EP3899371A1 - Chambre de combustion d'une turbomachine - Google Patents
Chambre de combustion d'une turbomachineInfo
- Publication number
- EP3899371A1 EP3899371A1 EP19845596.6A EP19845596A EP3899371A1 EP 3899371 A1 EP3899371 A1 EP 3899371A1 EP 19845596 A EP19845596 A EP 19845596A EP 3899371 A1 EP3899371 A1 EP 3899371A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- wall
- connection
- combustion chamber
- constituted
- peripheral 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.)
- Granted
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 30
- 230000002093 peripheral effect Effects 0.000 claims abstract description 28
- 238000006073 displacement reaction Methods 0.000 claims description 6
- 210000004907 gland Anatomy 0.000 claims description 4
- 239000000446 fuel Substances 0.000 description 20
- 239000003570 air Substances 0.000 description 14
- 239000007789 gas Substances 0.000 description 10
- 239000000243 solution Substances 0.000 description 5
- 238000002347 injection Methods 0.000 description 4
- 239000007924 injection Substances 0.000 description 4
- 239000002184 metal Substances 0.000 description 2
- 230000001172 regenerating effect Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 239000010935 stainless steel Substances 0.000 description 2
- 229910001220 stainless steel Inorganic materials 0.000 description 2
- 239000012080 ambient air Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 229910001092 metal group alloy Inorganic materials 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
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
- F23R3/002—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
- F23R3/28—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
- F23R3/42—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 invention relates to the field of regenerative cycle turbines intended in particular for the production of on-board electrical or mechanical energy from fuels for aeronautical, land, maritime and light mobile units.
- a turbine is made up of three elements:
- a compressor which has the role of compressing ambient air to a pressure of between 2 and 30 bars approximately;
- the exhaust gases exit the turbine at high temperatures (above 500 ° C), while the temperature of the air leaving the compressor is lower (typically between 200 ° C and 400 ° C), with circulation through a heat exchanger inserted between the exhaust gases and the compressed air, making it possible to partially reheat the air before entering the combustion chamber, thereby reducing fuel consumption.
- the invention relates more particularly to the combustion chamber and the injection of fuel into the combustion chamber.
- annular housing having a plurality of equidistant holes arranged
- annular flame tube positioned coaxially inside and spaced from said annular housing, - Said annular flame tube having a corresponding number of circumferentially equidistant holes aligned coaxially with the holes of said housing
- each tube being coaxial with the corresponding hole in the annular flame tube and the corresponding hole in the annular housing, each tube extending perpendicular to an axis of said annular flame tube, each tube having a conduit extending through it with an axis normal to the axis of the tube and parallel to the axis of said annular flame tube.
- German patent DE1254911 proposing hook-shaped injection nozzles mounted in the injection nozzle body, which is fixed in the flame holder with its nozzle tip, so as to be
- the external part of the hook-shaped injection nozzle body is slidably mounted in a guide, possibly associated with the external wall of the combustion chamber, and a clamping device directed in parallel at the mouthpiece of the nozzle is provided to hold the front end of the mouthpiece against a stop fixed in a hub of the flame holder.
- the British patent application GB2097112 describing a fuel burner for a gas turbine engine comprising a fuel supply arm and a fuel injector is known, the fuel supply arm and the fuel injector being combined, the fuel supply 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 supply 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 fuel passages for injecting 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 turbines having a combustion chamber isolated from the outside by a double wall, two walls defining an annular duct for the circulation of a flow of compressed air coming from the compressor and the third wall being the outer wall of the combustion chamber, allowing the circulation of the same flow of heated air before passing through a heat exchanger.
- the injector (s) must cross the three walls tightly or at least with a controlled leak. This results in a hyperstatic mounting which does not absorb the longitudinal thermal expansions of the injector, nor the radial and longitudinal thermal expansions of the metal walls subjected to highly differentiated temperatures.
- the present invention relates to a combustion chamber of a turbomachine, surrounded by two coaxial walls of revolution extending one inside the other and delimiting between them an annular circulation space. air, and a second air circulation space delimited by the wall of revolution of smaller diameter and the external wall of the combustion chamber, and at least one injector passing through said walls by openings, characterized in that the injector comprises a peripheral tube connected to said walls by three connections, at least two connections being watertight flexible connections allowing multidirectional travel, for example of the slide type and / or of the ball joint type or of the bellows type.
- Bellows is understood to mean, in the sense of this patent, a sealed envelope, deformable at least axially and radially, and optionally in torsion or in tilting.
- connection between said peripheral tube and the interior wall is constituted by an annular linear connection with a leak controlled by calibrating annular section
- connection between said peripheral tube and the intermediate wall is constituted by a bellows
- connection between said peripheral tube and the outer wall of the sheath is constituted by a bellows
- connection between said peripheral tube and the intermediate wall of the sheath is constituted by a ball joint and the connection between said peripheral tube and the external wall of the sheath is constituted by a sliding ball joint
- connection between said peripheral tube and the outer wall of the sleeve is constituted by a sliding ball joint and the connection between said peripheral tube and the intermediate wall of the sleeve is constituted by a ball joint.
- connection between said peripheral tube and the intermediate wall of the sleeve is constituted by a connection having several degrees of freedom to allow an axial displacement and a tangential displacement of the tube, and a tolerance for swiveling and in that the connection between said tube peripheral and the outer wall of the sheath is formed by rigid waterproof assembly.
- the invention also relates to a turbine having such a combustion chamber.
- a turbine having such a combustion chamber.
- FIG. 1 shows a sectional view of a turbomachine according to the invention
- FIG. 1 represents a perspective view of the turbomachine, comprising an exchanger (1), a compressor (2), a combustion chamber (3) and a turbine (4).
- a conical deflector (1 1) coaxial with the exchanger (1) circulates the hot gases from the turbine (4) towards a discharge outlet (12) after passing through the exchanger (2), passing through two cassettes (5, 6) between the tubes.
- the parts constituted by the compressor (2), the combustion chamber (3) and the turbine (4) are known to those skilled in the art, and comply with the state of knowledge in the field of turbomachinery.
- the exchanger (2) consists of a tube exchanger, comprising two coaxial annular cassettes (5, 6).
- the outer cassette (5) consists of an assembly of parallel tubes, made of a metal alloy resistant to high temperatures, for example refractory stainless steel 347.
- this outer cassette (5) consists of 2000 tubes with a length of 300 millimeters, an inner section of 2.8 millimeters and an outer section of 3 millimeters.
- the tubes are held in known manner by spacers to define passages for the hot gases coming from the turbine.
- the tubes form a sleeve with an outside radius of 158 millimeters and an inside radius of 128 millimeters.
- the inner cassette (6) consists of 2000 tubes with a length of 300 millimeters, an inner section of 2.8 millimeters and an outer section of 3 millimeters.
- the tubes form a sleeve with an outside radius of 123 millimeters and an inner radius of 67 millimeters.
- the two cassettes (5, 6) are coaxial and recessed one inside the other.
- Each of the cassettes (5, 6) has, at each end, a front sealing plate pierced for the passage of the tubes, and ensuring the constant spacing of the tubes.
- the tubes are brazed or welded to seal at their connection to the faceplates.
- This closure structure (8) consists of two nested coaxial parts, having the general shape of a rum baba mold, made of refractory stainless steel 347 with a thickness of 2 millimeters.
- the outer part (9) has an outer section corresponding to the outer section of the outer cassette (5) and an inner section corresponding to the inner section of the inner cassette (6).
- the interior part (10) has an exterior section corresponding to the interior section of the exterior cassette (5) and an interior section corresponding to the exterior section of the interior cassette (6).
- Each of the parts (9, 10) has a symmetry of revolution along the axis of the turbomachine, with a constant longitudinal section.
- the closure structure (8) deflects the gases from the outer cassette (5) towards the tubes constituting the inner cassette (6). This solution ensures a double passage of the gases in the exchanger (1), which significantly increases its thermal efficiency for a space requirement, and in particular a given length.
- the annular type combustion chamber (3) has an inner double envelope formed by a sheath (30) (“liner” in English ”) and a wall (31).
- the sheath (30) and the wall (31) define a tubular volume for circulation of the air flow coming from the exchanger (1).
- An outer wall (32) and the wall 31 define a tubular volume of air circulation coming from the compressor (2) and going towards the exchanger (1).
- the injector (35) passes through these three walls (30 to 32) through three slots.
- the walls (30 to 32) as well as the injector tube (35) are subjected to longitudinal and radial expansions.
- the fixation is ensured by a combination of connections avoiding hyperstatic situations.
- the connection between the injector tube (35) and the outer wall (32) is provided by a cylindrical bellows (36).
- connection between the tube (35) of the injector and the interior wall (30) is ensured by a sliding connection formed by a calibrated lumen defining with the external surface of the tube (35) a calibrated annular clearance.
- connection between the tube (35) of the injector and the intermediate wall (31) is provided by a fixed connection.
- the first variant is illustrated schematically in the figure
- the injector tube (35) crosses the three walls (30 to 31), with connections respectively: A ball joint (42) for passage through the outer wall
- the second variant is schematically illustrated by the figure
- the injector tube (35) crosses the three walls (30 to 31), with connections respectively:
- the third variant embodiment is illustrated diagrammatically in FIG. 4.
- the injector tube (35) crosses the three walls (30 to 31), with connections respectively:
- the fourth variant is illustrated diagrammatically in FIG. 5.
- the injector tube (35) crosses the three walls (30 to 31), with connections respectively:
- the fifth variant is illustrated diagrammatically in FIGS. 6 to 8.
- the injector tube (35) crosses the three walls (30 to 31), with connections respectively:
- connection between said peripheral tube and the intermediate wall (31) of the sleeve is constituted by a connection (80) having several degrees of freedom to allow axial displacement and a tangential displacement of the tube, and a tolerance for swiveling.
- connection between the peripheral tube (30) and the outer wall (32) of the sheath is formed by rigid sealed assembly.
- the external wall (32) is crossed by a cable gland (37) into which the head (38) of the nozzle (35) is inserted.
- This head (38) has a disc flange (38) engaged between the two parts of the gland (37) which ensures tightening and sealing of this disc flange (38).
- the inner end (40) passes through the inner wall (30) through a single hole formed in the wall (30). This hole is oblong in this case, to take into account the inclination of the axis of the nozzle (35) relative to the radial axis.
- connection between the nozzle (35) and the intermediate wall (31) is produced by a part having a conical upper part (41) flared outwards, extended at its base by a disc collar (42) movable in radial translation in a slot (42) formed in the head (44) of a tubular extension (43) welded to the surface of the interior wall (30).
- the disc collar (42) is flexible, which also allows a slight swiveling relative to this 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)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1874016A FR3090747B1 (fr) | 2018-12-21 | 2018-12-21 | Chambre de combustion d'une turbomachine |
PCT/FR2019/053108 WO2020128292A1 (fr) | 2018-12-21 | 2019-12-17 | Chambre de combustion d'une turbomachine |
Publications (3)
Publication Number | Publication Date |
---|---|
EP3899371A1 true EP3899371A1 (fr) | 2021-10-27 |
EP3899371C0 EP3899371C0 (fr) | 2024-02-07 |
EP3899371B1 EP3899371B1 (fr) | 2024-02-07 |
Family
ID=67441198
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19845596.6A Active EP3899371B1 (fr) | 2018-12-21 | 2019-12-17 | Chambre de combustion d'une turbomachine |
Country Status (6)
Country | Link |
---|---|
US (1) | US20220074595A1 (fr) |
EP (1) | EP3899371B1 (fr) |
CN (1) | CN113454390B (fr) |
CA (1) | CA3124209A1 (fr) |
FR (1) | FR3090747B1 (fr) |
WO (1) | WO2020128292A1 (fr) |
Family Cites Families (21)
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 |
GB2097112B (en) * | 1981-04-16 | 1984-12-12 | Rolls Royce | 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 (fr) | 2011-06-30 | 2019-10-30 | General Electric Company | Chambre de combustion et procédé d'alimentation en carburant de la chambre de combustion |
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/fr 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
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 (fr) | 2024-02-07 |
EP3899371B1 (fr) | 2024-02-07 |
CN113454390A (zh) | 2021-09-28 |
US20220074595A1 (en) | 2022-03-10 |
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