EP0909924A2 - Suspension d'une chambre de combustion annulaire de turbine à gaz - Google Patents

Suspension d'une chambre de combustion annulaire de turbine à gaz Download PDF

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Publication number
EP0909924A2
EP0909924A2 EP98117869A EP98117869A EP0909924A2 EP 0909924 A2 EP0909924 A2 EP 0909924A2 EP 98117869 A EP98117869 A EP 98117869A EP 98117869 A EP98117869 A EP 98117869A EP 0909924 A2 EP0909924 A2 EP 0909924A2
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
gas turbine
suspension
annular gas
circumference
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)
English (en)
Other versions
EP0909924A3 (fr
EP0909924B1 (fr
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
BMW Rolls Royce GmbH
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, BMW Rolls Royce GmbH filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP0909924A2 publication Critical patent/EP0909924A2/fr
Publication of EP0909924A3 publication Critical patent/EP0909924A3/fr
Application granted granted Critical
Publication of EP0909924B1 publication Critical patent/EP0909924B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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

Definitions

  • the invention relates to a suspension of an annular gas turbine combustion chamber in the outlet area of the same on a housing wall, over an annular, kinked adjoining the outer combustion chamber wall trained arm structure related to the gas turbine longitudinal axis has an outer and an inner leg.
  • the state of the art is, for example, EP 0 564 172 A1 referred.
  • Annular combustion chambers of gas turbines are usually carried in their front end area by the burners projecting into the combustion chamber interior, while in the rear end area, the so-called outlet area, they are suitably supported on a housing wall, the so-called. combustion chamber outer casing ".
  • the so-called effusion holes care must be taken to ensure that the rear combustion chamber wall section is also adequately cooled Suspension of the combustion chamber in this area must therefore not hinder effective cooling.
  • a suspension or a supporting structure that meets these requirements is shown, for example, in EP 0 564 172 A1 mentioned above.
  • This ring-shaped, bent arm structure which relates to the gas turbine longitudinal axis has an inner and an outer leg, is also known in specialist circles hair-pin "(hairpin).
  • the inner leg encloses an acute angle with the outer leg, likewise the inner leg is inclined at an acute angle with respect to the combustion chamber wall, which results in a wedge-shaped annular gap between the inner leg and the combustion chamber wall, which viewed in the flow direction of the cooling air flow running along the outside of the outer combustion chamber wall. In this way, cooling air can reach the rearmost end of the combustion chamber wall in an optimal manner.
  • this combustion chamber is supported via this arm structure only on the one surrounding the combustion chamber wall Housing wall, whereas the actual attachment of the combustion chamber over the inner wall of the ring combustion chamber. This can be too undesirable large relative movements in the rear end portion of the combustion chamber.
  • a flange adjoins the outer leg (the arm structure), which flange is fixedly connected to the housing wall (surrounding the combustion chamber wall) via a releasable connecting element.
  • Reference number 1 denotes an annular combustion chamber of a gas turbine, which is designed here as a stepped combustion chamber and thus next to one
  • a plurality of ring-shaped pilot burners 2 furthermore on the end face also has annularly arranged main burners 3.
  • the combustion chamber 1 is on a housing wall 7 surrounding the entire combustion chamber structure.
  • An annular, kinked design is provided for this Arm structure 8, located on the end portion of the outer combustion chamber wall 9a connects.
  • openings 13 in the arm structure 8 or in the legs 8a, 8b are so-called openings 13 in the arm structure 8 or in the legs 8a, 8b. If these openings or openings 13 in at least one the leg 8a, 8b, but preferably suitable in both legs 8a, 8b dimensioned and arranged, the arm structure 8 acts similar to one Leaf spring with customizable spring characteristics. Best results were with the design and arrangement explained below achieved by openings 13 in the arm structure 8.
  • the openings 13 are dovetail-shaped designed and distributed equally over the circumference of both legs 8a, 8b arranged, the narrowest portions of the openings of each Kink line 10 of the arm structure 8 are facing.
  • the breakthroughs 13 open to the crease line, so that - after these openings in the outer leg 8b and in the inner leg 8a in the illustration 1, so to speak, one above the other - between each breakdown 13 in the outer leg 8b and the adjacent opening 13 there is a so-called connection gap 14 in the inner leg 8a.
  • the stepped ring combustion chamber shown here 1 the pilot burner 2 and the main burner 3 offset in the circumferential direction arranged to each other.
  • An optimal combustion chamber suspension according to the invention results when in the section plane 15 of each burner (this section plane 15 runs through the Burner 2 or 3 itself and at least through the gas turbine longitudinal axis 11) in one of the legs 8a or 8b, but preferably in both of the Leg 8a, 8b an opening 13 is provided, in this Section plane 15 also the so-called connection gap 14 comes to rest.
  • openings 13 with respect to the burners 2 it is also possible to have the openings 13 with respect to the burners 2 to be arranged offset in the circumferential direction, so that then the cutting planes 15 of the individual burners 2, 3, for example, exactly in the middle between two each other neighboring openings 13 would come to rest (not shown).
  • any other intermediate positions of the are also possible Openings 13 in the legs 8a and / or 8b with respect to the burner cutting planes 15.
  • this quotient (Number of breakthroughs) / (total number of burners) "but also assume other useful values, for example 0.5 or 1.5 but also 2 or 2.5 or 3, the integer values of this quotient taking the advantage of simple periodic ones
  • different numerical values for the quotient mentioned can be useful than in the case of stepped combustion chambers (as shown here).
  • the inner combustion chamber wall 9b has a receptacle at the end 16 for the guide vane ring adjoining the combustion chamber 1 6, so that this over the combustion chamber 1 and its advantageous Suspension is also kept in an optimal manner.

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)
EP98117869A 1997-10-16 1998-09-21 Suspension d'une chambre de combustion annulaire de turbine à gaz Expired - Lifetime EP0909924B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19745683A DE19745683A1 (de) 1997-10-16 1997-10-16 Aufhängung einer ringförmigen Gasturbinen-Brennkammer
DE19745683 1997-10-16

Publications (3)

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

Family

ID=7845693

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98117869A Expired - Lifetime EP0909924B1 (fr) 1997-10-16 1998-09-21 Suspension d'une chambre de combustion annulaire de turbine à gaz

Country Status (3)

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

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2825783B1 (fr) * 2001-06-06 2003-11-07 Snecma Moteurs Accrochage de chambre de combustion cmc de turbomachine par pattes brasees
FR2825784B1 (fr) 2001-06-06 2003-08-29 Snecma Moteurs Accrochage de chambre de combustion cmc de turbomachine utilisant les trous de dilution
FR2825785B1 (fr) 2001-06-06 2004-08-27 Snecma Moteurs Liaison de chambre de combustion cmc de turbomachine en deux parties
FR2825781B1 (fr) * 2001-06-06 2004-02-06 Snecma Moteurs Montage elastique de chambre ce combustion cmc de turbomachine dans un carter metallique
FR2825787B1 (fr) 2001-06-06 2004-08-27 Snecma Moteurs Montage de chambre de combustion cmc de turbomachine par viroles de liaison souples
FR2825782A1 (fr) * 2001-06-06 2002-12-13 Snecma Moteurs Montage flottant radial de chambre de combustion cmc de turbomachine dans un carter metallique
SE519323C2 (sv) * 2001-06-28 2003-02-11 Volvo Aero Ab Moduluppbyggd gasturbin
FR2829228B1 (fr) * 2001-08-28 2005-07-15 Snecma Moteurs Chambre de combustion annulaire a double tete etagee
FR2840974B1 (fr) * 2002-06-13 2005-12-30 Snecma Propulsion Solide Anneau d'etancheite pour cahmbre de combustion et chambre de combustion comportant un tel anneau
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 (fr) * 2005-08-31 2007-03-02 Snecma Chambre de combustion d'une turbomachine
US7909570B2 (en) * 2006-08-25 2011-03-22 Pratt & Whitney Canada Corp. Interturbine duct with integrated baffle and seal
FR2913051B1 (fr) * 2007-02-28 2011-06-10 Snecma Etage de turbine dans une turbomachine
US8511089B2 (en) * 2009-07-31 2013-08-20 Rolls-Royce Corporation Relief slot for combustion liner
EP2397762A1 (fr) * 2010-06-17 2011-12-21 Siemens Aktiengesellschaft Dispositif amortisseur pour amortir les variations de pression dans la chambre de combustion d'une turbine
DE102015212573A1 (de) * 2015-07-06 2017-01-12 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit integriertem Turbinenvorleitrad sowie Verfahren zu deren Herstellung

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0564172A1 (fr) 1992-03-30 1993-10-06 General Electric Company Chambre de combustion annulaire double

Family Cites Families (13)

* 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
US3670497A (en) * 1970-09-02 1972-06-20 United Aircraft Corp Combustion chamber support
GB1578474A (en) * 1976-06-21 1980-11-05 Gen Electric Combustor mounting arrangement
FR2402068A1 (fr) * 1977-09-02 1979-03-30 Snecma Chambre de combustion anti-pollution
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
US5323605A (en) * 1990-10-01 1994-06-28 General Electric Company Double dome arched combustor
US5161940A (en) * 1991-06-21 1992-11-10 Pratt & Whitney Canada, Inc. Annular support
CA2070518C (fr) * 1991-07-01 2001-10-02 Adrian Mark Ablett Ensemble dome pour chambre de combustion
US5333443A (en) * 1993-02-08 1994-08-02 General Electric Company Seal assembly
FR2723177B1 (fr) * 1994-07-27 1996-09-06 Snecma Chambre de combustion comportant une double paroi
DE19600837A1 (de) * 1996-01-12 1997-07-17 Bmw Rolls Royce Gmbh Axial gestufte Ring-Brennkammer einer Gasturbine
US5619855A (en) * 1995-06-07 1997-04-15 General Electric Company High inlet mach combustor for gas turbine engine

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0564172A1 (fr) 1992-03-30 1993-10-06 General Electric Company Chambre de combustion annulaire double

Also Published As

Publication number Publication date
EP0909924A3 (fr) 2000-08-02
DE59809015D1 (de) 2003-08-21
US6131384A (en) 2000-10-17
EP0909924B1 (fr) 2003-07-16
DE19745683A1 (de) 1999-04-22

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