EP3899371B1 - Brennkammer einer turbomaschine - Google Patents

Brennkammer einer turbomaschine Download PDF

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Publication number
EP3899371B1
EP3899371B1 EP19845596.6A EP19845596A EP3899371B1 EP 3899371 B1 EP3899371 B1 EP 3899371B1 EP 19845596 A EP19845596 A EP 19845596A EP 3899371 B1 EP3899371 B1 EP 3899371B1
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EP
European Patent Office
Prior art keywords
wall
injector
combustion chamber
passage
connection
Prior art date
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Active
Application number
EP19845596.6A
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English (en)
French (fr)
Other versions
EP3899371A1 (de
EP3899371C0 (de
Inventor
Damien FAUVET
Marc NGUYEN
Baptiste Guerin
Jean-Michel Guimbard
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.)
Turbotech
Original Assignee
Turbotech
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Publication date
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Application granted granted Critical
Publication of EP3899371B1 publication Critical patent/EP3899371B1/de
Publication of EP3899371C0 publication Critical patent/EP3899371C0/de
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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
    • F23R3/46—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 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 vehicles and light mobile units.
  • 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). °C), with circulation through a heat exchanger inserted between the exhaust gases and the compressed air allowing the air to be partially heated before entering the combustion chamber, which reduces fuel consumption.
  • the invention relates more particularly to the combustion chamber and the injection of fuel into the combustion chamber.
  • German patent DE1254911 providing 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 movable relative to the walls of the combustion chamber.
  • the exterior part of the hook-shaped injection nozzle body is slidably mounted in a guide, possibly associated with the exterior wall of the combustion chamber, and a clamping device directed parallel to the tip mouthpiece of the nozzle is designed to hold the front end of the mouthpiece against a stop fixed in a hub of the flame holder.
  • the problem posed by the solutions of the prior art concerns turbines having a combustion chamber isolated from the outside by a double wall, two walls defining an annular conduit for the circulation of a flow of compressed air coming from the compressor and the third wall being the exterior wall of the combustion chamber, allowing the circulation of the same flow of air heated before passing through a heat exchanger.
  • the injector(s) must pass through the three walls in a sealed manner or at the very least with a controlled leak. This results in a hyperstatic assembly which does not make it possible to absorb the longitudinal thermal expansions of the injector, nor the radial and longitudinal thermal expansions of the metal walls subjected to strongly differentiated temperatures.
  • the injector passes through the walls of the combustion chamber through simple holes, referenced 38, 48 and 52.
  • This document of the prior art proposes to position the injector coaxially inside each of the coaxial holes 52, 48 and 38 provided in the housing 50.
  • This solution therefore leads to multiple disadvantages: on the one hand, the radial expansion of the injector is different from the surface expansion of the walls, which leads either to leaks between the periphery of the injector and the edge of the passage holes in the wall, or to tightness of the edges of the holes around the wall of the injector, which limits the possibilities of radial movement and can lead to deformation and fatigue of the walls .
  • the present invention relates to a combustion chamber of a turbomachine according to the subject of claim 1.
  • FIG. 1 describes a configuration not forming part of the invention as defined by the claims and 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 (11) coaxial with the exchanger (1) circulates the hot gases coming from the turbine (4) towards an evacuation outlet (12) after passing through the exchanger (2), crossing two cassettes (5, 6) between the tubes.
  • the exchanger (2) consists of a tube exchanger, comprising two coaxial annular cassettes (5, 6).
  • the outer cassette (5) is made up of an assembly of parallel tubes, made of a metal alloy resistant to high temperatures, for example refractory stainless steel 347.
  • this exterior cassette (5) is made up of 2000 tubes with a length of 300 millimeters, an interior section of 2.8 millimeters and an exterior section of 3 millimeters.
  • the tubes are held in a known manner by spacers to define passages for hot gases coming from the turbine.
  • the tubes form a sleeve with an outer radius of 158 millimeters and an inner radius of 128 millimeters.
  • the inner cassette (6) is made up 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 outer radius of 123 millimeters and an inner radius of 67 millimeters.
  • the two cassettes (5, 6) are coaxial and embedded one inside the other.
  • Each of the cassettes (5, 6) comprises, at each end, a front sealing plate pierced for the passage of the tubes, and ensuring the constant center distance of the tubes.
  • the tubes are brazed or welded to ensure tightness at their connection with the front plates.
  • This closing structure (8) is made up of two coaxial interlocking parts, having the general shape of a rum baba mold, in 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 inner part (10) has an outer section corresponding to the inner section of the outer cassette (5) and an inner section corresponding to the outer section of the inner 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 closing structure (8) ensures the deflection of gases coming from the outer cassette (5) towards the tubes constituting the inner cassette (6).
  • This solution ensures a double passage of gases in the exchanger (1), which significantly increases its thermal efficiency for a given size, and in particular a length.
  • the annular type combustion chamber (3) has a double inner 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 ports.
  • the walls (30 to 32) as well as the tube (35) of the injector are subjected to longitudinal and radial expansions. Fixation is ensured by a combination of connections avoiding hyperstatic situations.
  • connection between the tube (35) of the injector and the interior wall (30) is ensured by a slide connection formed by a calibrated lumen defining with the exterior 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 alternative embodiment does not conform to the invention as defined by the claims and is illustrated schematically by the figure 2 .
  • the second alternative embodiment does not conform to the invention as defined by the claims and is illustrated schematically by the Figure 3 .
  • the third alternative embodiment does not conform to the invention as defined by the claims and is illustrated schematically by the figure 4 .
  • the fourth alternative embodiment does not conform to the invention as defined by the claims and is illustrated schematically by the figure 5 .
  • connection between said peripheral tube and the intermediate wall (31) of the sheath is constituted by a connection (80) having several degrees of freedom to allow axial movement and tangential movement of the tube, and a tolerance for pivoting.
  • connection between the peripheral tube (30) and the outer wall (32) of the sheath is constituted by a rigid sealed assembly.
  • the outer wall (32) is crossed by a cable gland (37) into which the head (38) of the injector (35) is inserted.
  • This head (38) has a disc collar (38) engaged between the two parts of the gland (37) which ensures tightening and sealing of this disc collar (38).
  • the inner end (40) passes through the inner wall (30) through a simple hole formed in the wall (30).
  • This hole is oblong in this case, to take into account the inclination of the axis of the injector (35) relative to the radial axis.
  • connection between the injector (35) and the intermediate wall (31) is made by a part having a conical upper part (41) flared outwards, extended at its base by a disc flange (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 flange (42) is flexible, which also allows slight rotation in relation 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)
  • Joints Allowing Movement (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (4)

  1. - Brennkammer einer Turbomaschine, umfassend zwei koaxiale Rotationswände, umfassend eine Innenwand (30) und eine Zwischenwand (31), die sich ineinander erstrecken und zwischen sich einen ringförmigen Raum (33) für Luftzirkulation begrenzen, und eine Außenwand (32), und eine mindestens eine Einspritzdüse (35), die die Innen- (30), die Zwischen- (31) und die Außenwand (32) durch Schlitze durchdringt, dadurch gekennzeichnet, dass die mindestens eine Einspritzdüse (35) ein Umfangsrohr, das mit den Wänden (30 bis 32) durch drei Verbindungen verbunden ist, aufweist, wobei eine Verbindung zwischen dem Umfangsrohr und der Außenwand (32) durch eine starre dichte Verbindungsstelle gebildet wird, wobei eine Verbindung zwischen dem Umfangsrohr und der Zwischenwand (31) durch ein Stück hergestellt wird, das ein nach außen erweitertes konisches oberes Teil (41) aufweist, das an seiner Basis durch einen Scheibenflansch (42) verlängert wird, der in einer Spalte (42), die in dem Kopf (44) einer an die Oberfläche der Zwischenwand (31) geschweißten röhrenförmigen Verlängerung (43) gebildet ist, radial verschiebbar ist, wobei mindestens zwei Verbindungen flexible, dichte Verbindungen sind.
  2. - Brennkammer einer Turbomaschine nach Anspruch 1,
    dadurch gekennzeichnet, dass die Verbindung zwischen dem Umfangsrohr (35) und der Innenwand (30) durch eine ringförmige lineare Verbindung mit einer Leckage, die durch einen kalibrierenden ringförmigen Abschnitt geregelt wird, gebildet wird.
  3. - Brennkammer einer Turbomaschine nach Anspruch 1,
    dadurch gekennzeichnet, dass die Außenwand (32) durch eine Stopfbuchse (37) durchdrungen wird, in die der Kopf (38) der Einspritzdüse (35) eingesetzt ist, wobei der Kopf (38) einen Scheibenflansch (38), der zwischen den zwei Teilen der Stopfbuchse (37) in Eingriff genommen ist, aufweist.
  4. - Brennkammer einer Turbomaschine nach Anspruch 1,
    dadurch gekennzeichnet, dass das innere Ende (40) der Einspritzdüse (35) die Innenwand (30) durch den Durchgang in einem in der Innenwand (30) ausgebildeten Langloch durchdringt.
EP19845596.6A 2018-12-21 2019-12-17 Brennkammer einer turbomaschine Active EP3899371B1 (de)

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 EP3899371A1 (de) 2021-10-27
EP3899371B1 true EP3899371B1 (de) 2024-02-07
EP3899371C0 EP3899371C0 (de) 2024-02-07

Family

ID=67441198

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19845596.6A Active EP3899371B1 (de) 2018-12-21 2019-12-17 Brennkammer einer turbomaschine

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)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160334102A1 (en) * 2015-05-13 2016-11-17 Solar Turbines Incorporated Controlled-leak combustor grommet

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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
WO2013002669A1 (en) 2011-06-30 2013-01-03 General Electric Company Combustor and method of supplying fuel to the combustor
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
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

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160334102A1 (en) * 2015-05-13 2016-11-17 Solar Turbines Incorporated Controlled-leak combustor grommet

Also Published As

Publication number Publication date
CN113454390B (zh) 2023-02-24
CN113454390A (zh) 2021-09-28
EP3899371A1 (de) 2021-10-27
CA3124209A1 (fr) 2020-06-25
WO2020128292A1 (fr) 2020-06-25
US20220074595A1 (en) 2022-03-10
FR3090747B1 (fr) 2021-01-22
FR3090747A1 (fr) 2020-06-26
EP3899371C0 (de) 2024-02-07

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