EP3309359B1 - Ensemble d'aubes mobiles pour un moteur à turbine à gaz - Google Patents

Ensemble d'aubes mobiles pour un moteur à turbine à gaz Download PDF

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Publication number
EP3309359B1
EP3309359B1 EP17195629.5A EP17195629A EP3309359B1 EP 3309359 B1 EP3309359 B1 EP 3309359B1 EP 17195629 A EP17195629 A EP 17195629A EP 3309359 B1 EP3309359 B1 EP 3309359B1
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EP
European Patent Office
Prior art keywords
stiffening
blade assembly
carrier
shaped
section
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.)
Active
Application number
EP17195629.5A
Other languages
German (de)
English (en)
Other versions
EP3309359A1 (fr
Inventor
Miklos Gäbler
Sven Brüggmann
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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Publication of EP3309359A1 publication Critical patent/EP3309359A1/fr
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Publication of EP3309359B1 publication Critical patent/EP3309359B1/fr
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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
    • 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
    • F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial blades
    • 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
    • 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
    • F01D25/005—Selecting particular materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6032—Metal matrix composites [MMC]

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

Claims (13)

  1. Module d'aubes directrices pour un groupe moteur (T), comprenant un support d'aubes (23, 24) en forme de disque ou de forme annulaire, avec plusieurs aubes directrices (20, 21) qui sont prévues le long d'un cercle autour d'un axe médian (M) du module d'aubes directrices (2a, 2b), dans lequel
    - le support d'aubes (23, 24) présente une portion de support (230, 240) s'étendant radialement vers l'intérieur dans la direction de l'axe médian (M) par rapport aux aubes directrices (20, 21),
    - la portion de support (230, 240) comprend une région de connexion (231, 241) au niveau de laquelle est fixée une structure de renforcement (5a, 5b) avec au moins un élément de renforcement (50, 51), et
    - l'élément de renforcement (50, 51) est disposé au niveau d'un premier ou d'un deuxième côté frontal du support d'aubes (23, 24),
    caractérisé en ce que
    la région de connexion (231, 241) constitue au moins une saillie axiale (2310.1-2312.2 ; 2410.1-2410.2) qui fait partie d'un profilé de la région de connexion (231, 241) de section transversale en forme de T, en forme de I ou en forme de sapin et qui est saisie sur son pourtour par engagement par correspondance de formes par l'au moins un élément de renforcement (50, 51), de telle sorte que la saillie axiale (2310.1-2312.2 ; 2410.1-2410.2) soit reçue au moins en partie entre une portion radialement extérieure et une portion radialement intérieure de l'élément de renforcement (50, 51).
  2. Module d'aubes directrices selon la revendication 1, caractérisé en ce que le profilé en forme de T, en forme de I ou en forme de sapin de la région de connexion (231, 241) s'étend au moins en partie le long d'un cercle autour de l'axe médian (M).
  3. Module d'aubes directrices selon la revendication 1 ou 2, caractérisé en ce que
    - la structure de renforcement (5a, 5b) fixée à la région de connexion (231, 241) présente au moins un premier élément de renforcement (50) et au moins un deuxième élément de renforcement (51),
    - le premier élément de renforcement (50) est disposé au niveau d'un premier côté frontal du support d'aubes (23, 24) et le deuxième élément de renforcement (51) est disposé au niveau d'un deuxième côté frontal opposé au premier côté frontal, et
    - le premier et le deuxième élément de renforcement (50, 51) sont connectés à la région de connexion (231, 241) du support d'aubes (23, 24) et sont en outre connectés l'un à l'autre.
  4. Module d'aubes directrices selon la revendication 3, caractérisé en ce que les premier et deuxième éléments de renforcement (50, 51) disposés au niveau de côtés frontaux différents du support d'aubes (23, 24) sont connectés l'un à l'autre par le biais d'au moins un élément de connexion séparé (6) de la structure de renforcement (5a, 5b).
  5. Module d'aubes directrices selon la revendication 4, caractérisé en ce que l'au moins un élément de connexion séparé (6) s'étend à travers une ouverture de passage (O1, O2) dans la portion de support (230, 240) .
  6. Module d'aubes directrices selon la revendication 4 ou 5, caractérisé en ce que l'au moins un élément de connexion séparé (6) vient en prise autour des premier et deuxième éléments de renforcement (50, 51) de telle sorte qu'au moins des parties des deux éléments de renforcement (50, 51) soient reçues, en coupe transversale le long de l'axe médian (M), entre deux portions (60, 61) de l'élément de connexion (6).
  7. Module d'aubes directrices selon l'une quelconque des revendications 4 à 6, caractérisé en ce que l'au moins un élément de connexion est réalisé sous forme de pièce de serrage (6) qui est retenue par engagement par correspondance de formes et/ou par force au niveau des deux premier et deuxième éléments de renforcement (50, 51) et exerce à chaque fois sur le premier ou le deuxième élément de renforcement (50, 51) disposé au niveau de la région de connexion (231, 241), une force agissant dans la direction de l'autre, parmi le deuxième et le premier élément de renforcement (51, 50).
  8. Module d'aubes directrices selon l'une quelconque des revendications 1 à 7, caractérisé en ce que l'au moins un élément de renforcement (50, 51) est réalisé sous forme annulaire.
  9. Module d'aubes directrices selon l'une quelconque des revendications précédentes, caractérisé en ce que l'au moins un élément de renforcement (50, 51) est fabriqué au moins en partie en un matériau composite à matrice métallique.
  10. Module d'aubes directrices selon la revendication 9, caractérisé en ce que l'au moins un élément de renforcement (50, 51) présente un noyau (500) à gaine extérieure constitué d'un matériau composite à matrice métallique.
  11. Module d'aubes directrices selon la revendication 9 ou 10, caractérisé en ce que le support d'aubes (23, 24) présente une ouverture de passage (O1, O2) s'étendant axialement par rapport à l'axe médian (M), qui est limitée radialement par un bord intérieur de la portion de support (230, 240), et une portion de l'au moins un élément de renforcement (50, 51), formée d'un matériau composite à matrice métallique, s'étend axialement radialement à l'intérieur quant au bord intérieur de la région de connexion (231, 241).
  12. Module d'aubes directrices selon l'une quelconque des revendications précédentes, caractérisé en ce que le support d'aubes (23, 24) présente une ouverture de passage (O1, O2) s'étendant axialement par rapport à l'axe médian (M), qui est limitée radialement par un bord intérieur de la portion de support (230, 240), et l'au moins un élément de renforcement (50, 51) de la structure de renforcement (5a, 5b) s'étend axialement, avec au moins une portion (50.1, 51.2), radialement à l'intérieur quant au bord intérieur de la région de connexion (231, 241).
  13. Moteur à turbine à gaz comprenant au moins un module d'aubes directrices (2a, 2b) selon l'une quelconque des revendications 1 à 12.
EP17195629.5A 2016-10-12 2017-10-10 Ensemble d'aubes mobiles pour un moteur à turbine à gaz Active EP3309359B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102016219815.7A DE102016219815A1 (de) 2016-10-12 2016-10-12 Laufschaufelbaugruppe mit ring- oder scheibenförmigem Schaufelträger und radial innenliegender Versteifungsstruktur

Publications (2)

Publication Number Publication Date
EP3309359A1 EP3309359A1 (fr) 2018-04-18
EP3309359B1 true EP3309359B1 (fr) 2019-07-03

Family

ID=60080611

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17195629.5A Active EP3309359B1 (fr) 2016-10-12 2017-10-10 Ensemble d'aubes mobiles pour un moteur à turbine à gaz

Country Status (3)

Country Link
US (1) US10794188B2 (fr)
EP (1) EP3309359B1 (fr)
DE (1) DE102016219815A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102018205480A1 (de) * 2018-04-11 2019-10-17 Rolls-Royce Deutschland Ltd & Co Kg Laufschaufelbaugruppe mit einem Sperrelement zur axialen Sicherung eines Versteifungselements einer radial innenliegenden Versteifungsstruktur
US11549373B2 (en) 2020-12-16 2023-01-10 Raytheon Technologies Corporation Reduced deflection turbine rotor
CN114934815B (zh) * 2022-05-12 2023-10-31 中国航发四川燃气涡轮研究院 一种金属基复合材料箍环式发动机转子叶环结构

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US1325208A (en) * 1919-12-16 Elastic-fi
US1178452A (en) 1913-10-01 1916-04-04 Terry Steam Turbine Company Turbine-blading.
US3501249A (en) * 1968-06-24 1970-03-17 Westinghouse Electric Corp Side plates for turbine blades
US3610772A (en) * 1970-05-04 1971-10-05 Gen Motors Corp Bladed rotor
US3610777A (en) * 1970-05-15 1971-10-05 Gen Motors Corp Composite drum rotor
US3656864A (en) * 1970-11-09 1972-04-18 Gen Motors Corp Turbomachine rotor
FR2143561B1 (fr) * 1971-06-29 1974-03-08 Snecma
US3765796A (en) * 1972-05-01 1973-10-16 United Aircraft Corp Filament reinforced rotor assembly
US3787141A (en) * 1972-11-30 1974-01-22 United Aircraft Corp Filament reinforced motor assembly
DE4132332A1 (de) * 1990-12-14 1992-06-25 Ottomar Gradl Anordnung zum befestigen von schaufeln an der scheibe eines rotors
DE4324755C1 (de) * 1993-07-23 1994-09-22 Mtu Muenchen Gmbh Verfahren zur Herstellung faserverstärkter Triebwerkskomponenten
US5660526A (en) * 1995-06-05 1997-08-26 Allison Engine Company, Inc. Gas turbine rotor with remote support rings
US5632600A (en) * 1995-12-22 1997-05-27 General Electric Company Reinforced rotor disk assembly
GB2456637B (en) * 1997-06-03 2010-01-13 Rolls Royce Plc A fibre reinforced metal rotor
US6213720B1 (en) * 1999-06-11 2001-04-10 Alliedsignal, Inc. High strength composite reinforced turbomachinery disk
DE10163951C1 (de) 2001-12-22 2002-12-19 Mtu Aero Engines Gmbh Rotorscheibe aus Metall mit örtlichen Faserverstärkungen
DE10218459B3 (de) * 2002-04-25 2004-01-15 Mtu Aero Engines Gmbh Verdichter in mehrstufiger Axialbauart
FR2845436B1 (fr) * 2002-10-02 2004-12-31 Snecma Moteurs Tambour formant en particulier un rotor de turbomachine, compresseur et turbomoteur comprenant un tel tambour
DE10358421A1 (de) * 2003-12-13 2005-07-07 Mtu Aero Engines Gmbh Rotor für eine Turbomaschine
DE102006015838A1 (de) * 2006-04-03 2007-10-04 Rolls-Royce Deutschland Ltd & Co Kg Axialkompressor für ein Gasturbinentriebwerk
FR2941487B1 (fr) 2009-01-28 2011-03-04 Snecma Aube de turbomachine en materiau composite a pied renforce

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Also Published As

Publication number Publication date
US20180100398A1 (en) 2018-04-12
DE102016219815A1 (de) 2018-04-12
US10794188B2 (en) 2020-10-06
EP3309359A1 (fr) 2018-04-18

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