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EP1697618B1 - Stator vane carrier and plurality of stator vanes and method of mounting stator vanes to the stator vane carrier - Google Patents

Stator vane carrier and plurality of stator vanes and method of mounting stator vanes to the stator vane carrier Download PDF

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Publication number
EP1697618B1
EP1697618B1 EP04797660A EP04797660A EP1697618B1 EP 1697618 B1 EP1697618 B1 EP 1697618B1 EP 04797660 A EP04797660 A EP 04797660A EP 04797660 A EP04797660 A EP 04797660A EP 1697618 B1 EP1697618 B1 EP 1697618B1
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EP
European Patent Office
Prior art keywords
stator blade
stator
press
carrier
segment
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.)
Expired - Lifetime
Application number
EP04797660A
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German (de)
French (fr)
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EP1697618A1 (en
Inventor
Wilhelm Schulten
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Siemens AG
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Siemens AG
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Publication date
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Publication of EP1697618A1 publication Critical patent/EP1697618A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings

Definitions

  • the invention relates to an annular guide vane carrier with a plurality of guide vanes for a turbomachine for fastening the guide vanes according to
  • Gas turbines coupled to generators are used to convert fossil energy into electrical energy.
  • a gas turbine has along its rotor shaft in the flow direction of the gases to a compressor, a combustion chamber and a turbine unit.
  • the compressor draws in ambient air and compresses it.
  • the compressor air is mixed with a fuel and fed to the combustion chamber.
  • the mixture burns to a hot gaseous working medium and flows into the vaned turbine unit.
  • the vanes mounted on the housing of the turbine unit direct the working fluid onto the blades attached to the rotor so as to cause the rotor to rotate.
  • the thus recorded rotational energy of the rotor is converted by the generator coupled to the rotor into electrical energy. Furthermore, it is used to drive the compressor.
  • a compressor having a vane carrier as a housing for holding freestanding vanes.
  • a circumferential groove is provided with undercuts.
  • the housing is divided into two halves, so that when the housing is open, the guide vanes can be used for mounting in the divided circumferential groove and moved along it. Furthermore, it is described that intermediate pieces provided between the guide vanes are fixed by inserted documents.
  • the circumferential groove and the complementary Leitschaufelfborne the vanes are used with radial play in the circumferential groove.
  • the object of the invention is to provide a guide vane carrier with a plurality of guide vanes with reduced flow losses. Furthermore, it is the object of the invention to provide a method for mounting guide vanes on an annular guide vane carrier of a turbomachine thereto.
  • turbomachine task provides that aligned for each vane of the contact area and the support area in the radial direction of the rotor.
  • each vane or each Leitschaufelfuß is assigned at least one press segment.
  • a groove-shaped recess is provided in the groove bottom of the circumferential groove.
  • the pressing segments create a bias that presses the vane root against the undercuts of the circumferential groove so that the vane has a tight and secure fit with no play.
  • each press segment is supported in a support region in the recess and presses the guide blade foot unsprung against the undercut via a radially aligned contact region.
  • a resilient mounting of the guide vanes as for example from the aforementioned US 998,820 is known, is specifically avoided here.
  • all the press segments arranged in a recess adjoin one another in the circumferential direction to form a press segment ring, then all the press segments can be of identical construction and can be pushed one after the other one after the other for mounting. This reduces the manufacturing and assembly costs.
  • each pressing segment in the circumferential direction comprises at least two sections, wherein one of the sections in the radial direction has an excess to form the bias voltage.
  • the recess has an inner support region as an abutment on which the press segment is supported.
  • the oversize is slightly larger than the distance from the vane root to the inner support area.
  • Displacement in the circumferential direction of the assembled vanes is prevented when at least one securing element in the vane ring secures a vane against displacement in the circumferential direction.
  • platform elements are provided between two adjacent guide vanes of a guide vane ring.
  • the vane root can be made more compact and narrow, so that manufacturing processes such as forging or milling with little material use per blank are possible.
  • the platform element may additionally consist of a cheaper material, such as e.g. ST37, as the vane are made.
  • the turbomachine is a compressor.
  • the Fig. 5 shows a gas turbine 1 in a longitudinal partial section. It has inside a rotatably mounted about a rotational axis 2 rotor 3, which is also referred to as a turbine rotor or rotor shaft. Along the rotor 3 successively follow an intake 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of coaxially arranged burners 7, a turbine 8 and the exhaust housing. 9
  • annular compressor passage 10 is provided which extends in the direction of the annular combustion chamber 6 in cross section rejuvenated.
  • a diffuser 11 is arranged, which communicates with the annular combustion chamber 6 in flow communication.
  • the annular combustion chamber 6 forms a combustion chamber 12 for a mixture of a fuel and compressed air.
  • a hot gas duct 13 arranged in the turbine 8 is in flow communication with the combustion chamber 12, the exhaust gas casing 9 being arranged downstream of the hot gas duct 13.
  • blade rings are alternately arranged.
  • a stator blade ring 15 formed from guide vanes 14
  • a rotor blade ring 17 formed from rotor blades 16.
  • the stationary stator blades 14 are connected to a guide blade carrier 18, whereas the rotor blades 16 are connected to the rotor 3 by means of a disk 19.
  • the Fig. 1 shows a section through a vane support 18 and a freestanding vane 14.
  • the annular vane support 18 has on its the compressor passage 10 facing wall on an inner circumferential groove 21.
  • On the side walls 22 each formed by a projection 23 undercuts 24 are provided.
  • groove base 25 also two groove-shaped recesses 26 are arranged, the may also be formed as further circumferential grooves. The recesses 26 protrude into the guide blade carrier 18 with a radial depth which is greater than the width B of their opening in the groove base 25.
  • the vane 14 extends with its Leitschaufelfuß 27 in the circumferential groove 21 into it.
  • the guide blade root 27 is complementary to the undercuts 24 of the circumferential groove 21, ie T-shaped, formed so that the guide vane 14 is held in the circumferential groove 21.
  • a compressor channel 10 radially outwardly delimiting platform 29 is provided from which extends the freestanding airfoil profile 28 in the compressor passage 10 inside.
  • each press segments 30 are arranged, which presses the Leitschaufelfuß 27 with a bias to the projections 23 of the circumferential groove 21.
  • Fig. 2 shows the vane support 18 and the vane 14 according to section II-II of Fig. 1 , Between two adjacent vanes 14 of a vane ring 15, a platform member 32 is provided which limits the compressor duct 10 radially outward. In this case, the platform element 32 is hooked analogously to a guide blade foot 27 in the circumferential groove 21.
  • the pressing segment 30 abuts against the supporting wall 40 with a supporting region 31. Radially further inside, the pressing segment 30 points into a first section 34 (FIG. Figure 4 ) on its side facing the guide blade root 27, a contact region 33 which bears against the guide blade root 27 and presses against the projections 23; Supporting region 31 and contact region 33 lie on a radius for each guide blade (14, 16) and are aligned.
  • a second section 35 (FIG. Fig. 4 ) is a surface 36 which springs back relative to the contact region 33, the Platform element 32 facing. In the operating position, the surface 36 of the rear side of a side facing the guide blade 14 of the platform member 32 is contactless or with only comparatively low bias against.
  • Fig. 3 shows a cut through Fig. 1 according to the section plane III-III. Between two guide vanes 14, the platform element 32 is arranged.
  • the circumferential groove 21 extends in the circumferential direction U, wherein on the side walls 22, the undercuts 24 are shown.
  • groove base 25 are two recesses 26 with Abstütz alloyn 40.
  • left recess 26 is a press segment 30 is arranged, the surface 36 is shown.
  • the platform element 32 has, on an end face facing the guide blade 14, a recess 37 into which a tool with a lever can be inserted in order to push the guide blade 14 away from the contact region 33 in the direction of the surface 36 for disassembly.
  • every third platform element 32 can be fixed by a securing element 38, which is introduced into a further recess 39 of the downstream side of the guide vane 14.
  • the pressing segments 30 and securing elements 38 are located between the guide blade carrier 18 and the guide vanes 14 or the platform elements 32, so that they can not get into the compressor channel 10.
  • Fig. 4 shows the pressing segment 30 with the first portion 34 and the second portion 35.
  • the contact portion 33 is spaced from the opposite support portion 31 at a distance B 1 .
  • the surface 36 to the opposite rear side in another Distance B 2 spaced.
  • the distance B 1 is greater than the distance B 2 .
  • the curvature of the pressing segment 30 in the circumferential direction is not darg Nurse here.
  • the distance B 1 corresponds to a distance S ( Fig.1 ) measured between the support portion 31 and the vane root plus an oversize of about 0.3 mm.
  • the section 35 without oversize has a distance B 2 which can correspond approximately to the distance S.
  • a press segment 30 is first introduced into each groove-shaped recess 26. Either then the vane 14 can be introduced by radially in-moving into the circumferential groove 21 with subsequent rotation, so that the provided on the guide blade root 27 T-shaped projections engage behind the undercut 24. Or they are inserted into the circumferential groove 21, if this has a suitable opening, such as the parting line of the housing. Subsequently, the guide blade 14 is displaced in the direction of the free pressing segments 30 until the guide blade root 27 covers the surface 36 of the pressing segments 30 and abuts against the protruding contact region 33.
  • the guide blade 14 With a tool and with increased force, the guide blade 14 can now be pushed over the contact area 33 until the Leitschaufelfuß 27 completely covers the contact area 33. In this case, a part of the excess of the Leitschaufelfuß 27 is abraded. The prevailing in the press segment 30 bias then presses the Leitschaufelfuß 27 from the outside against the undercut 24 of the circumferential groove 21. Thus, a secure and predetermined position of the guide vane 14 is given.
  • a construction without platform elements 32 is also conceivable if the platforms 29 of the guide vanes 14 in the circumferential direction U are configured so wide that they fill the space bridged by the platform elements 32.
  • the pressing segments 30 remain unchanged.

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

Description

Die Erfindung betrifft einen ringförmigen Leitschaufelträger mit mehreren Leitschaufeln für eine Strömungsmaschine zum Befestigen der Leitschaufeln gemäßThe invention relates to an annular guide vane carrier with a plurality of guide vanes for a turbomachine for fastening the guide vanes according to

Anspruch 1 und ein Verfahren zum Montieren von Leitschaufeln an einem ringförmigen Leitschaufelträger einer Strömungsmaschine gemäß Anspruch 11.Claim 1 and a method for mounting vanes on an annular guide vane carrier of a turbomachine according to claim 11.

An Generatoren angekoppelte Gasturbinen werden zur Umwandlung von fossiler Energie in elektrische Energie eingesetzt. Eine Gasturbine weist dazu entlang ihrer Rotorwelle in Strömungsrichtung der Gase einen Verdichter, eine Brennkammer und eine Turbineneinheit auf. Beim Betrieb der Gasturbine saugt der Verdichter Umgebungsluft an und verdichtet diese. Anschlie-βend wird die Verdichterluft mit einem Brennmittel vermischt und der Brennkammer zugeführt. Dort verbrennt das Gemisch zu einem heißen gasförmigen Arbeitsmedium und strömt in die mit Schaufeln versehene Turbineneinheit ein. Die am Gehäuse der Turbineneinheit befestigten Leitschaufeln lenken das Arbeitsmedium auf die am Rotor befestigten Laufschaufeln, so dass diese den Rotor in eine Drehbewegung versetzen. Die so aufgenommene Rotationsenergie des Rotors wird durch den am Rotor angekoppelten Generator in elektrische Energie umgewandelt. Ferner wird sie zum Antrieb des Verdichters genutzt.Gas turbines coupled to generators are used to convert fossil energy into electrical energy. A gas turbine has along its rotor shaft in the flow direction of the gases to a compressor, a combustion chamber and a turbine unit. During operation of the gas turbine, the compressor draws in ambient air and compresses it. Subsequently, the compressor air is mixed with a fuel and fed to the combustion chamber. There, the mixture burns to a hot gaseous working medium and flows into the vaned turbine unit. The vanes mounted on the housing of the turbine unit direct the working fluid onto the blades attached to the rotor so as to cause the rotor to rotate. The thus recorded rotational energy of the rotor is converted by the generator coupled to the rotor into electrical energy. Furthermore, it is used to drive the compressor.

Hierzu ist eine Befestigung von Turbinenschaufeln aus der US 998,820 bekannt. Dabei drückt eine entlang des Umfangs einer ringförmigen Leitschaufelhaltenut sich erstreckende, leicht wellenförmige Blattfeder Leitschaufelfüße gegen die Hinterschneidungen der Leitschaufelhaltenut. Die Leitschaufeln der Turbine sind federgelagert und können somit den radialen Bewegungen des Rotors folgen. Die wellige Blattfeder nimmt entweder die auf die Leitschaufeln wirkenden Kräfte durch die radiale Rotorbewegung auf oder führt gegebenenfalls die Leitschaufeln in Radialrichtung nach.For this purpose, a fastening of turbine blades from the US 998,820 known. At this time, a slightly wavy leaf spring, which extends along the circumference of an annular vane holding groove, presses vane feet against the undercuts of the vane holding groove. The Guide vanes of the turbine are spring-loaded and can thus follow the radial movements of the rotor. The wavy leaf spring either absorbs the forces acting on the guide vanes by the radial rotor movement or, if appropriate, leads the guide vanes in the radial direction.

Aus der DE 44 36 731 ist ein Verdichter mit einem als Gehäuse ausgeführten Leitschaufelträger zum Halten von freistehenden Leitschaufeln bekannt. An der Innenseite des Leitschaufelträgers ist eine Umfangsnut mit Hinterschneidungen vorgesehen. Das Gehäuse ist in zwei Hälften unterteilt, so dass bei offenem Gehäuse die Leitschaufeln zur Montage in die aufgeteilte Umfangsnut eingesetzt und entlang dieser verschoben werden können. Ferner ist beschrieben, dass zwischen den Leitschaufeln vorgesehene Zwischenstücke durch eingelegte Unterlagen fixiert werden.From the DE 44 36 731 For example, a compressor is known having a vane carrier as a housing for holding freestanding vanes. On the inside of the guide vane carrier a circumferential groove is provided with undercuts. The housing is divided into two halves, so that when the housing is open, the guide vanes can be used for mounting in the divided circumferential groove and moved along it. Furthermore, it is described that intermediate pieces provided between the guide vanes are fixed by inserted documents.

Die Umfangsnut und die dazu komplementär ausgebildeten Leitschaufelfüße der Leitschaufeln sind dabei mit radialem Spiel in der Umfangsnut eingesetzt.The circumferential groove and the complementary Leitschaufelfüße the vanes are used with radial play in the circumferential groove.

Das radiale Spiel der freistehenden Leitschaufeln kann jedoch zu Strömungsverlusten in der zu komprimierenden Luft führen.However, the radial clearance of the free-standing vanes can lead to flow losses in the air to be compressed.

Die Aufgabe der Erfindung ist es, einen Leitschaufelträger mit mehreren Leitschaufeln mit verminderten Strömungsverlusten anzugeben. Ferner ist es die Aufgabe der Erfindung, ein Verfahren zum Montieren von Leitschaufeln an einem ringförmigen Leitschaufelträger einer Strömungsmaschine dazu anzugeben.The object of the invention is to provide a guide vane carrier with a plurality of guide vanes with reduced flow losses. Furthermore, it is the object of the invention to provide a method for mounting guide vanes on an annular guide vane carrier of a turbomachine thereto.

Die Lösung der auf die nach dem Oberbegriff des Anspruch 1 ausgebildete Strömungsmaschine gerichtete Aufgabe sieht vor, dass für jede Leitschaufel der Kontaktbereich und der Abstützbereich in Radialrichtung des Rotors gesehen fluchten.The solution to the problem addressed to the trained according to the preamble of claim 1 turbomachine task provides that aligned for each vane of the contact area and the support area in the radial direction of the rotor.

Die Erfindung geht dabei von der Erkenntnis aus, dass jeder Leitschaufel bzw. jedem Leitschaufelfuß zumindest ein Press-segment zugeordnet ist. Zur Aufnahme eines Presssegments ist im Nutgrund der Umfangsnut eine nutförmige Ausnehmung vorgesehen. Im montierten Zustand erzeugen die Presssegmente eine Vorspannung, die den Leitschaufelfuß an die Hinterschneidungen der Umfangsnut presst, so dass die Leitschaufel einen festen und sicheren Sitz ohne Spiel aufweist. Hierzu stützt sich jedes Presssegment in einem Abstützbereich in der Ausnehmung ab und drückt über einen dazu radial fluchtenden Kontaktbereich den Leitschaufelfuß ungefedert an die Hinterschneidung. Eine federnde Halterung der Leitschaufeln, so wie sie beispielsweise aus vorgenannten der US 998,820 bekannt ist, wird hier gezielt vermieden.The invention is based on the recognition that each vane or each Leitschaufelfuß is assigned at least one press segment. For receiving a press segment, a groove-shaped recess is provided in the groove bottom of the circumferential groove. When assembled, the pressing segments create a bias that presses the vane root against the undercuts of the circumferential groove so that the vane has a tight and secure fit with no play. For this purpose, each press segment is supported in a support region in the recess and presses the guide blade foot unsprung against the undercut via a radially aligned contact region. A resilient mounting of the guide vanes, as for example from the aforementioned US 998,820 is known, is specifically avoided here.

Ferner wird durch die Presssegmente erreicht, dass keine kostenintensive manuelle Anpassarbeit bei der Montage der Leitschaufeln nötig ist. Vergleichsweise große Toleranzen der Umfangsnut und der Leitschaufelfüße sind dabei kostenmindernd möglich.Furthermore, it is achieved by the pressing segments that no costly manual fitting work in the assembly of the guide vanes is necessary. Comparatively large tolerances of the circumferential groove and the Leitschaufelfüße are cost-reducing possible.

Besonders vorteilhaft ist die Weiterbildung, bei der im Nutgrund zwei nutförmige Ausnehmungen vorgesehen sind, in denen sich jeweils Presssegmente befinden. Somit wird eine Leitschaufel bzw. ein Leitschaufelfuß von einem Paar Presssegmenten an die Hinterschneidungen der Umfangsnut gepresst. Mit nur einem Presssegment könnte der Leitschaufelfuß um den Kontaktbereich, an der das Presssegment am Leitschaufelfuß anliegt, axial kippen, oder den Leitschaufelfuß ungleichmäßig an die beiden Hinterschneidungen anpressen.Particularly advantageous is the development in which two groove-shaped recesses are provided in the groove base, in each of which pressing segments are located. Thus, a vane or a Leitschaufelfuß is pressed by a pair of pressing segments to the undercuts of the circumferential groove. With only one pressing segment of the Leitschaufelfuß could tilt about the contact area at which the pressing segment abuts the Leitschaufelfuß, axially, or press the Leitschaufelfuß unevenly to the two undercuts.

Wenn die in einer Ausnehmung angeordneten Presssegmente in Umfangsrichtung aneinanderliegend einen Presssegmentring bilden, so können alle Presssegmente gleich ausgebildet sein und zur Montage einfach nacheinander aneinander geschoben werden. Die reduziert die Herstellungs- und die Montagekosten.If the pressing segments arranged in a recess adjoin one another in the circumferential direction to form a press segment ring, then all the press segments can be of identical construction and can be pushed one after the other one after the other for mounting. This reduces the manufacturing and assembly costs.

Eine einfache Montage einer Leitschaufel lässt sich erzielen, wenn jedes Presssegment in Umfangsrichtung zumindest zwei Abschnitte umfasst, wobei einer der Abschnitte in Radialrichtung ein Übermaß zur Bildung der Vorspannung aufweist. Bei der Montage wird der Leitschaufelfuß über ein bereits in der Ausnehmung vorgesehenes Presssegment in eine Betriebslage verschoben. Da die Leitschaufel oder deren Plattform in Umfangsrichtung breiter sein kann als der Leitschaufelfuß, ist es sinnvoll, das Übermaß nur in dem Abschnitt des Presssegments vorzusehen, der in der Betriebslage den Leitschaufelfuß kontaktiert. Da die anderen Abschnitte nur während des Verschiebevorgangs mit dem Leitschaufelfuß in Berührung kommen, würde ein hier vorgesehenes Übermaß den anfänglichen Verschiebevorgang hindern. Weiterhin dienen der oder die restlichen Abschnitte des Presssegments in Umfangsrichtung als Anschlagsfläche für nachfolgend eingebaute Presssegmente, die sich dann in richtiger Betriebslage befinden. Zweckmäßigerweise weist die Ausnehmung einen innere Abstützbereich als Gegenlager auf, an dem das Presssegment sich abstützt. Das Übermaß ist geringfügig größer als der Abstand vom Leitschaufelfuß zur inneren Abstützbereich.A simple assembly of a guide vane can be achieved if each pressing segment in the circumferential direction comprises at least two sections, wherein one of the sections in the radial direction has an excess to form the bias voltage. When mounting the Leitschaufelfuß is moved over an already provided in the recess pressing segment in an operating position. Since the vane or its platform can be wider in the circumferential direction than the vane root, it makes sense to provide the excess only in the portion of the press segment, which contacts the Leitschaufelfuß in the operating position. Since the other portions come into contact with the vane root only during the shifting operation, an oversized amount would prevent the initial shifting operation. Furthermore serve or the remaining portions of the press segment in the circumferential direction as a stop surface for subsequently installed press segments, which are then in the correct operating position. Conveniently, the recess has an inner support region as an abutment on which the press segment is supported. The oversize is slightly larger than the distance from the vane root to the inner support area.

Eine Verschiebung in Umfangsrichtung der montierten Leitschaufeln wird verhindert, wenn im Leitschaufelring zumindest ein Sicherungselement eine Leitschaufel gegen eine Verschiebung in Umfangsrichtung sichert.Displacement in the circumferential direction of the assembled vanes is prevented when at least one securing element in the vane ring secures a vane against displacement in the circumferential direction.

In einer vorteilhaften Weiterbildung sind zwischen zwei benachbarten Leitschaufeln eines Leitschaufelrings Plattformelemente vorgesehen. Der Leitschaufelfuß kann kompakter und schmaler gestaltet werden, so dass Herstellungsverfahren wie Schmieden oder Fräsen mit wenig Materialeinsatz pro Rohteil möglich sind. Das Plattformelement kann dabei zusätzlich aus einem preiswerteren Material, wie z.B. ST37, als die Leitschaufel gefertigt werden.In an advantageous development, platform elements are provided between two adjacent guide vanes of a guide vane ring. The vane root can be made more compact and narrow, so that manufacturing processes such as forging or milling with little material use per blank are possible. The platform element may additionally consist of a cheaper material, such as e.g. ST37, as the vane are made.

Zur Demontage der Leitschaufeln ist es sinnvoll, eine Aussparung an den Plattformelementen und oder an den Leitschaufelfüßen vorzusehen. Mittels eines Werkzeuges kann dann der Leitschaufelfuß gegenüber dem Presssegment verschoben werden, bis beide gelöst sind.For disassembly of the vanes, it makes sense, a recess to provide on the platform elements and or on the Leitschaufelfüßen. By means of a tool then the Leitschaufelfuß can be moved relative to the pressing segment until both are solved.

Vorzugsweise ist die Strömungsmaschine ein Verdichter.Preferably, the turbomachine is a compressor.

Die auf das Verfahren gerichtete Aufgabe wird durch die Merkmale des Anspruchs 11 gelöst.The object directed to the method is solved by the features of claim 11.

Die Erfindung wird anhand einer Zeichnung erläutert. Dabei zeigen:

Fig. 1
einen Schnitt durch einen Leitschaufelträger mit einer Leitschaufel,
Fig. 2
einen Schnitt durch einen Leitschaufelträger gemäß II-II,
Fig. 3
einen Schnitt durch einen Leitschaufelträger gemäß Schnitt III-III,
Fig. 4
ein Presssegment und
Fig. 5
einen Längsteilschnitt durch eine Gasturbine.
The invention will be explained with reference to a drawing. Showing:
Fig. 1
a section through a vane carrier with a vane,
Fig. 2
a section through a vane support according to II-II,
Fig. 3
a section through a vane carrier according to section III-III,
Fig. 4
a press segment and
Fig. 5
a longitudinal section through a gas turbine.

Die Fig. 5 zeigt eine Gasturbine 1 in einem Längsteilschnitt. Sie weist im Inneren einen um eine Drehachse 2 drehgelagerten Rotor 3 auf, der auch als Turbinenläufer oder Rotorwelle bezeichnet wird. Entlang des Rotors 3 folgen aufeinander ein Ansauggehäuse 4, ein Verdichter 5, eine torusartige Ringbrennkammer 6 mit mehreren koaxial angeordneten Brennern 7, eine Turbine 8 und das Abgasgehäuse 9.The Fig. 5 shows a gas turbine 1 in a longitudinal partial section. It has inside a rotatably mounted about a rotational axis 2 rotor 3, which is also referred to as a turbine rotor or rotor shaft. Along the rotor 3 successively follow an intake 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of coaxially arranged burners 7, a turbine 8 and the exhaust housing. 9

Im Verdichter 5 ist ein ringförmiger Verdichterkanal 10 vorgesehen, der sich in Richtung der Ringbrennkammer 6 im Querschnitt verjüngt. Am brennkammerseitigen Ausgang des Verdichters 5 ist ein Diffusor 11 angeordnet, der mit der Ringbrennkammer 6 in Strömungsverbindung steht. Die Ringbrennkammer 6 bildet einen Verbrennungsraum 12 für ein Gemisch aus einem Brennmittel und verdichteter Luft. Ein in der Turbine 8 angeordneter Heißgaskanal 13 ist mit dem Verbrennungsraum 12 in Strömungsverbindung, wobei dem Heißgaskanal 13 das Abgasgehäuse 9 nachgeordnet ist.In the compressor 5, an annular compressor passage 10 is provided which extends in the direction of the annular combustion chamber 6 in cross section rejuvenated. At the combustion chamber side output of the compressor 5, a diffuser 11 is arranged, which communicates with the annular combustion chamber 6 in flow communication. The annular combustion chamber 6 forms a combustion chamber 12 for a mixture of a fuel and compressed air. A hot gas duct 13 arranged in the turbine 8 is in flow communication with the combustion chamber 12, the exhaust gas casing 9 being arranged downstream of the hot gas duct 13.

Im Verdichterkanal 10 und im Heißgaskanal 13 sind jeweils alternierend Schaufelringe angeordnet. Es folgt einem aus Leitschaufeln 14 gebildeten Leitschaufelring 15 jeweils ein aus Laufschaufeln 16 gebildeter Laufschaufelring 17. Die feststehenden Leitschaufeln 14 sind dabei mit einem Leitschaufelträger 18 verbunden, wo hingegen die Laufschaufeln 16 am Rotor 3 mittels einer Scheibe 19 verbunden sind.In the compressor duct 10 and the hot gas duct 13, blade rings are alternately arranged. The following is followed by a stator blade ring 15 formed from guide vanes 14, a rotor blade ring 17 formed from rotor blades 16. The stationary stator blades 14 are connected to a guide blade carrier 18, whereas the rotor blades 16 are connected to the rotor 3 by means of a disk 19.

Während des Betriebes der Gasturbine 1 wird vom Verdichter 5 durch das Ansauggehäuse 4 Luft angesaugt und im Verdichterkanal 10 verdichtet. Eine am brennerseitigen Ende des Verdichters 5 bereitgestellt Luft L wird durch den Diffusor 11 zu den Brennern 7 geführt und dort mit einem Brennmittel vermischt. Das Gemisch wird dann unter Bildung eines Arbeitsfluids 20 im Verbrennungsraum 12 verbrannt. Von dort aus strömt das Arbeitsfluid 20 in den Heißgaskanal 13. An den in der Turbine 8 angeordneten Leitschaufeln 14 und an den Laufschaufeln 16 entspannt sich das Arbeitsfluid 20 impulsübertragend, so dass der Rotor 3 angetrieben wird und mit ihm eine an ihm angekoppelte Arbeitsmaschine (nicht dargestellt).During operation of the gas turbine 1 4 air is sucked in by the compressor 5 through the intake and compressed in the compressor passage 10. A provided at the burner-side end of the compressor 5 air L is passed through the diffuser 11 to the burners 7 and mixed there with a fuel. The mixture is then burned to form a working fluid 20 in the combustion chamber 12. From there, the working fluid 20 flows into the hot gas duct 13. At the turbine blades 8 arranged in the guide vanes 14 and the blades 16, the working fluid 20 relaxes momentum, so that the rotor 3 is driven and with him a coupled to him machine (not shown).

Die Fig. 1 zeigt einen Schnitt durch einen Leitschaufelträger 18 und eine freistehende Leitschaufel 14. Der ringförmige Leitschaufelträger 18 weist an seiner dem Verdichterkanal 10 zugewandten Wand eine innere Umfangsnut 21 auf. An dessen Seitenwänden 22 sind jeweils durch einen Vorsprung 23 gebildete Hinterschneidungen 24 vorgesehen. Im Nutgrund 25 sind ferner zwei nutenförmige Ausnehmungen 26 angeordnet, die ebenfalls als weitere Umfangsnuten ausgebildet sein können. Die Ausnehmungen 26 ragen dabei mit einer radialen Tiefe in den Leitschaufelträger 18 hinein, die größer ist als die Breite B ihrer Öffnung im Nutgrund 25.The Fig. 1 shows a section through a vane support 18 and a freestanding vane 14. The annular vane support 18 has on its the compressor passage 10 facing wall on an inner circumferential groove 21. On the side walls 22 each formed by a projection 23 undercuts 24 are provided. In groove base 25 also two groove-shaped recesses 26 are arranged, the may also be formed as further circumferential grooves. The recesses 26 protrude into the guide blade carrier 18 with a radial depth which is greater than the width B of their opening in the groove base 25.

Die Leitschaufel 14 erstreckt sich mit ihrem Leitschaufelfuß 27 in die Umfangsnut 21 hinein. Dabei ist der Leitschaufelfuß 27 komplementär zu den Hinterschneidungen 24 der Umfangsnut 21, also T-förmig, ausgebildet, so dass die Leitschaufel 14 in der Umfangsnut 21 gehalten wird. Am Leitschaufelfuß 27 ist eine den Verdichterkanal 10 radial nach außen begrenzende Plattform 29 vorgesehen, von der aus sich das freistehende Schaufelblattprofil 28 in den Verdichterkanal 10 hinein erstreckt.The vane 14 extends with its Leitschaufelfuß 27 in the circumferential groove 21 into it. In this case, the guide blade root 27 is complementary to the undercuts 24 of the circumferential groove 21, ie T-shaped, formed so that the guide vane 14 is held in the circumferential groove 21. On the guide blade root 27, a compressor channel 10 radially outwardly delimiting platform 29 is provided from which extends the freestanding airfoil profile 28 in the compressor passage 10 inside.

In den Ausnehmungen 26 sind jeweils Presssegmente 30 angeordnet, die den Leitschaufelfuß 27 mit einer Vorspannung an die Vorsprünge 23 der Umfangsnut 21 presst.In the recesses 26 each press segments 30 are arranged, which presses the Leitschaufelfuß 27 with a bias to the projections 23 of the circumferential groove 21.

Fig. 2 zeigt den Leitschaufelträger 18 und die Leitschaufel 14 gemäß dem Schnitt II-II der Fig. 1. Zwischen zwei benachbarten Leitschaufeln 14 eines Leitschaufelrings 15 ist ein Plattformelement 32 vorgesehen, welches den Verdichterkanal 10 radial nach außen begrenzt. Dabei ist das Plattformelement 32 analog eines Leitschaufelfußes 27 in der Umfangsnut 21 verhakt. Fig. 2 shows the vane support 18 and the vane 14 according to section II-II of Fig. 1 , Between two adjacent vanes 14 of a vane ring 15, a platform member 32 is provided which limits the compressor duct 10 radially outward. In this case, the platform element 32 is hooked analogously to a guide blade foot 27 in the circumferential groove 21.

Radial von außen nach innen betrachtet liegt das Presssegment 30 mit einem Abstützbereich 31 an der Abstützwand 40 an. Radial weiter innen weist das Presssegment 30 in einen ersten Abschnitt 34 (Fig.4) an seiner dem Leitschaufelfuß 27 zugewandten Seite einen Kontaktbereich 33 auf, die am Leitschaufelfuß 27 anliegt und diesen gegen die Vorsprünge 23 presst; Abstützbereich 31 und Kontaktbereich 33 liegen für jede Leitschaufel (14, 16) auf einem Radius und fluchten. In einem zweiten Abschnitt 35 (Fig. 4) ist eine Fläche 36, die gegenüber dem Kontaktbereich 33 zurückspringt, dem Plattformelement 32 zugewandt. In der Betriebslage liegt die Fläche 36 der Rückseite eines zur Leitschaufel 14 benachbarten des Plattformelements 32 berührungslos oder mit nur vergleichsweise geringer Vorspannung gegenüber.Viewed radially from outside to inside, the pressing segment 30 abuts against the supporting wall 40 with a supporting region 31. Radially further inside, the pressing segment 30 points into a first section 34 (FIG. Figure 4 ) on its side facing the guide blade root 27, a contact region 33 which bears against the guide blade root 27 and presses against the projections 23; Supporting region 31 and contact region 33 lie on a radius for each guide blade (14, 16) and are aligned. In a second section 35 (FIG. Fig. 4 ) is a surface 36 which springs back relative to the contact region 33, the Platform element 32 facing. In the operating position, the surface 36 of the rear side of a side facing the guide blade 14 of the platform member 32 is contactless or with only comparatively low bias against.

Fig. 3 zeigt einen Schnitt durch Fig. 1 gemäß der Schnittebene III-III. Zwischen zwei Leitschaufeln 14 ist das Plattformelement 32 angeordnet. Die Umfangsnut 21 verläuft dabei in Umfangsrichtung U, wobei an deren Seitenwänden 22 die Hinterschneidungen 24 gezeigt sind. Im Nutgrund 25 befinden sich zwei Ausnehmungen 26 mit Abstützwänden 40. In der in Fig. 3 links dargestellten Ausnehmung 26 ist ein Presssegment 30 angeordnet, dessen Fläche 36 gezeigt ist. Das Plattformelement 32 weist an einer der Leitschaufel 14 zugewandten Stirnseite eine Aussparung 37 auf, in welches ein Werkzeug mit einem Hebel einbringbar ist, um die Leitschaufel 14 zur Demontage von dem Kontaktbereich 33 in Richtung der Fläche 36 zu schieben und sie somit zu lösen. Fig. 3 shows a cut through Fig. 1 according to the section plane III-III. Between two guide vanes 14, the platform element 32 is arranged. The circumferential groove 21 extends in the circumferential direction U, wherein on the side walls 22, the undercuts 24 are shown. In groove base 25 are two recesses 26 with Abstützwänden 40. In the in Fig. 3 left recess 26 is a press segment 30 is arranged, the surface 36 is shown. The platform element 32 has, on an end face facing the guide blade 14, a recess 37 into which a tool with a lever can be inserted in order to push the guide blade 14 away from the contact region 33 in the direction of the surface 36 for disassembly.

Damit die Leitschaufeln 14 und die Plattformelemente 32 sich aufgrund von Toleranzen und instationären Wärmedehnungen in Umfangsrichtung U nicht verschieben, kann beispielsweise jedes dritte Plattformelement 32 durch ein Sicherungselement 38, welches in eine weitere Aussparung 39 der strömungsabgewandten Seite der Leitschaufel 14 eingebracht ist, fixiert werden.So that the guide vanes 14 and the platform elements 32 do not shift due to tolerances and transient thermal expansions in the circumferential direction U, for example, every third platform element 32 can be fixed by a securing element 38, which is introduced into a further recess 39 of the downstream side of the guide vane 14.

Die Presssegmente 30 und Sicherungselemente 38 befinden sich zwischen Leitschaufelträger 18 und den Leitschaufeln 14 bzw. den Plattformelementen 32, so dass sie nicht in den Verdichterkanal 10 hineingelangen können.The pressing segments 30 and securing elements 38 are located between the guide blade carrier 18 and the guide vanes 14 or the platform elements 32, so that they can not get into the compressor channel 10.

Fig. 4 zeigt das Presssegment 30 mit dem ersten Abschnitt 34 und dem zweiten Abschnitt 35. Im ersten Abschnitt 34 ist der Kontaktbereich 33 zum gegenüberliegenden Abstützbereich 31 in einem Abstand B1 beabstandet. Im zweiten Abschnitt 35 ist die Fläche 36 zur gegenüberliegenden Rückseite in einem weiteren Abstand B2 beabstandet. Der Abstand B1 ist größer als der Abstand B2. Die Krümmung des Presssegmentes 30 in Umfangsrichtung ist hierbei nicht dargstellt. Fig. 4 shows the pressing segment 30 with the first portion 34 and the second portion 35. In the first portion 34, the contact portion 33 is spaced from the opposite support portion 31 at a distance B 1 . In the second section 35, the surface 36 to the opposite rear side in another Distance B 2 spaced. The distance B 1 is greater than the distance B 2 . The curvature of the pressing segment 30 in the circumferential direction is not dargstellt here.

Der Abstand B1 entspricht einem Abstand S (Fig.1), der zwischen dem Abstützbereich 31 und dem Leitschaufelfuß gemessen wird, zuzüglich eines Übermaßes von ca. 0,3 mm. Der Abschnitt 35 ohne Übermaß weist dagegen einen Abstand B2 auf, der annähernd dem Abstand S entsprechen kann.The distance B 1 corresponds to a distance S ( Fig.1 ) measured between the support portion 31 and the vane root plus an oversize of about 0.3 mm. By contrast, the section 35 without oversize has a distance B 2 which can correspond approximately to the distance S.

Weil der Abstand B2 um ca. 0,3 mm größer ist als der Abstand S, wirkt in der Betriebslage eine durch das Presssegment 30 erzeugte Vorspannung auf den Leitschaufelfuß 27, der diesen an die Hinterschneidung 24 ungefedert presst und sicher fixiert.Because the distance B 2 is greater than the distance S by approximately 0.3 mm, in the operating position, a preload generated by the press segment 30 acts on the guide blade root 27, which presses it against the undercut 24 unsprung and securely fixes it.

Zur Montage einer Leitschaufel 14 an dem Leitschaufelträger 18 wird zuerst in jede nutförmige Ausnehmung 26 jeweils ein Presssegment 30 eingebracht. Entweder kann dann die Leitschaufel 14 durch radiales Hineinbewegen in die Umfangsnut 21 mit anschließendem Verdrehen eingebracht werden, so dass die am Leitschaufelfuß 27 vorgesehenen T-förmigen Vorsprünge die Hinterschneidung 24 hintergreifen. Oder sie werden in die Umfangsnut 21 eingeschoben, wenn diese eine dafür geeignete Öffnung aufweist, wie z.B. die Teilfuge des Gehäuses. Anschließend wird die Leitschaufel 14 in Richtung der freien Presssegmente 30 verschoben, bis der Leitschaufelfuß 27 die Fläche 36 der Presssegmente 30 überdeckt und an den hervorstehenden Kontaktbereich 33 anstößt. Mit einem Werkzeug und mit erhöhtem Kraftaufwand kann nun die Leitschaufel 14 über den Kontaktbereich 33 geschoben werden, bis der Leitschaufelfuß 27 den Kontaktbereich 33 vollständig überdeckt. Dabei wird ein Teil des Übermaßes vom Leitschaufelfuß 27 abgerieben. Die im Presssegment 30 herrschende Vorspannung presst dann den Leitschaufelfuß 27 von außen gegen die Hinterschneidung 24 der Umfangsnut 21. Somit ist eine sichere und vorbestimmte Lage der Leitschaufel 14 gegeben.For mounting a guide blade 14 on the guide blade carrier 18, a press segment 30 is first introduced into each groove-shaped recess 26. Either then the vane 14 can be introduced by radially in-moving into the circumferential groove 21 with subsequent rotation, so that the provided on the guide blade root 27 T-shaped projections engage behind the undercut 24. Or they are inserted into the circumferential groove 21, if this has a suitable opening, such as the parting line of the housing. Subsequently, the guide blade 14 is displaced in the direction of the free pressing segments 30 until the guide blade root 27 covers the surface 36 of the pressing segments 30 and abuts against the protruding contact region 33. With a tool and with increased force, the guide blade 14 can now be pushed over the contact area 33 until the Leitschaufelfuß 27 completely covers the contact area 33. In this case, a part of the excess of the Leitschaufelfuß 27 is abraded. The prevailing in the press segment 30 bias then presses the Leitschaufelfuß 27 from the outside against the undercut 24 of the circumferential groove 21. Thus, a secure and predetermined position of the guide vane 14 is given.

Eine Konstruktion ohne Plattformelemente 32 ist auch denkbar, wenn die Plattformen 29 der Leitschaufeln 14 in Umfangsrichtung U so breit ausgestaltet werden, dass sie den von den Plattformelementen 32 überbrückten Raum ausfüllen. Die Presssegmente 30 bleiben dabei unverändert.A construction without platform elements 32 is also conceivable if the platforms 29 of the guide vanes 14 in the circumferential direction U are configured so wide that they fill the space bridged by the platform elements 32. The pressing segments 30 remain unchanged.

Durch die Presssegmente 30 wird erreicht, dass keine kostenintensive manuelle Anpassarbeit bei der Montage der Leitschaufeln 14 nötig ist. Ferner ist die Umfangsnut 21 und sind die Leitschaufelfüße 27 mit vergleichsweise großen Toleranzen herstellbar. Die Plattformelemente 32 als auch die Presssegmente 30 können aus dem kostengünstigen Material ST37 gefertigt sein.By pressing segments 30 is achieved that no costly manual fitting work in the assembly of the guide vanes 14 is necessary. Furthermore, the circumferential groove 21 and the guide blade feet 27 can be produced with comparatively large tolerances. The platform elements 32 as well as the pressing segments 30 can be made of the inexpensive material ST37.

Die Anwendung der Erfindung auf Dampfturbinen zum Befestigen von Dampfturbinenleitschaufeln wäre auch denkbar.The application of the invention to steam turbines for mounting steam turbine guide vanes would also be conceivable.

Claims (11)

  1. Annular stator blade carrier (18) for the fastening of stator blades (14, 16) for a turbomachine,
    having a plurality of radially extending stator blades (14, 16) with equal angular spacing with regard to a rotor (3) and with stator blade roots (27) disposed on the outside, which stator blades (14, 16) form a stator blade ring (15),
    on which carrier the stator blade roots (27) are retained in an inner circumferential groove (21) by undercuts (24) behind which the stator blade roots (27) can fit, and with at least one groove-like recess (26) which extends in the groove base (25) of the circumferential groove (21) along its circumference, and with at least one annular press segment (30) which is arranged therein and presses against the stator blade roots (27) under pretension (23),
    wherein the press segment, as seen radially on the outside, is supported in the groove-like recess (26) in a support region (31) and, as seen radially on the inside, butts against the stator blade root (17), forming a contact region,
    characterized in that
    the press segment (30) supports the stator blade (14, 16) in an unsprung manner and
    in that for each stator blade (14, 16) the contact region and the support region (31) are in alignment, as seen in the radial direction of the rotor (3).
  2. Stator blade carrier (18) according to Claim 1,
    characterized in that
    provision is made in the groove base (25) for two groove-like recesses (26), in which press segments (30) are located in each case.
  3. Stator blade carrier (18) according to Claim 1 or 2,
    characterized in that
    the press segments of a recess (26), abutting in the circumferential direction (U), form a press-segment ring.
  4. Stator blade carrier (18) according to one of the preceding claims,
    characterized in that
    each press segment (30) comprises at least two sections in the circumferential direction (U), wherein at least one of the sections has an oversize in the radial direction for forming the pretension (23).
  5. Stator blade carrier (18) according to Claim 4,
    characterized in that
    the section provided with the oversize has a width (B1) which is larger than the distance from the stator blade root (27) to the inner support region (31).
  6. Stator blade carrier (18) according to one of the preceding claims,
    characterized in that
    the stator blade ring (15) is locked against displacement in the circumferential direction (U) by at least one locking element (38).
  7. Stator blade carrier (18) according to one of the preceding claims,
    characterized in that
    platform elements (32) are provided between two adjacent stator blades (14, 16) of a stator blade ring (15) in each case.
  8. Stator blade carrier (18) according to one of the preceding claims,
    characterized in that
    the stator blade roots (27) and/or the platform elements (32) have a cutout (37) for moving them away.
  9. Turbomachine,
    characterized in that this is equipped with an annular stator blade carrier (18) according to one of Claims 1 to 8.
  10. Turbomachine according to Claim 9,
    characterized in that it is designed as a compressor (5).
  11. Method for installing stator blades (14, 16) in a device according to one of, or to a plurality of, Claims 1 to 9, characterized in that
    for installing each stator blade (14, 16) on the stator blade carrier (18) the following working steps are carried out:
    a) a press segment (30) is introduced into a recess (26) so that its section provided with the oversize faces an already installed stator blade (14, 16),
    b) the press segment is then slid towards the installed stator blade (14, 16) until it butts against the press segment of the adjacent stator blade (14, 16),
    c) a stator blade (14, 16) is then introduced into the circumferential groove (21) and slid in the direction of the press segment (30) until its stator blade root (27) butts against the section provided with the oversize,
    d) by force action, the stator blade root (27) is slid over the section provided with the oversize until the stator blade root (27) butts against the already installed stator blade (14, 16) so that it is pressed in an unsprung manner onto the undercut (24, under a pretension (23) which is created by the press segment (30).
EP04797660A 2003-12-23 2004-11-05 Stator vane carrier and plurality of stator vanes and method of mounting stator vanes to the stator vane carrier Expired - Lifetime EP1697618B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04797660A EP1697618B1 (en) 2003-12-23 2004-11-05 Stator vane carrier and plurality of stator vanes and method of mounting stator vanes to the stator vane carrier

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP03029771A EP1548232A1 (en) 2003-12-23 2003-12-23 Turbomachine comprising a stator vane support and method of mounting stator vanes to the stator vane support
PCT/EP2004/012553 WO2005066463A1 (en) 2003-12-23 2004-11-05 Turbo machine with a vane support and method for mounting vanes on a vane support
EP04797660A EP1697618B1 (en) 2003-12-23 2004-11-05 Stator vane carrier and plurality of stator vanes and method of mounting stator vanes to the stator vane carrier

Publications (2)

Publication Number Publication Date
EP1697618A1 EP1697618A1 (en) 2006-09-06
EP1697618B1 true EP1697618B1 (en) 2012-12-26

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Family Applications (2)

Application Number Title Priority Date Filing Date
EP03029771A Withdrawn EP1548232A1 (en) 2003-12-23 2003-12-23 Turbomachine comprising a stator vane support and method of mounting stator vanes to the stator vane support
EP04797660A Expired - Lifetime EP1697618B1 (en) 2003-12-23 2004-11-05 Stator vane carrier and plurality of stator vanes and method of mounting stator vanes to the stator vane carrier

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP03029771A Withdrawn EP1548232A1 (en) 2003-12-23 2003-12-23 Turbomachine comprising a stator vane support and method of mounting stator vanes to the stator vane support

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EP (2) EP1548232A1 (en)
WO (1) WO2005066463A1 (en)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7806655B2 (en) * 2007-02-27 2010-10-05 General Electric Company Method and apparatus for assembling blade shims
US8047778B2 (en) * 2009-01-06 2011-11-01 General Electric Company Method and apparatus for insuring proper installation of stators in a compressor case
US8133019B2 (en) * 2009-01-21 2012-03-13 General Electric Company Discrete load fins for individual stator vanes
CH703997A1 (en) * 2010-10-27 2012-04-30 Alstom Technology Ltd Blade assembly, in particular vane.
EP2679776A1 (en) * 2012-06-28 2014-01-01 Alstom Technology Ltd Cooling system and method for an axial flow turbine
EP2851515A1 (en) * 2013-09-24 2015-03-25 Siemens Aktiengesellschaft Assembly for attaching a turbine blade
US9388704B2 (en) * 2013-11-13 2016-07-12 Siemens Energy, Inc. Vane array with one or more non-integral platforms
EP2995775A1 (en) * 2014-09-15 2016-03-16 Siemens Aktiengesellschaft Handheld device for driving a guide vane into a vane groove
FR3048719B1 (en) * 2016-03-14 2018-03-02 Safran Aircraft Engines FLOW RECTIFIER FOR TURBOMACHINE WITH INTEGRATED AND REPORTED PLATFORMS
US11125092B2 (en) * 2018-08-14 2021-09-21 Raytheon Technologies Corporation Gas turbine engine having cantilevered stators

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Publication number Priority date Publication date Assignee Title
US998820A (en) * 1908-05-13 1911-07-25 George Westinghouse Turbine-blading.
GB216737A (en) * 1923-08-02 1924-06-05 Karl Baumann Improvements relating to elastic fluid turbines
DE518106C (en) * 1924-02-18 1931-02-24 Jan Kieswetter Device to compensate for different thermal expansions between an outer housing wall and an intermediate wall of the same housing, especially in the case of steam or gas turbines
CH482915A (en) * 1967-11-03 1969-12-15 Sulzer Ag Guide device for axial turbine
IT1062412B (en) * 1976-06-15 1984-10-10 Nuovo Pignone Spa PERFECT LOCKING SYSTEM IN POSITION OF THE BLADES ON THE STATIC CASE OF AN AXIAL COMPRESSOR OPERATING IN A PULVERULENT ENVIRONMENT
US5205708A (en) * 1992-02-07 1993-04-27 General Electric Company High pressure turbine component interference fit up
DE4436731A1 (en) * 1994-10-14 1996-04-18 Abb Management Ag compressor

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Publication number Publication date
EP1697618A1 (en) 2006-09-06
EP1548232A1 (en) 2005-06-29
WO2005066463A1 (en) 2005-07-21

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