EP2671028B1 - Injecteur de chambre de combustion de turbine a gaz a double circuit de carburant et chambre de combustion equipee d'au moins un tel injecteur - Google Patents

Injecteur de chambre de combustion de turbine a gaz a double circuit de carburant et chambre de combustion equipee d'au moins un tel injecteur Download PDF

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Publication number
EP2671028B1
EP2671028B1 EP12706638.9A EP12706638A EP2671028B1 EP 2671028 B1 EP2671028 B1 EP 2671028B1 EP 12706638 A EP12706638 A EP 12706638A EP 2671028 B1 EP2671028 B1 EP 2671028B1
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EP
European Patent Office
Prior art keywords
circuit
injector
combustion chamber
injectors
fuel
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.)
Active
Application number
EP12706638.9A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2671028A1 (fr
Inventor
Bernard Joseph Jean-Pierre Carrere
Jean-Luc DABAT
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.)
Safran Helicopter Engines SAS
Original Assignee
Safran Helicopter Engines SAS
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Filing date
Publication date
Application filed by Safran Helicopter Engines SAS filed Critical Safran Helicopter Engines SAS
Priority to PL12706638T priority Critical patent/PL2671028T3/pl
Publication of EP2671028A1 publication Critical patent/EP2671028A1/fr
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Publication of EP2671028B1 publication Critical patent/EP2671028B1/fr
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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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/101—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet
    • F23D11/102—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet in an internal mixing chamber
    • F23D11/103—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet in an internal mixing chamber with means creating a swirl inside the mixing chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/106—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet
    • F23D11/107—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet at least one of both being subjected to a swirling motion
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00014—Pilot burners specially adapted for ignition of main burners in furnaces or gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00016—Preventing or reducing deposit build-up on burner parts, e.g. from carbon

Definitions

  • the invention relates to a gas turbine combustion chamber injector, in particular a gas turbine engine, comprising a double fuel injection circuit.
  • the invention also relates to a combustion chamber equipped with at least one such dual circuit injector and single circuit injectors.
  • a mixture of compressed air and suitable fuel is generally injected into the combustion chamber using a plurality of injectors.
  • the injectors are mounted in the wall of a flame tube arranged, preferably at the bottom of the chamber. This makes it possible to homogeneously distribute the mixtures originating from the various injectors.
  • a nozzle introduces fuel at the end of a tubing.
  • the fuel is adjusted in a centering guide.
  • the air comes from the last stage of a compressor of the gas machine and is introduced into the injector annularly.
  • Air and fuel are typically introduced into contra-rotated channel swirlers or tendrils, and the fuel particles are sprayed into the air via a mixer.
  • the mixture ignited with a candle located at a certain distance, is burned in the chamber.
  • the generated gases then have a high kinetic energy, which is exploited to generate propulsion or mechanical energy.
  • the ignition of the chamber is provided by two injectors dedicated to start, each starter injector being associated with a candle.
  • the other injectors are dedicated to the post-start systems: transient acceleration or deceleration regimes and stabilized flight regimes.
  • This architecture requires the availability of specific starter injectors, and therefore an additional mass, specific mounting holes for these injectors on the flame tube that supports all the injectors, as well as the introduction of additional controls which result.
  • combustion chambers equipped with injectors having a dual fuel supply circuit, an auxiliary circuit and a main circuit.
  • the auxiliary circuit is dedicated to idle operation, that is to say at low load, while the main circuit or both circuits are solicited at intermediate speeds and stabilized. At full throttle, the ratio of flows between the two circuits is reversed and the main circuit becomes dominant or the sole supplier of fuel.
  • FR 2 906 868 or FR 2,896,030 filed in the name of the plaintiff.
  • Another double circuit injector is known from the patent US 7,513,116 .
  • the invention aims to remedy this problem, by proposing a starter injector that can also be used in all flight regimes without cost or additional mass. To do this, this starter injector has a particular configuration of dual fuel circuit and air circuit.
  • the present invention relates to a gas turbine combustion chamber injector, having a dual fuel injection circuit and an air circuit.
  • the fuel injection circuits consist of a starter fuel circuit, capable of triggering the ignition of the chamber and then operating in all flight regimes, and a main fuel circuit, able to operate in the engine. all the flight regimes after the start.
  • the fuel systems have parallel conduits formed in a common tube of longitudinal axis.
  • the conduit of the starting circuit opens, at one end, substantially in the center of a spherical injector body extending the common tube.
  • the duct houses an injection ramp capable of driving the fuel in rotation before projecting it inside the chamber by a central channel passing through a central swirling wall.
  • the conduit of the main circuit opens into an annular channel formed in the body facing nozzle channels arranged radially in the main wall around the central channel.
  • the air circuit is guided between two portions of concentric spheres constituted by the injector body and a sheath surrounding the injector body and having an opening through which the whirlpool opens.
  • the injector according to the invention has a greatly reduced size thanks to its doubly spherical architecture.
  • the central starting circuit is thermally protected from coking by the circulation of fuel in the annular channel of the main circuit.
  • the main circuit is itself thermally protected by the flow of peripheral air flowing in the inter-spherical space.
  • the swirler is in an inclined position with respect to the longitudinal axis of the injector. This inclination makes it possible to position the end of the starting circuit at the center of the latter and to orient the air and fuel jets in the direction of the candle arranged at the bottom of the chamber.
  • the invention also relates to a combustion chamber equipped with at least one double circuit injector presented above and single circuit injectors. All the injectors are mounted in alignment on the casing surrounding the combustion chamber and pass through a flame tube through orifices formed along at least one line parallel to the longitudinal axis of the flame tube.
  • the dual circuit injectors are directed towards the spark plug so that these injectors are able to project an air / fuel cone at the outlet of the whirlpool directed towards the bottom of the combustion chamber.
  • the combustion chamber is equipped with two non-adjacent dual circuit injectors on the injector line.
  • an injector 1 comprises a fastening flange 10 on a casing 2 of the annular combustion chamber 3, a common shaft tube 11 X'X longitudinal reference of the injector, and a circular swirl 4 central wall 14 and axis of symmetry Y'Y inclined relative to the axis X'X.
  • This central wall 14 allows to project, through the opening 15 of a sleeve 5, an air / fuel mixture in a flame tube 6 which bears on the sleeve 5.
  • the swirl 4 is dimensioned so that the fins 40 of this whirlpool, regularly distributed around the periphery of the central wall 14, support in a self-adjusting and self-centering manner on the edge of the opening 15.
  • the dual fuel injection circuit consists of a starting fuel circuit C1, able to trigger the ignition of the chamber 3 and to operate in all flight regimes, and a main fuel circuit C2, able to work in all flight regimes after starting.
  • the circuits C1 and C2 are coupled to fuel supply pipes (not shown). These circuits consist of access bores 2a, 2b formed in the fastening flange 10, in connection with parallel longitudinal conduits, respectively 12a and 12b, extending in the tube 11 bearing on sealing sleeves 13a and 13b housed in this tube. These ducts extend in the tube 11 parallel to the longitudinal axis X'X and open into the combustion chamber 3 through the central wall 14.
  • the conduit 12a opens - at one end 12e - substantially in the center of a hemispherical injector body 11s in extension of the tube 11.
  • the conduit 12a houses - in a recess cylindrical 21 inclined axis coincides with the Y'Y axis of the whirlpool 4 - a helical fuel rail 7.
  • the recess 21 has a conical end 21c coupled through the central wall 14 of the whirlpool 4, to a central channel 41 of axis coincides with the Y'Y axis of the whirlpool 4 or the recess 21. This central channel 41 opens into the combustion chamber 3.
  • a nozzle 8 is advantageously mounted in the access bore 2b of the flange 10. This nozzle makes it possible to calibrate the fuel flow which varies according to the flight phases.
  • the longitudinal duct 12b is oriented in a final portion 12f parallel to the axis Y'Y and opens into an annular channel 16 formed in the spherical body 11s.
  • This annular channel 16 advantageously has two ends 16e. In other words, this channel is not looped on itself. Thus, no "dead" zone where fuel could stagnate is formed.
  • the annular channel 16 is brazed to the central wall by means of a suitable solder 20 which reveals the non-looped shape of the annular channel 16.
  • This annular channel 16 communicates with nozzle channels 42 arranged radially and distributed equidistantly around of the central channel 41.
  • these nozzle channels have the same diameter.
  • the radial channels 42 advantageously have an orientation along axes K'K symmetrically inclined with respect to the axis Y'Y of the central channel 41 (see in particular the figure 1b ), and contra-rotation relative to the inclination of the vanes 40 of the swirler 4.
  • the number of radial channels 42 is equal to a multiple of the number of vanes 40 of the swirler 4.
  • the inlet air flow F E - from the last compression stage - passes through openings 170 formed in a flared lid 17 extending the tube 11, and is then guided in an air circuit C3 circulating in a space inter-spherical "E".
  • This space "E” is formed between two portions of concentric spheres formed by the injector body 11s and partially by the sleeve 5 in a spherical portion 5s enveloping the injector body 11s.
  • the sheath also has a cylindrical portion with a circular section 5c, which makes it possible to provide support for the flame tube 6 and the flared lid 17 of the tube 11.
  • the injector according to the invention has a minimum space requirement thanks to this interpass. -spherical.
  • the central starting circuit C1 is thermally protected from coking by the circulation of the fuel in the annular channel 16 of the main circuit C2, this main circuit being itself thermally protected by the flow of peripheral air F flowing in the inter-spherical space "E" of the air circuit C3.
  • the air flow F S advantageously forms, passing between the fins 40, an air cone Ca enclosing the fuel outlet cone Cs of the main circuit C2.
  • the tube 11 'does not have a flared lid 17 to form the openings 170 for access to the air flow F E in the circuit C3.
  • the tube 11 ' is extended directly by the spherical body 11s.
  • the conical end portion 21c of the recess 21 passes through the central wall 14 of the swirler 4 and acts as a central channel 41.
  • the partial perspective view illustrates the combustion chamber 3 equipped with injectors mounted on the wall of the flame tube 6: two double circuit injectors 1 shown above and seven single circuit injectors 100.
  • the chamber is partially cut to to show some injectors in full and the candle 101 on the side of the bottom 3f of the chamber.
  • All the injectors 1, 100 are regularly mounted on the annular periphery of the chamber 3. Orifices 60 were made in the tube 6 to enclose the sleeves 5 of the injectors 1, 100.
  • the dual circuit injectors 1 are oriented towards the spark plug 101. Thanks to the inclined orientation of the nozzle channels 42 and the central channels 41, the dual circuit injectors 1 are able to project air / fuel cones Ca / Cs at the outlet of the swirlers to the bottom 3f of the combustion chamber 3. After ignition, the flame goes to the bottom 3f, turns and emerges through the opposite outlet 3s.
  • the two dual circuit injectors 1 are separated by a single circuit injector 100 so as to facilitate the orientation of the dual circuit injectors 1 towards the candle 101.
  • the body of the injector may form a more or less complete sphere part depending on the opening size or the diameter of the common tube. It is also possible to form several lines of injectors in the flame tube.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Ignition Installations For Internal Combustion Engines (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
EP12706638.9A 2011-02-02 2012-01-27 Injecteur de chambre de combustion de turbine a gaz a double circuit de carburant et chambre de combustion equipee d'au moins un tel injecteur Active EP2671028B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL12706638T PL2671028T3 (pl) 2011-02-02 2012-01-27 Wtryskiwacz komory spalania turbiny gazowej z podwójnym obwodem paliwa i komora spalania wyposażona w co najmniej jeden taki wtryskiwacz

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1150807A FR2971039B1 (fr) 2011-02-02 2011-02-02 Injecteur de chambre de combustion de turbine a gaz a double circuit de carburant et chambre de combustion equipee d'au moins un tel injecteur
PCT/FR2012/050177 WO2012104525A1 (fr) 2011-02-02 2012-01-27 Injecteur de chambre de combustion de turbine a gaz a double circuit de carburant et chambre de combustion equipee d'au moins un tel injecteur

Publications (2)

Publication Number Publication Date
EP2671028A1 EP2671028A1 (fr) 2013-12-11
EP2671028B1 true EP2671028B1 (fr) 2018-07-25

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Application Number Title Priority Date Filing Date
EP12706638.9A Active EP2671028B1 (fr) 2011-02-02 2012-01-27 Injecteur de chambre de combustion de turbine a gaz a double circuit de carburant et chambre de combustion equipee d'au moins un tel injecteur

Country Status (11)

Country Link
US (1) US9347667B2 (ko)
EP (1) EP2671028B1 (ko)
JP (1) JP5985514B2 (ko)
KR (1) KR101877591B1 (ko)
CN (1) CN103354890B (ko)
CA (1) CA2825864C (ko)
ES (1) ES2686560T3 (ko)
FR (1) FR2971039B1 (ko)
PL (1) PL2671028T3 (ko)
RU (1) RU2584741C2 (ko)
WO (1) WO2012104525A1 (ko)

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FR2996288B1 (fr) * 2012-10-01 2014-09-12 Turbomeca Injecteur a double circuit de chambre de combustion de turbomachine.
FR2996289B1 (fr) * 2012-10-01 2018-10-12 Turbomeca Chambre de combustion comprenant un tube a flamme fixe au moyen de trois elements de centrage.
FR3001497B1 (fr) * 2013-01-29 2016-05-13 Turbomeca Ensemble de combustion de turbomachine comprenant un circuit d alimentation de carburant ameliore
FR3001525B1 (fr) * 2013-01-29 2016-12-09 Turbomeca Procede de gestion de la consommation de carburant d un ensemble bimoteur et ensemble associe
EP2951505A4 (en) * 2013-02-01 2016-01-06 Hamilton Sundstrand Corp FUEL INJECTOR FOR HEAVY-START AND OPERATION OF A GAS TURBINE MOTOR
US9404422B2 (en) * 2013-05-23 2016-08-02 Honeywell International Inc. Gas turbine fuel injector having flow guide for receiving air flow
WO2015009488A1 (en) 2013-07-15 2015-01-22 Hamilton Sundstrand Corporation Combustion system, apparatus and method
US9625156B2 (en) * 2013-10-30 2017-04-18 Honeywell International Inc. Gas turbine engines having fuel injector shrouds with interior ribs
FR3017693B1 (fr) * 2014-02-19 2019-07-26 Safran Helicopter Engines Chambre de combustion de turbomachine
CN104019475A (zh) * 2014-06-23 2014-09-03 叶祖湘 一种装有燃烧机系统的大小灶具
FR3050255B1 (fr) 2016-04-13 2019-10-25 Safran Helicopter Engines Injecteurs ameliores pour chambre de combustion de turbine a gaz
FR3059047B1 (fr) * 2016-11-21 2020-08-28 Safran Helicopter Engines Injecteur de chambre de combustion pour une turbomachine et son procede de fabrication
FR3067444B1 (fr) * 2017-06-12 2019-12-27 Safran Helicopter Engines Architecture de combustion de carburant de turbomachine comportant des moyens de deflexion
FR3068113B1 (fr) 2017-06-27 2019-08-23 Safran Helicopter Engines Injecteur de carburant a jet plat pour une turbomachine d'aeronef
US10816211B2 (en) * 2017-08-25 2020-10-27 Honeywell International Inc. Axially staged rich quench lean combustion system
FR3081211B1 (fr) * 2018-05-16 2021-02-26 Safran Aircraft Engines Ensemble pour une chambre de combustion de turbomachine
CN109185923B (zh) * 2018-08-03 2023-09-12 新奥能源动力科技（上海）有限公司 一种燃烧室头部装置、燃烧室及燃气轮机
CN109185924B (zh) * 2018-08-03 2023-09-12 新奥能源动力科技（上海）有限公司 燃烧室的头部装置、燃烧室及燃气轮机
FR3087250B1 (fr) 2018-10-11 2020-09-25 Safran Helicopter Engines Injecteur de carburant monobloc a jet plat pour une turbomachine d'aeronef et son procede de fabrication
RU187491U1 (ru) * 2018-11-15 2019-03-11 Публичное Акционерное Общество "Одк-Сатурн" Испарительная камера сгорания газотурбинного двигателя
FR3099231B1 (fr) 2019-07-24 2022-08-12 Safran Helicopter Engines Injecteur de carburant a circuit de purge pour une turbomachine d’aeronef
US11988386B2 (en) 2021-12-03 2024-05-21 Honeywell International Inc. Gas turbine engine injector module with thermally coupled fuel lines having respective outlets
US12117174B2 (en) * 2023-02-14 2024-10-15 Collins Engine Nozzles, Inc. Combustor section support structures

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Also Published As

Publication number Publication date
KR101877591B1 (ko) 2018-07-12
CA2825864C (fr) 2019-05-21
US20130305726A1 (en) 2013-11-21
FR2971039B1 (fr) 2013-01-11
RU2584741C2 (ru) 2016-05-20
JP2014504696A (ja) 2014-02-24
PL2671028T3 (pl) 2018-11-30
CN103354890A (zh) 2013-10-16
ES2686560T3 (es) 2018-10-18
EP2671028A1 (fr) 2013-12-11
KR20140008350A (ko) 2014-01-21
CN103354890B (zh) 2016-06-29
RU2013139354A (ru) 2015-03-10
WO2012104525A1 (fr) 2012-08-09
CA2825864A1 (fr) 2012-09-09
US9347667B2 (en) 2016-05-24
JP5985514B2 (ja) 2016-09-06
FR2971039A1 (fr) 2012-08-03

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