EP0909924A3 - Suspension for an annular gas turbine combustor - Google Patents

Suspension for an annular gas turbine combustor Download PDF

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Publication number
EP0909924A3
EP0909924A3 EP98117869A EP98117869A EP0909924A3 EP 0909924 A3 EP0909924 A3 EP 0909924A3 EP 98117869 A EP98117869 A EP 98117869A EP 98117869 A EP98117869 A EP 98117869A EP 0909924 A3 EP0909924 A3 EP 0909924A3
Authority
EP
European Patent Office
Prior art keywords
suspension
gas turbine
leg
annular gas
combustion chamber
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.)
Granted
Application number
EP98117869A
Other languages
German (de)
French (fr)
Other versions
EP0909924B1 (en
EP0909924A2 (en
Inventor
Michael Ebel
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
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP0909924A2 publication Critical patent/EP0909924A2/en
Publication of EP0909924A3 publication Critical patent/EP0909924A3/en
Application granted granted Critical
Publication of EP0909924B1 publication Critical patent/EP0909924B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • F01D25/164—Flexible supports; Vibration damping means associated with the bearing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/60—Assembly methods
    • F05B2230/604—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins
    • F05B2230/606—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Die Erfindung betrifft eine Aufhängung einer ringförmigen Gasturbinen-Brennkammer im Austrittsbereich derselben an einer Gehäusewand, über eine sich an die äußere Brennkammerwand anschließende, ringförmige, geknickt ausgebildete Armstruktur, die in Bezug auf die Gasturbinen-Längsachse einen äußeren und einen inneren Schenkel aufweist. Erfindungsgemäß schließt sich an den äußeren Schenkel ein Flansch an, der über ein lösbares Verbindungselement fest mit der Gehäusewand verbunden ist. Bevorzugt weisen beide Schenkel über dem Umfang gleichartig verteilt angeordnete, schwalbenschwanzförmige Durchbrechungen auf, deren engste Abschnitte der Knicklinie der Armstruktur zugewandt und zur Knicklinie hin offen sind, so daß zwischen jeder Durchbrechung im äußeren Schenkel und der benachbarten Durchbrechung im inneren Schenkel eine Verbindungslücke vorliegt. Hierdurch ergibt sich eine Aufhängung nach Art einer Blattfeder.

Figure 00000001
The invention relates to a suspension of an annular gas turbine combustion chamber in the outlet region thereof on a housing wall, via an annular, kinked arm structure which adjoins the outer combustion chamber wall and which has an outer and an inner leg with respect to the longitudinal axis of the gas turbine. According to the invention, a flange adjoins the outer leg and is fixedly connected to the housing wall via a releasable connecting element. Preferably, both legs have dovetail-shaped openings distributed uniformly over the circumference, the narrowest sections of which face the crease line of the arm structure and are open towards the crease line, so that there is a connection gap between each opening in the outer leg and the adjacent opening in the inner leg. This results in a suspension in the manner of a leaf spring.
Figure 00000001
EP98117869A 1997-10-16 1998-09-21 Suspension for an annular gas turbine combustor Expired - Lifetime EP0909924B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19745683A DE19745683A1 (en) 1997-10-16 1997-10-16 Suspension of an annular gas turbine combustion chamber
DE19745683 1997-10-16

Publications (3)

Publication Number Publication Date
EP0909924A2 EP0909924A2 (en) 1999-04-21
EP0909924A3 true EP0909924A3 (en) 2000-08-02
EP0909924B1 EP0909924B1 (en) 2003-07-16

Family

ID=7845693

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98117869A Expired - Lifetime EP0909924B1 (en) 1997-10-16 1998-09-21 Suspension for an annular gas turbine combustor

Country Status (3)

Country Link
US (1) US6131384A (en)
EP (1) EP0909924B1 (en)
DE (2) DE19745683A1 (en)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2825783B1 (en) 2001-06-06 2003-11-07 Snecma Moteurs HANGING OF CMC COMBUSTION CHAMBER OF TURBOMACHINE BY BRAZED LEGS
FR2825787B1 (en) 2001-06-06 2004-08-27 Snecma Moteurs FITTING OF CMC COMBUSTION CHAMBER OF TURBOMACHINE BY FLEXIBLE LINKS
FR2825785B1 (en) * 2001-06-06 2004-08-27 Snecma Moteurs TWO-PIECE TURBOMACHINE CMC COMBUSTION CHAMBER LINKAGE
FR2825781B1 (en) * 2001-06-06 2004-02-06 Snecma Moteurs ELASTIC MOUNTING OF THIS COMBUSTION CMC OF TURBOMACHINE IN A METAL HOUSING
FR2825784B1 (en) * 2001-06-06 2003-08-29 Snecma Moteurs HANGING THE TURBOMACHINE CMC COMBUSTION CHAMBER USING THE DILUTION HOLES
FR2825782A1 (en) * 2001-06-06 2002-12-13 Snecma Moteurs Turbine with metal casing has composition combustion chamber fitted with sliding coupling to allow for differences in expansion coefficients
SE519323C2 (en) * 2001-06-28 2003-02-11 Volvo Aero Ab Modular gas turbine
FR2829228B1 (en) * 2001-08-28 2005-07-15 Snecma Moteurs ANNULAR COMBUSTION CHAMBER WITH DOUBLE HEADED HEAD
FR2840974B1 (en) * 2002-06-13 2005-12-30 Snecma Propulsion Solide SEAL RING FOR COMBUSTION CAHMBERS AND COMBUSTION CHAMBER COMPRISING SUCH A RING
US7025563B2 (en) * 2003-12-19 2006-04-11 United Technologies Corporation Stator vane assembly for a gas turbine engine
US7229247B2 (en) * 2004-08-27 2007-06-12 Pratt & Whitney Canada Corp. Duct with integrated baffle
FR2890156A1 (en) * 2005-08-31 2007-03-02 Snecma Turbomachine e.g. aircraft turbojet, combustion chamber, has internal and external flanges with orifices of triangular shape, where successive triangular orifices are arranged in staggered and head-to-tail configuration
US7909570B2 (en) * 2006-08-25 2011-03-22 Pratt & Whitney Canada Corp. Interturbine duct with integrated baffle and seal
FR2913051B1 (en) * 2007-02-28 2011-06-10 Snecma TURBINE STAGE IN A TURBOMACHINE
US8511089B2 (en) * 2009-07-31 2013-08-20 Rolls-Royce Corporation Relief slot for combustion liner
EP2397762A1 (en) * 2010-06-17 2011-12-21 Siemens Aktiengesellschaft Damping device for damping pressure oscillations within a combustion chamber of a turbine
DE102015212573A1 (en) * 2015-07-06 2017-01-12 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine combustor with integrated turbine guide wheel and method for its production

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2702987A (en) * 1952-06-11 1955-03-01 Nicolin Curt Rene Expansible element for connecting pipes of different diameters
GB1578474A (en) * 1976-06-21 1980-11-05 Gen Electric Combustor mounting arrangement
EP0519861A1 (en) * 1991-06-21 1992-12-23 Pratt & Whitney Canada, Inc. Annular support
EP0521687A1 (en) * 1991-07-01 1993-01-07 General Electric Company Combustor dome assembly
US5323605A (en) * 1990-10-01 1994-06-28 General Electric Company Double dome arched combustor
DE19600837A1 (en) * 1996-01-12 1997-07-17 Bmw Rolls Royce Gmbh Axially stepped annular combustion chamber for aircraft gas turbine

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3670497A (en) * 1970-09-02 1972-06-20 United Aircraft Corp Combustion chamber support
FR2402068A1 (en) * 1977-09-02 1979-03-30 Snecma ANTI-POLLUTION COMBUSTION CHAMBER
US4191011A (en) * 1977-12-21 1980-03-04 General Motors Corporation Mount assembly for porous transition panel at annular combustor outlet
US4483149A (en) * 1982-05-20 1984-11-20 United Technologies Corporation Diffuser case for a gas turbine engine
CA2089302C (en) * 1992-03-30 2004-07-06 Joseph Frank Savelli Double annular combustor
US5333443A (en) * 1993-02-08 1994-08-02 General Electric Company Seal assembly
FR2723177B1 (en) * 1994-07-27 1996-09-06 Snecma COMBUSTION CHAMBER COMPRISING A DOUBLE WALL
US5619855A (en) * 1995-06-07 1997-04-15 General Electric Company High inlet mach combustor for gas turbine engine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2702987A (en) * 1952-06-11 1955-03-01 Nicolin Curt Rene Expansible element for connecting pipes of different diameters
GB1578474A (en) * 1976-06-21 1980-11-05 Gen Electric Combustor mounting arrangement
US5323605A (en) * 1990-10-01 1994-06-28 General Electric Company Double dome arched combustor
EP0519861A1 (en) * 1991-06-21 1992-12-23 Pratt & Whitney Canada, Inc. Annular support
EP0521687A1 (en) * 1991-07-01 1993-01-07 General Electric Company Combustor dome assembly
DE19600837A1 (en) * 1996-01-12 1997-07-17 Bmw Rolls Royce Gmbh Axially stepped annular combustion chamber for aircraft gas turbine

Also Published As

Publication number Publication date
EP0909924B1 (en) 2003-07-16
EP0909924A2 (en) 1999-04-21
DE59809015D1 (en) 2003-08-21
DE19745683A1 (en) 1999-04-22
US6131384A (en) 2000-10-17

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