EP1265032B1 - Architecture de chambre de combustion de turbomachine en matériau à matrice céramique - Google Patents
Architecture de chambre de combustion de turbomachine en matériau à matrice céramique Download PDFInfo
- Publication number
- EP1265032B1 EP1265032B1 EP02291361A EP02291361A EP1265032B1 EP 1265032 B1 EP1265032 B1 EP 1265032B1 EP 02291361 A EP02291361 A EP 02291361A EP 02291361 A EP02291361 A EP 02291361A EP 1265032 B1 EP1265032 B1 EP 1265032B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- flange
- nozzle
- shell
- turbomachine according
- 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.)
- Expired - Lifetime
Links
Images
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
- F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
-
- 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
- F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
-
- 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
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M2900/00—Special features of, or arrangements for combustion chambers
- F23M2900/05002—Means for accommodate thermal expansion of the wall liner
Definitions
- the present invention relates to the field of turbomachines and more particularly it relates to the interface between the high pressure turbine and the combustion chamber of turbojets having a combustion chamber CMC (ceramic matrix composite).
- CMC ceramic matrix composite
- the high pressure turbine including its inlet distributor (HPT nozzle), the combustion chamber as well as the casing (also called envelope) of this room are made in a same material, usually of metal type.
- HPT nozzle inlet distributor
- the combustion chamber as well as the casing (also called envelope) of this room are made in a same material, usually of metal type.
- CMC-type high temperature composite materials as shown in US-A-5,291,732.
- difficulties of implementation of these materials and their cost make that their use is most often limited to the combustion chamber itself, the distributor inlet of the high pressure turbine and the remaining housing then made more typically in metallic materials.
- metallic materials and Composite materials have very different coefficients of thermal expansion. This results in particularly acute interface problems at the level of the distributor, inlet of the high pressure turbine, and connection with the housing of the bedroom.
- the present invention overcomes these disadvantages by proposing a connection crankcase with the capacity to absorb the displacements induced by differences in the expansion coefficients of these parts.
- An object of the invention is also to propose a structure of simple form and whose manufacture is particularly easy.
- a turbomachine comprising, in a envelope of metallic material and in a direction F of gas flow, a fuel injection assembly, combustion chamber made of material composite and a metal material distributor forming the entrance stage to vanes of a high-pressure turbine, and said distributor being supported by said envelope and fixed thereto by first removable fixing means, characterized in that said combustion chamber is mounted floating in said envelope and held in position by the only said distributor to which it is resiliently secured by second removable attachment means.
- the first removable fastening means are adapted to allow radial free expansion of said dispenser with respect to said envelope.
- said second means of removable fasteners comprise on the one hand first holding means for pinch an end internal axial wall of said chamber of combustion between an internal circular platform of the dispenser and a flange supporting an inner annular wall of said envelope and second holding means for holding a wall with elastic prestressing external axial end of said combustion chamber on a platform external circular of the distributor.
- the support flange is sectorised to compensate for the differences circumferential geometries resulting from the existing differential expansion at high temperatures between said inner circular distributor platform and said inner axial wall of the combustion chamber.
- This support flange is mounted between a flange of said inner annular wall of the envelope and a ferrule made of metallic material held against this flange by said first removable fastening means.
- said first removable fastening means have a plurality of bolts, each of which has screw axes running through a corresponding oblong hole of said support flange is provided with a shoulder on which is pressed against said ferrule so as to allow sliding of said support flange between said ferrule and said flange of the inner annular wall of the envelope.
- said flange of the wall inner ring of the envelope has a circular groove for receiving a "omega" type circular sealing gasket intended to seal between said flange of the inner annular wall of the casing and said support flange.
- a composite material shell advantageously brazed to said outer end wall of the combustion chamber is maintained with a elastic prestress against said external circular distributor platform by the second holding means, said ferrule having a groove to receive an omega-type circular seal intended for sealing between said outer end wall of the chamber of combustion and said outer circular platform of the dispenser.
- this space 16 comprising, in the direction of gas flow, firstly an injection assembly formed of a plurality of injection systems 20 and regularly distributed around the duct 18 and each having a nozzle fuel injection device 22 fixed to the outer annular casing 12 (in a simplification of the drawings the mixer and the baffle associated with each injection nozzle were not shown), then a combustion chamber in high temperature composite material 24, CMC type or other (carbon by example), formed of an outer axial wall 26 and an inner axial wall 28, both coaxial axis 10, and a transverse wall 30 which constitutes the bottom of this combustion chamber and which has flaps 32, 34 fixed by all suitable means, for example metal or refractory bolts with screws conical), on the upstream ends 36, 38 of the axial walls 26, 28, this bottom of the chamber 30 being provided with orifices 40 to allow fuel injection and part of the oxidant in the combustion chamber 24, and finally a annular distributor 42 in metallic material forming an input stage of a high pressure turbine (not shown) and conventionally comprising a plurality of fixed vanes 44
- the combustion chamber is mounted floating in the annular envelope and held in position by the only distributor to which it is resiliently secured by second removable attachment means which comprise on the one hand first holding means 52 for holding by pinching an end internal axial wall 54 of the combustion chamber (opposite the upstream end 38) between the inner circular platform of the distributor 48 and a flange 56 serving to support the inner annular envelope 14 and second holding means 58 for holding with prestressing elastic 60 an end outer axial wall 62 of said chamber of combustion (opposite the upstream end 36) on the outer circular platform of the dispenser 46.
- the support flange 56 is mounted between a flange 64 of the inner annular casing 14 and a ferrule made of metallic material 66 held against this flange by the first removable fastening means 50.
- Through orifices 68, 70 for the passage of the compressed oxidant previously separated, at the outlet of the diffusion duct 18, in at least two streams F1, F2 separate flowing from both sides of the combustion chamber 24 (and notably ensuring its cooling), are provided in the platforms external metal 46 and internal 48 of the distributor 42 to ensure a cooling the vanes fixed 44 of the distributor at the inlet of the rotor of the turbine high pressure.
- the combustion chamber 24 having a coefficient of thermal expansion very different from other metal parts forming the turbomachine, in particular the dispenser 42 to which it is attached and the annular casing 12, 14, it is provided that the first removable fixing means 50 are adapted to allow at high temperatures radial free expansion of the dispenser with respect to the annular envelope.
- the support flange 56 is pierced with holes oblongs 72 for cooperating with the screw axes of the plurality of bolts 50 a shoulder 74 serves to support the ferrule 66 so as to allow a sliding of this support flange between the ferrule and the flange 64 of the envelope 14.
- this flange is sectorised to compensate for differences circumferential geometries resulting from the differential expansion existing at these high temperatures between the inner circular platform 48 of the dispenser and the internal axial wall 28, 54 of the combustion chamber.
- the flange of the inner annular casing 64 comprises a circular groove 76 for receiving a circular seal of type "Omega" 78 for sealing between this flange of the envelope ring and the support flange 56.
- the outer circular platform distributor 46 comprises a flange 80 provided with a circular groove 82 for receive a plate seal 84, one end of which will come into contact with the outer annular casing 12 to seal against the flow F1.
- the seal between the combustion chamber 24 and the distributor 42 it is provided between the outer end wall of the combustion chamber 62 and the outer circular platform of the distributor 46 also by means of a omega-type seal ring 86 mounted in a groove circular 88 of a shell of composite material 90, preferably brazed on the outer end wall of the combustion chamber 62, and maintained with an elastic prestress (obtained for example by the spring 60) against the platform external circular distributor 46 by the second holding means 58.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0107360 | 2001-06-06 | ||
FR0107360A FR2825780B1 (fr) | 2001-06-06 | 2001-06-06 | Architecure de chambre de combustion de turbomachine en materiau a matrice ceramique |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1265032A1 EP1265032A1 (fr) | 2002-12-11 |
EP1265032B1 true EP1265032B1 (fr) | 2004-10-06 |
Family
ID=8863984
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP02291361A Expired - Lifetime EP1265032B1 (fr) | 2001-06-06 | 2002-06-04 | Architecture de chambre de combustion de turbomachine en matériau à matrice céramique |
Country Status (5)
Country | Link |
---|---|
US (1) | US6679062B2 (ja) |
EP (1) | EP1265032B1 (ja) |
JP (1) | JP3983603B2 (ja) |
DE (1) | DE60201467T2 (ja) |
FR (1) | FR2825780B1 (ja) |
Families Citing this family (27)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
US6895761B2 (en) * | 2002-12-20 | 2005-05-24 | General Electric Company | Mounting assembly for the aft end of a ceramic matrix composite liner in a gas turbine engine combustor |
US7152411B2 (en) * | 2003-06-27 | 2006-12-26 | General Electric Company | Rabbet mounted combuster |
FR2871844B1 (fr) * | 2004-06-17 | 2006-09-29 | Snecma Moteurs Sa | Montage etanche d'un distributeur de turbine haute pression sur une extremite d'une chambre de combustion dans une turbine a gaz |
FR2871846B1 (fr) * | 2004-06-17 | 2006-09-29 | Snecma Moteurs Sa | Chambre de combustion en cmc de turbine a gaz supportee dans un carter metallique par des organes de liaison en cmc |
FR2871847B1 (fr) * | 2004-06-17 | 2006-09-29 | Snecma Moteurs Sa | Montage d'un distributeur de turbine sur une chambre de combustion a parois en cmc dans une turbine a gaz |
FR2871845B1 (fr) * | 2004-06-17 | 2009-06-26 | Snecma Moteurs Sa | Montage de chambre de combustion de turbine a gaz avec distributeur integre de turbine haute pression |
US7647779B2 (en) * | 2005-04-27 | 2010-01-19 | United Technologies Corporation | Compliant metal support for ceramic combustor liner in a gas turbine engine |
US20070134087A1 (en) * | 2005-12-08 | 2007-06-14 | General Electric Company | Methods and apparatus for assembling turbine engines |
US8038389B2 (en) * | 2006-01-04 | 2011-10-18 | General Electric Company | Method and apparatus for assembling turbine nozzle assembly |
EP1843009A1 (de) | 2006-04-06 | 2007-10-10 | Siemens Aktiengesellschaft | Leitschaufelsegment einer thermischen Strömungsmaschine, zugehöriges Herstellungsverfahren sowie thermische Strömungsmaschine |
FR2906350B1 (fr) * | 2006-09-22 | 2009-03-20 | Snecma Sa | Chambre de combustion annulaire d'une turbomachine |
DE102006060857B4 (de) | 2006-12-22 | 2014-02-13 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | CMC-Brennkammerauskleidung in Doppelschichtbauweise |
EP1985806A1 (en) * | 2007-04-27 | 2008-10-29 | Siemens Aktiengesellschaft | Platform cooling of a turbine vane |
US8745989B2 (en) * | 2009-04-09 | 2014-06-10 | Pratt & Whitney Canada Corp. | Reverse flow ceramic matrix composite combustor |
US8226361B2 (en) * | 2009-07-08 | 2012-07-24 | General Electric Company | Composite article and support frame assembly |
US8206096B2 (en) * | 2009-07-08 | 2012-06-26 | General Electric Company | Composite turbine nozzle |
US9234431B2 (en) * | 2010-07-20 | 2016-01-12 | Siemens Energy, Inc. | Seal assembly for controlling fluid flow |
FR2963061B1 (fr) * | 2010-07-26 | 2012-07-27 | Snecma | Systeme d?injection de carburant pour turbo-reacteur et procede d?assemblage d?un tel systeme d?injection |
US10059431B2 (en) | 2011-06-09 | 2018-08-28 | United Technologies Corporation | Method and apparatus for attaching components having dissimilar rates of thermal expansion |
US9290261B2 (en) | 2011-06-09 | 2016-03-22 | United Technologies Corporation | Method and assembly for attaching components |
US9335051B2 (en) * | 2011-07-13 | 2016-05-10 | United Technologies Corporation | Ceramic matrix composite combustor vane ring assembly |
US9435266B2 (en) | 2013-03-15 | 2016-09-06 | Rolls-Royce North American Technologies, Inc. | Seals for a gas turbine engine |
GB201315871D0 (en) * | 2013-09-06 | 2013-10-23 | Rolls Royce Plc | A combustion chamber arrangement |
EP3236155B1 (en) * | 2016-04-22 | 2020-05-06 | Rolls-Royce plc | Combustion chamber with segmented wall |
US10495001B2 (en) * | 2017-06-15 | 2019-12-03 | General Electric Company | Combustion section heat transfer system for a propulsion system |
US11708765B1 (en) | 2022-05-13 | 2023-07-25 | Raytheon Technologies Corporation | Gas turbine engine article with branched flange |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3775975A (en) * | 1972-09-05 | 1973-12-04 | Gen Electric | Fuel distribution system |
US4912922A (en) * | 1972-12-19 | 1990-04-03 | General Electric Company | Combustion chamber construction |
US3965066A (en) * | 1974-03-15 | 1976-06-22 | General Electric Company | Combustor-turbine nozzle interconnection |
US5335502A (en) * | 1992-09-09 | 1994-08-09 | General Electric Company | Arched combustor |
US5291732A (en) * | 1993-02-08 | 1994-03-08 | General Electric Company | Combustor liner support assembly |
US6397603B1 (en) * | 2000-05-05 | 2002-06-04 | The United States Of America As Represented By The Secretary Of The Air Force | Conbustor having a ceramic matrix composite liner |
-
2001
- 2001-06-06 FR FR0107360A patent/FR2825780B1/fr not_active Expired - Fee Related
-
2002
- 2002-05-30 JP JP2002156754A patent/JP3983603B2/ja not_active Expired - Lifetime
- 2002-06-04 EP EP02291361A patent/EP1265032B1/fr not_active Expired - Lifetime
- 2002-06-04 DE DE60201467T patent/DE60201467T2/de not_active Expired - Lifetime
- 2002-06-05 US US10/162,384 patent/US6679062B2/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
DE60201467D1 (de) | 2004-11-11 |
EP1265032A1 (fr) | 2002-12-11 |
JP3983603B2 (ja) | 2007-09-26 |
US20020184891A1 (en) | 2002-12-12 |
US6679062B2 (en) | 2004-01-20 |
JP2003035104A (ja) | 2003-02-07 |
DE60201467T2 (de) | 2006-03-09 |
FR2825780A1 (fr) | 2002-12-13 |
FR2825780B1 (fr) | 2003-08-29 |
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