EP2524112B1 - Schaufelscheibenanordung - Google Patents

Schaufelscheibenanordung Download PDF

Info

Publication number
EP2524112B1
EP2524112B1 EP11700085.1A EP11700085A EP2524112B1 EP 2524112 B1 EP2524112 B1 EP 2524112B1 EP 11700085 A EP11700085 A EP 11700085A EP 2524112 B1 EP2524112 B1 EP 2524112B1
Authority
EP
European Patent Office
Prior art keywords
groove
bulb
parts
faces
disk
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
EP11700085.1A
Other languages
English (en)
French (fr)
Other versions
EP2524112A1 (de
Inventor
Fabrice Marcel Noel Garin
Romain Nicolas Lunel
Bruno André Jean VARIN
Clément ROUSSILLE
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.)
Safran Aircraft Engines SAS
Safran Ceramics SA
Original Assignee
SNECMA Propulsion Solide SA
SNECMA SAS
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.)
Filing date
Publication date
Application filed by SNECMA Propulsion Solide SA, SNECMA SAS filed Critical SNECMA Propulsion Solide SA
Publication of EP2524112A1 publication Critical patent/EP2524112A1/de
Application granted granted Critical
Publication of EP2524112B1 publication Critical patent/EP2524112B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3084—Fixing blades to rotors; Blade roots ; Blade spacers the blades being made of ceramics
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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
    • F05D2250/71—Shape curved
    • 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

Definitions

  • the main parts have a variable thickness, their opposite faces having inclinations equal to the face which is in front of them among the overhanging faces and the upper faces, and thus compensate for their difference in inclination, while the external parts maintain the in place resting inserts based on the peripheral face of the disk, and that the internal parts have the same effect during operation by possibly leaning against the bulb.

Landscapes

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

Claims (4)

  1. Anordnung, umfassend eine Scheibe (2) und wenigstens eine Schaufel (4), von der ein Fuß (3) in einer Nut (1) der Scheibe aufgenommen ist, wobei die Nut zwei über einen Grund der Nut hinausragende Seiten (6) umfasst, die mit einer ersten Neigung gegenüber einer Mittelebene der Nut versehen sind, wobei der Fuß (3) zwei Oberseiten (9) aufweist, die unter den hinausragenden Seiten (6) gelegen, aber mit einer zweiten Neigung gegenüber der Mittelebene versehen sind, welche geringer als die erste Neigung ist, und wobei Einsätze (11) zwischen dem Fuß (3) und der Scheibe (2) hinzugefügt sind, die Hauptteile (12), welche zwischen den hinausragenden Seiten und den Oberseiten (9) angeordnet sind, sowie Außenteile (13), welche an die Hauptteile angeschlossen sind und durch eine Öffnung der Nut verlaufen, umfassen, dadurch gekennzeichnet, dass die Außenteile - sich in Richtung von von den Hauptteilen abgewandten freien Enden voneinander entfernend - über eine Umfangsseite (7) der Scheibe (2) verlaufen und die Einsätze (11) auch an die Hauptteile (12) angeschlossene Innenteile (14) umfassen, die - sich in Richtung von von den Hauptteilen abgewandten freien Enden einander nähernd - zwischen dem Fuß und dem Grund (5) der Nut verlaufen.
  2. Anordnung nach Anspruch 1, dadurch gekennzeichnet, dass die Schaufeln aus Verbundwerkstoff bestehen und die Scheibe aus Metall besteht.
  3. Anordnung nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, dass die Einsätze an den Innenteilen (14) voneinander getrennt sind.
  4. Anordnung nach einem der Ansprüche 1 bis 3. dadurch gekennzeichnet, dass in einem Betriebszustand, in dem der Fuß (3) auf den Mittelteilen (12) aufliegt und die Mittelteile auf den hinausragenden Seiten (6) aufliegen, zwischen den Außenteilen (13) und der Scheibe sowie zwischen den Innenteilen (14) und dem Fuß Spiele vorhanden sind.
EP11700085.1A 2010-01-12 2011-01-11 Schaufelscheibenanordung Active EP2524112B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1050164A FR2955143B1 (fr) 2010-01-12 2010-01-12 Agencement de disque aubage
PCT/EP2011/050245 WO2011086056A1 (fr) 2010-01-12 2011-01-11 Agencement de disque aubage

Publications (2)

Publication Number Publication Date
EP2524112A1 EP2524112A1 (de) 2012-11-21
EP2524112B1 true EP2524112B1 (de) 2014-12-17

Family

ID=42537539

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11700085.1A Active EP2524112B1 (de) 2010-01-12 2011-01-11 Schaufelscheibenanordung

Country Status (4)

Country Link
US (1) US9157330B2 (de)
EP (1) EP2524112B1 (de)
FR (1) FR2955143B1 (de)
WO (1) WO2011086056A1 (de)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2972483B1 (fr) 2011-03-07 2013-04-19 Snecma Carter de turbine comportant des moyens de fixation de secteurs d'anneau
FR2981132B1 (fr) * 2011-10-10 2013-12-06 Snecma Ensemble pour turbomachine a refroidissement de disque
WO2015023345A2 (en) * 2013-05-29 2015-02-19 General Electric Company Composite airfoil metal patch
FR3009579B1 (fr) 2013-08-07 2015-09-25 Snecma Carter de turbine en deux materiaux
CA2915234A1 (en) 2015-01-13 2016-07-13 Rolls-Royce Corporation Turbine wheel with clamped blade attachment
US10577951B2 (en) 2016-11-30 2020-03-03 Rolls-Royce North American Technologies Inc. Gas turbine engine with dovetail connection having contoured root
US10605100B2 (en) * 2017-05-24 2020-03-31 General Electric Company Ceramic matrix composite (CMC) turbine blade assembly, dovetail sleeve, and method of mounting CMC turbine blade
JP6765344B2 (ja) 2017-05-31 2020-10-07 三菱重工業株式会社 複合材料翼及び複合材料翼の製造方法
FR3130906B1 (fr) * 2021-12-16 2023-11-24 Safran Aircraft Engines Rotor de turbomachine

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2950083A (en) * 1954-07-23 1960-08-23 Thompson Ramo Wooldridge Inc Blade assembly
US3132841A (en) * 1958-05-12 1964-05-12 Gen Motors Corp Compressor blade and manufacture thereof
US4417854A (en) * 1980-03-21 1983-11-29 Rockwell International Corporation Compliant interface for ceramic turbine blades
FR2608674B1 (fr) * 1986-12-17 1991-04-19 Snecma Roue de turbine a aubes ceramique
US6619924B2 (en) * 2001-09-13 2003-09-16 General Electric Company Method and system for replacing a compressor blade
US7713029B1 (en) * 2007-03-28 2010-05-11 Florida Turbine Technologies, Inc. Turbine blade with spar and shell construction
US8206118B2 (en) 2008-01-04 2012-06-26 United Technologies Corporation Airfoil attachment
FR2972483B1 (fr) 2011-03-07 2013-04-19 Snecma Carter de turbine comportant des moyens de fixation de secteurs d'anneau

Also Published As

Publication number Publication date
FR2955143A1 (fr) 2011-07-15
FR2955143B1 (fr) 2012-05-11
US20120308391A1 (en) 2012-12-06
US9157330B2 (en) 2015-10-13
WO2011086056A1 (fr) 2011-07-21
EP2524112A1 (de) 2012-11-21

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