accordance with Claim 16, characterized in that the tie-rod (47) is tensioned from the first arrangement (30) disposed upstream of the blisks (6).
  18. Method in accordance with Claim 16, characterized in that the tie-rod (12) is tensioned from the second arrangement (28) disposed downstream of the blisks (6).
EP08158102A 2007-07-06 2008-06-12 Method and device for clamping bladed rotor discs of a jet engine Ceased EP2011965B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102007031712A DE102007031712A1 (en) 2007-07-06 2007-07-06 Device and method for clamping bladed rotor disks of a jet engine

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EP2011965A2 EP2011965A2 (en) 2009-01-07
EP2011965A3 EP2011965A3 (en) 2011-05-11
EP2011965B1 true EP2011965B1 (en) 2012-08-08

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DE (1) DE102007031712A1 (en)

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US8152471B2 (en) 2012-04-10
EP2011965A2 (en) 2009-01-07
EP2011965A3 (en) 2011-05-11
US20090016886A1 (en) 2009-01-15
DE102007031712A1 (en) 2009-01-08

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