US20220074595A1 - Turbomachine combustion chamber - Google Patents
Turbomachine combustion chamber Download PDFInfo
- Publication number
- US20220074595A1 US20220074595A1 US17/416,956 US201917416956A US2022074595A1 US 20220074595 A1 US20220074595 A1 US 20220074595A1 US 201917416956 A US201917416956 A US 201917416956A US 2022074595 A1 US2022074595 A1 US 2022074595A1
- Authority
- US
- United States
- Prior art keywords
- connection
- peripheral tube
- turbine engine
- wall
- tube
- 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.)
- Abandoned
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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
- F23R3/48—Flame tube interconnectors, e.g. cross-over tubes
-
- 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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- 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
- F23R3/002—Wall structures
-
- 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
- F23R3/005—Combined with pressure or heat exchangers
-
- 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
- F23R3/54—Reverse-flow combustion chambers
-
- 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
- F23R2900/00001—Arrangements using bellows, e.g. to adjust volumes or reduce thermal stresses
Definitions
- the present disclosure relates to the field of regenerative-cycle turbines intended, in particular, for the on-board production of electrical or mechanical energy from fuels for aeronautical, terrestrial, and maritime vehicles, and lightweight mobile units.
- a turbine is made up of three elements:
- the exhaust gases emerge from the turbine at high temperatures (greater than 500° C.), while the temperature of the air emerging from the compressor is lower (typically between 200° C. and 400° C.), having a circulation through a heat exchanger inserted between the exhaust gases and the compressed air, which makes it possible to partially reheat the air before it enters the combustion chamber, making it possible to reduce the fuel consumption.
- the present disclosure relates more particularly to the combustion chamber and the injection of fuel into the combustion chamber.
- German patent DE1254911 proposes injection nozzles in the form of hooks, mounted in the body of the injection nozzle, which is fixed in the flame holder by the nozzle tip thereof, so as to be displaceable with respect to the walls of the combustion chamber.
- the external part of the body of the injection nozzle in the form of a hook, is slidably mounted in a guide, optionally associated with the exterior wall of the combustion chamber, and a clamping device, directed in parallel with the mouthpiece of the nozzle is provided for keeping the front end of the mouthpiece against a stop fixed to a hub of the flame holder.
- British patent GB2097112 describes a fuel burner for a gas turbine engine, comprising a fuel feed arm and a fuel injector, the fuel feed arm and the fuel injector being joined together, the fuel feed arm having at least one fuel passage, the fuel injector 65 comprising a body having a passage in communication with the at least one fuel passage in the fuel feed arm, the body having an air duct, the axis of the air duct being coaxial with the axis of the fuel injector, the fuel injector having one or more 70 fuel passages to inject fuel into the air duct, the fuel burner having locating means at the end adjacent to the fuel injector, the locating means being arranged to engage with corresponding locating means on an engine component.
- the problem posed by the solutions of the prior art relates to the turbines having a combustion chamber that is insulated from the outside by a double wall, two walls defining an annular channel for the circulation of a flow of compressed air originating from the compressor, and the third wall being the exterior wall of the combustion chamber, allowing for the circulation of the same air flow, previously reheated upon crossing a heat exchanger.
- the injector or injectors must cross the three walls in a sealed manner, or at least in a manner having controlled leakage. This results in hyperstatic mounting, which does not allow for absorption of the longitudinal thermal expansions of the injector, or the radial and longitudinal thermal expansions of the metal walls exposed to extremely different temperatures.
- the injector passes through the walls of the combustion chamber via simple holes, references 38 , 48 and 52 .
- This document proposes positioning the injector coaxially inside each of the coaxial holes 52 , 48 and 38 provided in the housing 50 .
- This solution thus results in several disadvantages: the radial expansion of the injector is different from the surface expansion of the walls, resulting either in leaks between the periphery of the injector and the edge of the through-holes in the wall, or in clamping of the edges of the holes around the wall of the injector, which limits the radial displacement possibilities and may lead to deformations and to fatigue of the walls.
- the present disclosure relates to a combustion chamber of a turbine engine, surrounded by two coaxial axisymmetric walls, extending one inside the other and delimiting therebetween an annular air-circulation space, and a second air-circulation space delimited by the axisymmetric wall of smaller diameter and the exterior wall of the combustion chamber, and at least one injector that crosses the walls via ports, wherein the injector comprises a peripheral tube that is connected to the walls by three connections, at least two connections being flexible sealed connections allowing for multidirectional clearance, for example, of the slide type and/or of the ball joint type, or of the bellows type.
- bellows means a sealed casing that can be deformed at least axially and radially, and optionally in a torsional or tilting manner.
- the present disclosure also relates to a turbine comprising a combustion chamber of this kind.
- FIG. 1 is a cross section of a turbine engine according to the present disclosure.
- FIGS. 2 to 8 are schematic views of different variants.
- FIG. 1 is a perspective view of the turbine engine, comprising a heat exchanger ( 1 ), a compressor ( 2 ), a combustion chamber ( 3 ), and a turbine ( 4 ).
- a conical deflector ( 11 ) which is coaxial with the heat exchanger ( 1 ), causes the hot gases, originating from the turbine ( 4 ), to circulate towards a discharge outlet ( 12 ) after having passed through the heat exchanger ( 1 ), passing through two cassettes ( 5 , 6 ) between the tubes.
- the parts formed by the compressor ( 2 ), the combustion chamber ( 3 ) and the turbine ( 4 ) are known to a person skilled in the art, and are in accordance with the state of knowledge in the field of turbine engines.
- the heat exchanger ( 1 ) is formed by a tube heat exchanger, comprising two coaxial annular cassettes ( 5 , 6 ).
- the external cassette ( 5 ) is formed by an assembly of parallel tubes, made of a metal alloy that is resistant to high temperatures, for example, refractory stainless steel 347.
- the external cassette ( 5 ) is formed of 2000 tubes having a length of 300 millimeters, an internal cross-section of 2.8 millimeters, and an external cross-section of 3 millimeters.
- the tubes are held in a known manner by means of inserts for defining the passages of hot gases originating from the turbine.
- the tubes form a sleeve having an external radius of 158 millimeters and an internal radius of 128 millimeters.
- the internal cassette ( 6 ) is formed of 2000 tubes having a length of 300 millimeters, an internal cross-section of 2.8 millimeters, and an external cross-section of 3 millimeters.
- the tubes form a sleeve having an external radius of 123 millimeters and an internal radius of 67 millimeters.
- the two cassettes ( 5 , 6 ) are coaxial and are fitted into one another.
- the two cassettes ( 5 , 6 ) are united, at the end opposite the compressor ( 2 ), by an annular closure structure ( 8 ).
- Each of the cassettes ( 5 , 6 ) comprises, at each end, a front sealing plate that is pierced for the tubes to pass through, and ensures the constant center distance of the tubes.
- the tubes are brazed or soldered in order to ensure sealing in the region of the connection thereof to the front plates.
- the closure structure ( 8 ) is formed of two coaxial parts that are fitted together and have the general shape of a rum baba mold, which parts are made of refractory stainless steel 347 of a thickness of 2 millimeters.
- the outer part ( 9 ) has an external cross section that corresponds to the external cross section of the external cassette ( 5 ), and an internal cross section that corresponds to the internal cross section of the internal cassette ( 6 ).
- the inner part ( 10 ) has an external cross section that corresponds to the internal cross section of the external cassette ( 5 ), and an internal cross section that corresponds to the external cross section of the internal cassette ( 6 ).
- Each of the parts ( 9 , 10 ) is rotationally symmetric according to the axis of the turbine engine, having a constant longitudinal cross section.
- the closure structure ( 8 ) ensures the deflection of the gases, originating from the external cassette ( 5 ), towards the tubes that make up the internal cassette ( 6 ).
- This solution ensures a double passage of the gases in the heat exchanger ( 1 ), which significantly increases the thermal efficiency thereof for a given bulk, and, in particular, length.
- the combustion chamber ( 3 ) of the annular type has a double interior casing formed by a sheath ( 30 ) (“liner”) and an intermediate wall ( 31 ).
- the liner ( 30 ) and the intermediate wall ( 31 ) define a tubular volume for circulation of the air flow originating from the heat exchanger ( 1 ).
- An exterior wall ( 32 ) and the intermediate wall ( 31 ) define a tubular volume for circulation of the air flow originating from the compressor ( 2 ) and travelling towards the heat exchanger ( 1 ).
- the tube ( 35 ) of the injector passes through the three walls ( 30 to 32 ) via three ports.
- the walls ( 30 to 32 ) as well as the tube ( 35 ) of the injector are subjected to longitudinal and radial expansions. The fixing is ensured by a combination of connections, avoiding the hyperstatic situations.
- connection between the tube ( 35 ) of the injector and the interior wall ( 30 ) is ensured by a sliding connection formed by a calibrated port defining, together with the outside surface of the tube ( 35 ), a calibrated annular clearance.
- connection between the tube ( 35 ) of the injector and the intermediate wall ( 31 ) is ensured by a fixed connection.
- the first variant is illustrated schematically by FIG. 2 .
- the tube ( 35 ) of the injector passes through the three walls ( 30 to 32 ) having the respective connections:
- the second variant is illustrated schematically by FIG. 3 .
- the tube ( 35 ) of the injector passes through the three walls ( 30 to 32 ) having the respective connections:
- the third variant is illustrated schematically by FIG. 4 .
- the tube ( 35 ) of the injector passes through the three walls ( 30 to 32 ) having the respective connections:
- the fourth variant is illustrated schematically by FIG. 5 .
- the tube ( 35 ) of the injector passes through the three walls ( 30 to 32 ) having the respective connections:
- the fifth variant is illustrated schematically by FIGS. 6 to 8 .
- the tube ( 35 ) of the injector passes through the three walls ( 30 to 32 ) having the respective connections:
- connection between the peripheral tube ( 35 ) and the intermediate wall ( 31 ) of the liner is formed by a connection ( 80 ) having several degrees of freedom for allowing axial displacement and tangential displacement of the tube, and a tolerance for a ball joint.
- connection between the peripheral tube ( 35 ) and the exterior wall ( 32 ) of the liner is formed by a sealed rigid assembly.
- the head ( 38 ) comprises a discal flange ( 38 ) that is engaged between the two parts of the gland ( 37 ), which ensures clamping and sealing of the discal flange ( 38 ).
- the inside end ( 40 ) passes through the interior wall ( 30 ), via passage in a simple hole formed in the interior wall ( 30 ).
- the hole is oblong in this case, in order to take into account the inclination of the axis of the nozzle ( 35 ) with respect to the radial axis.
- connection between the nozzle ( 35 ) and the intermediate wall ( 31 ) is achieved by a part having a conical upper portion ( 41 ) that is flared towards the outside and is extended at the base thereof by a discal flange ( 42 ) that is movable in radial translation in a slit ( 42 ) formed in the head ( 44 ) of a tubular extension ( 43 ) soldered to the surface of the interior wall ( 30 ).
- the discal flange ( 42 ) is flexible, which furthermore allows for a lightweight ball joint with respect to the tubular extension ( 43 ).
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Fuel-Injection Apparatus (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Joints Allowing Movement (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1874016A FR3090747B1 (fr) | 2018-12-21 | 2018-12-21 | Chambre de combustion d'une turbomachine |
FR1874016 | 2018-12-21 | ||
PCT/FR2019/053108 WO2020128292A1 (fr) | 2018-12-21 | 2019-12-17 | Chambre de combustion d'une turbomachine |
Publications (1)
Publication Number | Publication Date |
---|---|
US20220074595A1 true US20220074595A1 (en) | 2022-03-10 |
Family
ID=67441198
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US17/416,956 Abandoned US20220074595A1 (en) | 2018-12-21 | 2019-12-17 | Turbomachine combustion chamber |
Country Status (6)
Country | Link |
---|---|
US (1) | US20220074595A1 (de) |
EP (1) | EP3899371B1 (de) |
CN (1) | CN113454390B (de) |
CA (1) | CA3124209A1 (de) |
FR (1) | FR3090747B1 (de) |
WO (1) | WO2020128292A1 (de) |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4441323A (en) * | 1981-04-16 | 1984-04-10 | Rolls-Royce Limited | Combustion equipment for a gas turbine engine including a fuel burner capable of accurate positioning and installation as a unit in a flame tube |
Family Cites Families (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB859805A (en) * | 1958-07-21 | 1961-01-25 | Gen Motors Corp | Improvements relating to gas turbine engine combustion systems |
DE1254911B (de) * | 1965-09-23 | 1967-11-23 | Daimler Benz Ag | Anordnung des Einspritzduesenkoerpers an bzw. in der Brennkammer von Gasturbinentriebwerken |
GB2093584B (en) * | 1981-02-21 | 1984-12-19 | Rolls Royce | Improvements in or relating to fuel burners and combustion equipment for use in gas turbine engines |
US4903476A (en) * | 1988-12-27 | 1990-02-27 | General Electric Company | Gas turbine igniter with ball-joint support |
US5966926A (en) | 1997-05-28 | 1999-10-19 | Capstone Turbine Corporation | Liquid fuel injector purge system |
US6438940B1 (en) * | 1999-12-21 | 2002-08-27 | General Electric Company | Methods and apparatus for providing uniform ignition in an augmenter |
US6438936B1 (en) | 2000-05-16 | 2002-08-27 | Elliott Energy Systems, Inc. | Recuperator for use with turbine/turbo-alternator |
US6442929B1 (en) * | 2001-06-04 | 2002-09-03 | Power Systems Mfg., Llc | Igniter assembly having spring biasing of a semi-hemispherical mount |
US7024863B2 (en) * | 2003-07-08 | 2006-04-11 | Pratt & Whitney Canada Corp. | Combustor attachment with rotational joint |
GB2433984B (en) * | 2006-01-04 | 2007-11-21 | Rolls Royce Plc | A combustor assembly |
FR2921463B1 (fr) * | 2007-09-26 | 2013-12-06 | Snecma | Chambre de combustion d'une turbomachine |
EP2726787B1 (de) | 2011-06-30 | 2019-10-30 | General Electric Company | Brennkammer und verfahren zur brennstoffversorgung der brennkammer |
US9032735B2 (en) * | 2012-04-26 | 2015-05-19 | General Electric Company | Combustor and a method for assembling the combustor |
FR3000522B1 (fr) * | 2012-12-27 | 2018-11-02 | Safran Aircraft Engines | Dispositif de liaison a double tube |
US9803555B2 (en) | 2014-04-23 | 2017-10-31 | General Electric Company | Fuel delivery system with moveably attached fuel tube |
US9803863B2 (en) * | 2015-05-13 | 2017-10-31 | Solar Turbines Incorporated | Controlled-leak combustor grommet |
FR3038699B1 (fr) * | 2015-07-08 | 2022-06-24 | Snecma | Chambre de combustion coudee d'une turbomachine |
GB2543803B (en) * | 2015-10-29 | 2019-10-30 | Rolls Royce Plc | A combustion chamber assembly |
GB2548585B (en) * | 2016-03-22 | 2020-05-27 | Rolls Royce Plc | A combustion chamber assembly |
FR3059363B1 (fr) | 2016-11-25 | 2019-04-05 | Turbotech | Turbomachine, notamment turbogenerateur et echangeur pour une telle turbomachine |
-
2018
- 2018-12-21 FR FR1874016A patent/FR3090747B1/fr active Active
-
2019
- 2019-12-17 WO PCT/FR2019/053108 patent/WO2020128292A1/fr unknown
- 2019-12-17 CN CN201980091938.XA patent/CN113454390B/zh active Active
- 2019-12-17 EP EP19845596.6A patent/EP3899371B1/de active Active
- 2019-12-17 US US17/416,956 patent/US20220074595A1/en not_active Abandoned
- 2019-12-17 CA CA3124209A patent/CA3124209A1/fr active Pending
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4441323A (en) * | 1981-04-16 | 1984-04-10 | Rolls-Royce Limited | Combustion equipment for a gas turbine engine including a fuel burner capable of accurate positioning and installation as a unit in a flame tube |
Also Published As
Publication number | Publication date |
---|---|
CA3124209A1 (fr) | 2020-06-25 |
FR3090747A1 (fr) | 2020-06-26 |
WO2020128292A1 (fr) | 2020-06-25 |
CN113454390B (zh) | 2023-02-24 |
FR3090747B1 (fr) | 2021-01-22 |
EP3899371C0 (de) | 2024-02-07 |
EP3899371B1 (de) | 2024-02-07 |
EP3899371A1 (de) | 2021-10-27 |
CN113454390A (zh) | 2021-09-28 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP3431878B1 (de) | Kraftstoffdüsen | |
US8181440B2 (en) | Arrangement of a semiconductor-type igniter plug in a gas turbine engine combustion chamber | |
US10197285B2 (en) | Gas turbine engine wall assembly interface | |
US2958183A (en) | Rocket combustion chamber | |
EP3220047B1 (de) | Gasturbinenstromhülsenhalterung | |
EP3039347B1 (de) | Wandanordnung für gasturbinenmotor mit stützschalenkonturregionen | |
US10088161B2 (en) | Gas turbine engine wall assembly with circumferential rail stud architecture | |
RU2696158C2 (ru) | Теплоизолированная топливная форсунка для газотурбинного двигателя | |
CN102607064A (zh) | 燃烧室喷嘴及制造燃烧室喷嘴的方法 | |
US8752389B2 (en) | Fuel nozzle assembly for use with a gas turbine engine and method of assembling same | |
US10808937B2 (en) | Gas turbine engine wall assembly with offset rail | |
JP2020514657A (ja) | マイクロチャネル冷却を備えた燃料ノズル組立体 | |
US20150176841A1 (en) | Apparatus for mixing fuel in a gas turbine nozzle | |
US10174946B2 (en) | Nozzle guide for a combustor of a gas turbine engine | |
US7287383B2 (en) | Afterburner arrangement | |
US20220074595A1 (en) | Turbomachine combustion chamber | |
CN214247529U (zh) | 航空发动机核心机尾喷管以及航空发动机核心机 | |
CN115949968A (zh) | 燃烧器旋流器到伪圆顶附接以及与cmc圆顶接口 | |
CN108870444A (zh) | 燃气涡轮发动机的燃烧器组件 | |
US10982856B2 (en) | Fuel nozzle with sleeves for thermal protection | |
JPH01131821A (ja) | ガスタービン燃焼器の支承構造 | |
JP2009192195A (ja) | ガスタービンエンジンの燃焼装置 | |
EP4339513A2 (de) | Brennkammeranordnung | |
US20240093869A1 (en) | Fuel nozzle | |
CN116379474B (zh) | 一种航空发动机燃油喷嘴热防护结构 |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: TURBOTECH, FRANCE Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:FAUVET, DAMIEN;NGUYEN, MARC;GUERIN, BAPTISTE;AND OTHERS;REEL/FRAME:057549/0675 Effective date: 20210901 |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: DOCKETED NEW CASE - READY FOR EXAMINATION |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: NON FINAL ACTION MAILED |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: RESPONSE TO NON-FINAL OFFICE ACTION ENTERED AND FORWARDED TO EXAMINER |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: FINAL REJECTION MAILED |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |