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EP1564376B1 - Turbomachine rotor construction - Google Patents

Turbomachine rotor construction Download PDF

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Publication number
EP1564376B1
EP1564376B1 EP05100785.4A EP05100785A EP1564376B1 EP 1564376 B1 EP1564376 B1 EP 1564376B1 EP 05100785 A EP05100785 A EP 05100785A EP 1564376 B1 EP1564376 B1 EP 1564376B1
Authority
EP
European Patent Office
Prior art keywords
rotor
rotor core
rings
cooling air
hot gas
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.)
Not-in-force
Application number
EP05100785.4A
Other languages
German (de)
French (fr)
Other versions
EP1564376A2 (en
EP1564376A3 (en
Inventor
Klaus DÖBBELING
Joachim Krautzig
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.)
Ansaldo Energia Switzerland AG
Original Assignee
Ansaldo Energia Switzerland AG
Priority date (The priority date 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 date listed.)
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Publication date
Application filed by Ansaldo Energia Switzerland AG filed Critical Ansaldo Energia Switzerland AG
Publication of EP1564376A2 publication Critical patent/EP1564376A2/en
Publication of EP1564376A3 publication Critical patent/EP1564376A3/en
Application granted granted Critical
Publication of EP1564376B1 publication Critical patent/EP1564376B1/en
Not-in-force legal-status Critical Current
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/5853—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps heat insulation or conduction

Definitions

  • the present invention relates to the field of turbomachinery. It relates to a rotor according to the preamble of claim 1.
  • Rotors for high-temperature use in gas or steam turbines are preferably made of ferritic steels because of the lower material costs, the better weldability and ultrasound testability and because of the better fracture mechanical properties. Above 450 ° C, however, the mechanical properties of ferritic steels decrease so much that the use of austenitic steels becomes necessary.
  • the rotor located in gas turbines below the hot gas channel is shielded by separate blades and heat shields made of high temperature materials.
  • this shield has a highly segmented structure and the individual elements are attached to the rotor only by hooks of various types. If a ferritic material is used for the rotor, relatively large amounts of cooling air of at most 450 ° C for flushing the spaces between the rotor and the shielding elements are required. Compressors, even if they have outlet temperatures greater than about 450 ° C, have so far been mostly designed without any shielding and cooling because the clean shield provides little help against excessive peak loads and cooling with recirculation of cooling air into the compressor duct Efficiency deteriorates.
  • the essence of the invention is a rotor core of a first favorable Material that is not sufficient for the higher temperatures in the hot gas channel or cooling air channel, and then concentrically surround the rotor core with shielding rings of a second material, which shield the rotor core against the higher temperature in the hot gas channel or cooling air duct, the second material opposite the first material has a higher heat resistance.
  • the shielding rings are connected to the rotor core cohesively.
  • the first material is a ferritic steel and the second material is an austenitic steel. It has proven particularly useful to connect the shielding rings with the rotor core by soldering or welding. The shielding effect can be further improved if additional cooling channels for the passage of cooling air are provided on the inside of the shielding rings.
  • the shielding rings can be designed exclusively for shielding the rotor core and each have a flat rectangular or wedge-shaped cross section, or, if they shield the rotor core against the temperatures in the hot gas duct, can be designed to accommodate moving blades.
  • the shielding rings each have a cross-sectional profile in the form of a double T in order to achieve greater radial flexibility and thermal insulation.
  • a rotor 11 of a compressor 10 is shown in longitudinal section.
  • the compressor 10 is part of a gas turbine.
  • the section includes the high-pressure and output stages of the multi-stage compressor 10.
  • the rotor 11 is rotatably mounted within the compressor 10 about a rotor axis 21.
  • the rotor 11 consists of a plurality of rotor rings 16a, 16b, 16c arranged in succession in the axial direction, which are connected to one another by welds 15, 17.
  • the rotor 11 is surrounded concentrically by a hot gas channel 12 through which the compressed gas (air) flows in the direction of the drawn arrows.
  • blades 13 and vanes 14 are arranged in alternating rows in the axial direction one behind the other.
  • the vanes 14 are mounted on the hot gas channel 12 enclosing housing.
  • the blades 13 are fixed to the rotor 11 and rotate with the rotor 11 about the rotor axis 21.
  • the central rotor ring 16b in the section of which the high-pressure and output stages of the compressor 10 are located, and which is correspondingly exposed to the highest temperatures in the hot gas duct 12 (or in the cooling air duct), is composed of two different materials: the main component is a solid, central rotor core 22 made of a ferritic steel.
  • Several shielding rings 18 made of austenitic steel with a double T-shaped cross-sectional profile are pushed onto this rotor core one behind the other in the axial direction and welded to the rotor core 22 on the ring inner surface (welded connection 19). In another embodiment, they are soldered. Between adjacent shielding rings 18 are on the outer periphery recesses provided, which serve for receiving and holding the blades 13.
  • the thermal capacity of the rotor 11 is improved, without the rotor must be made entirely of an austenitic material.
  • the austenitic material shielding rings 18 between the hot gas passage 13 of the compressor or the turbine cooling air passage and the ferritic material rotor core 22, the temperatures at the compressor outlet and the cooling air in the cooling air passage can be raised by about 100 ° C.
  • the present invention proposes to use a rotor with a rotor core made of ferritic material, which is surrounded by relatively thin shielding rings of austenitic material, which are firmly connected to the rotor core by soldering or welding.
  • the cross-section of the shielding rings may vary depending on the local requirements: Wide and flat rectangular cross-sections, which are not the subject of the present invention, with a cylindrical or conical outer surface are particularly suitable for purely shielding purposes.
  • Individual rings may be provided with hooks for holding rotor blades.
  • the inventive rings with double T-profile allow greater radial flexibility and thermal insulation.
  • channels for a cooling medium may be integrated on the inner circumference of the shielding rings.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

TECHNISCHES GEBIETTECHNICAL AREA

Die vorliegende Erfindung bezieht sich auf das Gebiet der Turbomaschinen. Sie betrifft einen Rotor gemäss dem Oberbegriff des Anspruchs 1.The present invention relates to the field of turbomachinery. It relates to a rotor according to the preamble of claim 1.

STAND DER TECHNIKSTATE OF THE ART

Rotoren für den Hochtemperatureinsatz bei Gas- oder Dampfturbinen werden wegen der niedrigeren Materialkosten, der besseren Schweissbarkeit und Ultraschall-Testbarkeit und wegen der günstigeren bruchmechanischen Eigenschaften vorzugsweise aus ferritischen Stählen hergestellt. Oberhalb von 450°C fallen jedoch die mechanischen Eigenschaften von ferritischen Stählen so stark ab, dass der Einsatz von austenitischen Stählen notwendig wird.Rotors for high-temperature use in gas or steam turbines are preferably made of ferritic steels because of the lower material costs, the better weldability and ultrasound testability and because of the better fracture mechanical properties. Above 450 ° C, however, the mechanical properties of ferritic steels decrease so much that the use of austenitic steels becomes necessary.

Seit langer Zeit wird der in Gasturbinen unterhalb des Heissgaskanals liegende Rotor durch separate Schaufeln und Hitzeschilde aus Hochtemperaturmaterialien abgeschirmt. Diese Abschirmung hat jedoch eine hochgradig segmentierte Struktur und die einzelnen Elemente sind nur durch Haken verschiedener Art am Rotor befestigt. Wenn ein ferritisches Material für den Rotor eingesetzt wird, werden relativ grosse Mengen Kühlluft von maximal 450°C zur Spülung der Zwischenräume zwischen dem Rotor und den Abschirmelementen benötigt.
Kompressoren sind, selbst wenn sie Auslasstemperaturen von mehr als etwa 450°C hatten, bisher meist ohne irgendeine Abschirmung und Kühlung ausgelegt worden, weil die reine Abschirmung nur wenig Hilfe gegen zu hohe Spitzenlasten bringt und die Kühlung mit einer Rückführung von Kühlluft in den Kompressorkanal den Wirkungsgrad verschlechtert.For a long time, the rotor located in gas turbines below the hot gas channel is shielded by separate blades and heat shields made of high temperature materials. However, this shield has a highly segmented structure and the individual elements are attached to the rotor only by hooks of various types. If a ferritic material is used for the rotor, relatively large amounts of cooling air of at most 450 ° C for flushing the spaces between the rotor and the shielding elements are required.
Compressors, even if they have outlet temperatures greater than about 450 ° C, have so far been mostly designed without any shielding and cooling because the clean shield provides little help against excessive peak loads and cooling with recirculation of cooling air into the compressor duct Efficiency deteriorates.

Gleichwohl ist auch bei Kompressoren bereits der Einsatz von Hitzeschilden zur Abschirmung des Rotors vom Heissgaskanal vorgeschlagen worden (siehe die US-A-5,842,831 und die US-BI-6,416,276 ). Die Hitzeschilde sind bei diesen bekannten Abschirmungen formschlüssig am Rotor befestigt. Sie weisen daher dieselben Nachteile auf, die weiter oben bereits für die Gasturbinen mit segmentierter Abschirmung angeführt worden sind. Es ist ebenfalls bekannt den Rotor aus zwei verschiedenen Teilen herzustellen, nämlich einen Rotorkern und z.B. hohl zylindrische Abschirmungen, die aus verschiedenen Materialien angefertigt werden und die anschließend mittels einer stoffschlüssigen Verbindung miteinander verbunden werden. Diese Vorgehensweise ist z.B. aus US6350325 , EP0264936 und GB616432 bekannt.Nevertheless, the use of heat shields for shielding the rotor from the hot gas duct has also been proposed in compressors (see the US Pat US-A-5,842,831 and the US 6,416,276 BI ). The heat shields are positively secured to the rotor in these known shields. They therefore have the same disadvantages that have already been mentioned above for the gas turbine with segmented shielding. It is also known to manufacture the rotor from two different parts, namely a rotor core and, for example, hollow cylindrical shields, which are made of different materials and which are then connected to each other by means of a material connection. This procedure is eg off US6350325 . EP0264936 and GB616432 known.

DARSTELLUNG DER ERFINDUNGPRESENTATION OF THE INVENTION

Es ist daher Aufgabe der Erfindung, einen Rotor für den Betrieb bei erhöhten Temperaturen zu schaffen, der die Nachteile bekannter Rotoren vermeidet und insbesondere die Verwendung eines günstigeren Materials für den Rotor ermöglicht, ohne wesentliche Abstriche bei der Betriebstemperatur und dem Wirkungsgrad der Maschine machen zu müssen.
Die Aufgabe wird durch die Gesamtheit der Merkmale des Anspruchs 1 gelöst. Der Kern der Erfindung besteht darin, einen Rotorkern aus einem ersten günstigen Material zu fertigen, das für die höheren Temperaturen im Heissgaskanal bzw. Kühlluftkanal nicht ausreicht, und dann den Rotorkern konzentrisch mit Abschirmringen aus einem zweiten Material zu umgeben, welche den Rotorkern gegen die höhere Temperatur im Heissgaskanal bzw. Kühlluftkanal abschirmen, wobei das zweite Material gegenüber dem ersten Material eine höhere Wärmefestigkeit aufweist. Die Abschirmringe werden dabei mit dem Rotorkern stoffschlüssig verbunden.
Bevorzugt ist das erste Material ein ferritischer Stahl und zweite Material ein austenitischer Stahl.
Es hat sich besonders bewährt, die Abschirmringe mit dem Rotorkern durch Löten oder Schweissen zu verbinden.
Die Abschirmwirkung lässt sich weiter verbessern, wenn auf der Innenseite der Abschirmringe zusätzlich Kühlkanäle für das Durchströmen von Kühlluft vorgesehen sind.
Je nach Position innerhalb des Rotors können die Abschirmringe ausschliesslich zur Abschirmung des Rotorkerns ausgebildet sein und jeweils einen flachen rechteckigen oder keilförmigen Querschnitt aufweisen, oder sie können, wenn sie den Rotorkern gegen die Temperaturen im Heissgaskanal abschirmen, zur Aufnahme von Laufschaufeln ausgebildet sein. Erfindungsgemäss weisen die Abschirmringe jeweils ein Querschnittsprofil in Form eines doppelten T auf, um eine grössere radiale Flexibilität und Wärmeisolierung zu erreichen.It is therefore an object of the invention to provide a rotor for operation at elevated temperatures, which avoids the disadvantages of known rotors and in particular allows the use of a cheaper material for the rotor, without having to make significant reductions in the operating temperature and efficiency of the machine ,
The object is solved by the entirety of the features of claim 1. The essence of the invention is a rotor core of a first favorable Material that is not sufficient for the higher temperatures in the hot gas channel or cooling air channel, and then concentrically surround the rotor core with shielding rings of a second material, which shield the rotor core against the higher temperature in the hot gas channel or cooling air duct, the second material opposite the first material has a higher heat resistance. The shielding rings are connected to the rotor core cohesively.
Preferably, the first material is a ferritic steel and the second material is an austenitic steel.
It has proven particularly useful to connect the shielding rings with the rotor core by soldering or welding.
The shielding effect can be further improved if additional cooling channels for the passage of cooling air are provided on the inside of the shielding rings.
Depending on the position within the rotor, the shielding rings can be designed exclusively for shielding the rotor core and each have a flat rectangular or wedge-shaped cross section, or, if they shield the rotor core against the temperatures in the hot gas duct, can be designed to accommodate moving blades. According to the invention, the shielding rings each have a cross-sectional profile in the form of a double T in order to achieve greater radial flexibility and thermal insulation.

Die oben erwähnten flachen rechteckigen oder keilförmigen Querschnitte sind somit nicht Gegenstand der vorliegenden Erfindung.The above-mentioned flat rectangular or wedge-shaped cross sections are therefore not the subject of the present invention.

KURZE ERLÄUTERUNG DER FIGURENBRIEF EXPLANATION OF THE FIGURES

Die Erfindung soll nachfolgend anhand von Ausführungsbeispielen im Zusammenhang mit der Zeichnung näher erläutert werden. Die einzige Figur zeigt in einem längsgeschnittenen Ausschnitt den Rotor eines Kompressors gemäss einem bevorzugten Ausführungsbeispiel der ErfindungThe invention will be explained in more detail with reference to embodiments in conjunction with the drawings. The only figure shows in a longitudinal section, the rotor of a compressor according to a preferred embodiment of the invention

WEGE ZUR AUSFÜHRUNG DER ERFINDUNGWAYS FOR CARRYING OUT THE INVENTION

In der Figur ist der Ausschnitt eines Rotors 11 eines Kompressors 10 im Längsschnitt wiedergegeben. Der Kompressor 10 ist Teil einer Gasturbine. Der Ausschnitt umfasst die Hochdruck- und Ausgangsstufen des mehrstufigen Kompressors 10. Der Rotor 11 ist innerhalb des Kompressors 10 um eine Rotorachse 21 drehbar gelagert. Der Rotor 11 besteht aus mehreren in axialer Richtung hintereinander angeordneten Rotorringen 16a, 16b, 16c, die durch Schweissnähte 15, 17 miteinander verbunden sind. Der Rotor 11 ist konzentrisch von einem Heissgaskanal 12 umgeben, durch den in Richtung der eingezeichneten Pfeile das komprimierte Gas (Luft) strömt.In the figure, the detail of a rotor 11 of a compressor 10 is shown in longitudinal section. The compressor 10 is part of a gas turbine. The section includes the high-pressure and output stages of the multi-stage compressor 10. The rotor 11 is rotatably mounted within the compressor 10 about a rotor axis 21. The rotor 11 consists of a plurality of rotor rings 16a, 16b, 16c arranged in succession in the axial direction, which are connected to one another by welds 15, 17. The rotor 11 is surrounded concentrically by a hot gas channel 12 through which the compressed gas (air) flows in the direction of the drawn arrows.

Im Heissgaskanal 12 sind in alternierenden Reihen in axialer Richtung hintereinander Laufschaufeln 13 und Leitschaufeln 14 angeordnet. Die Leitschaufeln 14 sind am den Heissgaskanal 12 umschliessenden Gehäuse angebracht. Die Laufschaufeln 13 sind am Rotor 11 befestigt und drehen sich mit dem Rotor 11 um die Rotorachse 21.In the hot gas channel 12 blades 13 and vanes 14 are arranged in alternating rows in the axial direction one behind the other. The vanes 14 are mounted on the hot gas channel 12 enclosing housing. The blades 13 are fixed to the rotor 11 and rotate with the rotor 11 about the rotor axis 21.

Der mittlere Rotorring 16b, in dessen Abschnitt sich die Hochdruck- und Ausgangsstufen des Kompressors 10 befinden, und der entsprechend den höchsten Temperaturen im Heissgaskanal 12 (oder im Kühlluftkanal) ausgesetzt ist, ist aus zwei unterschiedlichen Materialien aufgebaut: Hauptbestandteil ist ein massiver, zentraler Rotorkern 22 aus einem ferritischen Stahl. Auf diesen Rotorkern sind in axialer Richtung hintereinander mehrere Abschirmringe 18 aus austenitischem Stahl mit Doppel-T-förmigem Querschnittsprofil aufgeschoben und an der Ringinnenfläche mit dem Rotorkern 22 verschweisst (Schweissverbindung 19). In einem anderen Ausführungsbeispiel sind sie verlötet. Zwischen benachbarten Abschirmringen 18 sind am äusseren Umfang Aussparungen vorgesehen, die zur Aufnahme und Halterung der Laufschaufeln 13 dienen. Unterhalb der Laufschaufeln 13 befinden sich zwischen den Abschirmringen 18 Hohlräume. Durch den T-förmigen Fussbereich der Abschirmringe 18 verlaufen kurz oberhalb der Schweissverbindungen 19 in axialer Richtung zusätzliche Kühlkanäle 20, welche die thermische Entkopplung zwischen Rotorkern 22 und Heissgaskanal 12 bzw. Kühlluftkanal weiter verbessern.
Durch die vorliegende Erfindung wird die thermische Belastbarkeit des Rotors 11 verbessert, ohne dass der Rotor vollständig aus einem austenitischen Material hergestellt werden muss. Durch die Anordnung der Abschirmringe 18 aus austenitischem Material zwischen dem Heissgaskanal 13 des Kompressors oder dem Kühlluftkanal der Turbine und dem Rotorkern 22 aus ferritischem Material können die Temperaturen am Kompressorauslass bzw. der Kühlluft im Kühlluftkanal um etwa 100°C angehoben werden. Gleichzeitig ist nur eine geringe Menge an Kühlluft mit niedrigerer Temperatur zur Kühlung der Innenseite der Abschirmringe 18 (mittels der Kühlkanäle 20) nötig. Hierdurch lassen sich deutliche Verbesserungen im Wirkungsgrad erzielen, ohne dass der Rotor in seiner Gesamtheit aus einem anderen Material gefertigt werden muss.
Insgesamt schlägt die vorliegende Erfindung vor, einen Rotor mit einem Rotorkern aus ferritischem Material einzusetzen, der von relativ dünnen Abschirmringen aus austenitischem Material umgeben ist, die mit dem Rotorkern durch Löten oder Schweissen fest verbunden sind. Der Querschnitt der Abschirmringe kann je nach den lokalen Anforderungen unterschiedlich sein: Breite und flache rechteckige Querschnitte, welche nicht Gegenstand der vorliegenden Erfindung sind, mit einer zylindrischen oder konischen Aussenfläche sind besonders für reine Abschirmzwecke geeignet. Einzelne Ringe können mit Haken für die Halterung von Laufschaufeln versehen sein. Die erfindungsgemässen Ringe mit Doppel-T-Profil ermöglichen eine grössere radiale Flexibilität und Wärmeisolation. Um den ferritischen Rotorkern vor zu hohen Temperaturen zu schützen, können Kanäle für ein Kühlmedium am inneren Umfang der Abschirmringe integriert sein.The central rotor ring 16b, in the section of which the high-pressure and output stages of the compressor 10 are located, and which is correspondingly exposed to the highest temperatures in the hot gas duct 12 (or in the cooling air duct), is composed of two different materials: the main component is a solid, central rotor core 22 made of a ferritic steel. Several shielding rings 18 made of austenitic steel with a double T-shaped cross-sectional profile are pushed onto this rotor core one behind the other in the axial direction and welded to the rotor core 22 on the ring inner surface (welded connection 19). In another embodiment, they are soldered. Between adjacent shielding rings 18 are on the outer periphery recesses provided, which serve for receiving and holding the blades 13. Below the blades 13 are located between the shield 18 cavities. Due to the T-shaped foot region of the shielding rings 18, additional cooling channels 20, which further improve the thermal decoupling between the rotor core 22 and the hot gas channel 12 or cooling air channel, extend in the axial direction just above the welded connections 19.
By the present invention, the thermal capacity of the rotor 11 is improved, without the rotor must be made entirely of an austenitic material. By arranging the austenitic material shielding rings 18 between the hot gas passage 13 of the compressor or the turbine cooling air passage and the ferritic material rotor core 22, the temperatures at the compressor outlet and the cooling air in the cooling air passage can be raised by about 100 ° C. At the same time, only a small amount of lower temperature cooling air is needed to cool the inside of the shielding rings 18 (by means of the cooling channels 20). As a result, significant improvements in the efficiency can be achieved without the rotor in its entirety must be made of a different material.
Overall, the present invention proposes to use a rotor with a rotor core made of ferritic material, which is surrounded by relatively thin shielding rings of austenitic material, which are firmly connected to the rotor core by soldering or welding. The cross-section of the shielding rings may vary depending on the local requirements: Wide and flat rectangular cross-sections, which are not the subject of the present invention, with a cylindrical or conical outer surface are particularly suitable for purely shielding purposes. Individual rings may be provided with hooks for holding rotor blades. The inventive rings with double T-profile allow greater radial flexibility and thermal insulation. In order to protect the ferritic rotor core from excessively high temperatures, channels for a cooling medium may be integrated on the inner circumference of the shielding rings.

BEZUGSZEICHENLISTELIST OF REFERENCE NUMBERS

1010
Kompressorcompressor
1111
Rotorrotor
1212
HeissgaskanalHot-gas duct
1313
Laufschaufelblade
1414
Leitschaufelvane
15,1715.17
SchweissnahtWeld
16a,b,c16a, b, c
Rotorringrotor ring
1818
Abschirmringshielding
1919
Schweissverbindungwelded joint
2020
Kühlkanalcooling channel
2121
Rotorachserotor axis
2222
Rotorkernrotor core

Claims (5)

  1. Rotor (11) of a thermally loaded turbomachine, in particular a compressor (10) or a gas turbine, which rotor (11) is mounted rotatably about a rotor axis (21) and surrounded concentrically by a hot gas channel (12) or cooling air channel, wherein the rotor (11) comprises a rotor core (22) made from a first material, the rotor core (22) is concentrically surrounded by screening rings (18) made from a second material which screen the rotor core (22) against the temperature in the hot gas channel (12) or cooling air channel, wherein the second material has a higher heat resistance than the first material, and the screening rings (18) are connected to the rotor core (22) by substance bonding; the rotor is characterized in that the screening rings (18) each have a cross-sectional profile in the form of a double T.
  2. Rotor according to claim 1, characterized in that the first material is a ferritic steel, and the second material is an austenitic steel.
  3. Rotor according to one of claims 1 or 2, characterized in that the screening rings (18) are connected to the rotor core (22) by soldering or welding.
  4. Rotor according to any of claims 1 to 3, characterized in that cooling channels (20) are provided on the inside of the screening rings (18) for the through-flow of cooling air.
  5. Rotor according to any of claims 1 to 4, characterized in that the screening rings (18) screen the rotor core (22) against the temperatures in the hot gas channel (12), and that the screening rings (18) are configured to receive rotor blades (13).
EP05100785.4A 2004-02-14 2005-02-04 Turbomachine rotor construction Not-in-force EP1564376B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004007327A DE102004007327A1 (en) 2004-02-14 2004-02-14 rotor
DE102004007327 2004-02-14

Publications (3)

Publication Number Publication Date
EP1564376A2 EP1564376A2 (en) 2005-08-17
EP1564376A3 EP1564376A3 (en) 2013-06-19
EP1564376B1 true EP1564376B1 (en) 2018-10-03

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EP05100785.4A Not-in-force EP1564376B1 (en) 2004-02-14 2005-02-04 Turbomachine rotor construction

Country Status (3)

Country Link
US (1) US7476078B2 (en)
EP (1) EP1564376B1 (en)
DE (1) DE102004007327A1 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9771802B2 (en) 2014-02-25 2017-09-26 Siemens Energy, Inc. Thermal shields for gas turbine rotor
US10036278B2 (en) * 2014-04-11 2018-07-31 United Technologies Corporation High pressure compressor thermal shield apparatus and system

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GB616432A (en) * 1946-08-30 1949-01-21 Power Jets Res & Dev Ltd Improvements relating to turbine rotors and the like bladed structures
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Also Published As

Publication number Publication date
DE102004007327A1 (en) 2005-09-15
EP1564376A2 (en) 2005-08-17
US7476078B2 (en) 2009-01-13
US20060269403A9 (en) 2006-11-30
EP1564376A3 (en) 2013-06-19
US20050180847A1 (en) 2005-08-18

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