EP1278012B1 - Système d'injection aéromécanique à vrille primaire anti-retour - Google Patents
Système d'injection aéromécanique à vrille primaire anti-retour Download PDFInfo
- Publication number
- EP1278012B1 EP1278012B1 EP02291767A EP02291767A EP1278012B1 EP 1278012 B1 EP1278012 B1 EP 1278012B1 EP 02291767 A EP02291767 A EP 02291767A EP 02291767 A EP02291767 A EP 02291767A EP 1278012 B1 EP1278012 B1 EP 1278012B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- injection
- fuel
- injection nozzle
- combustion chamber
- injection system
- 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
- F23R3/02—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
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
Definitions
- the present invention relates to the specific field of turbomachines and is more particularly concerned with the problem posed by the injection of fuel into the combustion chamber of a turbomachine.
- the injection of fuel into the combustion chamber 50 is carried out from several injection systems 52 each comprising, on the one hand, a nozzle of fuel injection 54 ensuring the vaporization of the fuel in the combustion chamber and secondly a mixer / deflector assembly 56 which carries the combustion / fuel mixture and the diffuse in this combustion chamber.
- This mixer / baffle assembly comprises a first vortex or swirl device 58 (swirler 58) slidably mounted on the fuel injection nozzle 54 (via a sleeve 60), a venturi device 62, a second vortex device or secondary swirler 64 and a deflector 66 fixed to the bottom of the combustion chamber 68.
- This conventional injection system architecture has the major drawback of presenting, under certain particular conditions of use, a risk of self-ignition likely to cause destruction of the combustion chamber. Indeed, the impact of fuel on the internal surface of the venturi, necessary to obtain a film of fuel whose fragmentation in fine droplets will be ensured by the shears generated by the primary and secondary tendrils, sometimes results in fuel increases in the vanes of the primary swirl. In addition, because the impact zone of the fuel on this inner surface is not precisely localized, a fuel injection to countercurrent in this primary swirl may also possibly occur. However, such a return of fuel in the primary swirler can contribute to bringing this fuel outside the flame tube and thus risk destroying the focus of the combustion chamber of the turbomachine.
- a turbomachine injection system comprising firstly a fuel injection nozzle for vaporizing the fuel in the combustion chamber and secondly a mixer / deflector assembly disposed coaxially to said injection nozzle and which conducts the combustion / fuel mixture and diffuses it into said combustion chamber, said mixer / deflector assembly comprising a first vortex device (or primary swirler) and at least a second vortex device (or secondary swirler) ) disposed axially at a determined distance from each other and separated by a venturi device disposed coaxially with said injection nozzle, said first vortex device being fixedly attached to said injection nozzle and separated therefrom constant radial distance, characterized in that the venturi device has an internal surface presenting r an upstream part a discontinuity of slope.
- the second vortex device is slidably mounted relative to said injection nozzle via a ring integral with said second vortex device and which can move perpendicularly to an axis of revolution of said vane nozzle. injection, in an annular housing of said venturi device.
- the upstream portion of the inner surface of the venturi device may comprise a concave step or a convex step.
- capillary fuel injection into the primary swirler can be limited.
- the annular combustion chamber is formed of an outer axial wall 24 and an inner axial wall 26, both coaxial with axis 10, and a transverse wall 28 forming chamber bottom and provided with a plurality of openings 30 for fixing the injection systems.
- the different connections between the upstream ends of the axial walls of the chamber 24, 26, possibly caps 32, 34 extending upstream these wall ends, and folded ends of the chamber bottom 28 is performed by any conventional fastening means (not shown), for example screw bolts with a conical head, preferably of the type with a prison nut.
- Each injection system of the injection assembly comprises firstly a fuel injection nozzle 36 for vaporizing the fuel in the combustion chamber and secondly a mixer / deflector assembly 38 coaxial with this nozzle injection and that achieves the combustion / fuel mixture and the diffuse in this combustion chamber.
- This mixer / baffle assembly comprises at least a first vortex device (swirler 40) and a second vortex device 42 spaced axially from each other by a predetermined distance and separated by a device. Venturi 44.
- the secondary swirler is extended by a deflector 46 fixed to the chamber bottom 28 and which extends through the opening 30 in the combustion chamber 22.
- the primary swirler 40 is fixed integrally to the injection nozzle 36, for example by means of a sleeve 48, and from which it is separated by a constant radial distance. This distance is determined so that, irrespective of the operating conditions of the turbomachine (autorotation, idle, full throttle), the fuel vaporized by the injection nozzle can not in any way impact the primary swirler. Thus, it is possible to avoid any possible countercurrent injection of fuel into this primary swirler resulting from the fuel dispersions naturally existing from one injector to the other (because of the injection angles, the circumferential homogeneity, etc.). ) as fuel rebounds on the venturi device.
- the venturi device furthermore has on its inner surface 44A an upstream portion presenting at P a slope discontinuity so as to prevent, or at the very least, to reduce significantly, any risk of capillary rise of the fuel in the primary swirler 40 of the injection system 20.
- This discontinuity of slope made upstream of the outer surface E of the fuel injection cone may for example be constituted by a step concave. In the embodiment of FIG. 3, this discontinuity of slope is instead constituted by a convex step.
- the secondary swirler 42 is slidably mounted relative to to this injection nozzle, perpendicularly to an axis of revolution S of the nozzle, for example by means of a ring 47 fixed to this secondary swirler and movable in an annular housing 49 of the venturi device 44. A this effect, a sufficient clearance is left between the inner periphery of this annular housing and the outer periphery of the ring.
- the injection nozzle is constantly centered with respect to the primary swirler and the venturi device thus avoiding any injection of countercurrent fuel, and the slope discontinuity of this venturi also makes it possible to avoid any rise of fuel by capillarity.
- a good spraying of the fuel is ensured in all flight conditions and in particular in the most severe special conditions of re-ignition in autorotation at low Mach, conditions under which the pressure drops of air supply are too weak to ensure sufficient fragmentation of the fuel and thus access to a large field of re-ignition.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
- Nozzles (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0109456 | 2001-07-16 | ||
FR0109456A FR2827367B1 (fr) | 2001-07-16 | 2001-07-16 | Systeme d'injection aeromecanique a vrille primaire anti-retour |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1278012A2 EP1278012A2 (fr) | 2003-01-22 |
EP1278012A3 EP1278012A3 (fr) | 2003-11-19 |
EP1278012B1 true EP1278012B1 (fr) | 2006-10-25 |
Family
ID=8865551
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP02291767A Expired - Lifetime EP1278012B1 (fr) | 2001-07-16 | 2002-07-12 | Système d'injection aéromécanique à vrille primaire anti-retour |
Country Status (10)
Country | Link |
---|---|
US (1) | US6959551B2 (ja) |
EP (1) | EP1278012B1 (ja) |
JP (1) | JP4066241B2 (ja) |
CN (1) | CN1230650C (ja) |
CA (1) | CA2393082C (ja) |
DE (1) | DE60215589T2 (ja) |
ES (1) | ES2272650T3 (ja) |
FR (1) | FR2827367B1 (ja) |
RU (1) | RU2295645C2 (ja) |
UA (1) | UA76709C2 (ja) |
Families Citing this family (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6691515B2 (en) * | 2002-03-12 | 2004-02-17 | Rolls-Royce Corporation | Dry low combustion system with means for eliminating combustion noise |
US6968692B2 (en) | 2002-04-26 | 2005-11-29 | Rolls-Royce Corporation | Fuel premixing module for gas turbine engine combustor |
US20050229600A1 (en) * | 2004-04-16 | 2005-10-20 | Kastrup David A | Methods and apparatus for fabricating gas turbine engine combustors |
US7966832B1 (en) * | 2004-12-29 | 2011-06-28 | Solar Turbines Inc | Combustor |
US7316117B2 (en) * | 2005-02-04 | 2008-01-08 | Siemens Power Generation, Inc. | Can-annular turbine combustors comprising swirler assembly and base plate arrangements, and combinations |
US7628019B2 (en) * | 2005-03-21 | 2009-12-08 | United Technologies Corporation | Fuel injector bearing plate assembly and swirler assembly |
JP2006300448A (ja) * | 2005-04-22 | 2006-11-02 | Mitsubishi Heavy Ind Ltd | ガスタービンの燃焼器 |
CN100390397C (zh) * | 2005-04-30 | 2008-05-28 | 张鸿元 | 空气压缩航空发动机 |
US7513098B2 (en) | 2005-06-29 | 2009-04-07 | Siemens Energy, Inc. | Swirler assembly and combinations of same in gas turbine engine combustors |
US7617689B2 (en) * | 2006-03-02 | 2009-11-17 | Honeywell International Inc. | Combustor dome assembly including retaining ring |
FR2901574B1 (fr) * | 2006-05-29 | 2008-07-04 | Snecma Sa | Dispositif de guidage d'un flux d'air a l'entree d'une chambre de combustion dans une turbomachine |
FR2903170B1 (fr) * | 2006-06-29 | 2011-12-23 | Snecma | Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif |
FR2903173B1 (fr) * | 2006-06-29 | 2008-08-29 | Snecma Sa | Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif |
FR2908867B1 (fr) * | 2006-11-16 | 2012-06-15 | Snecma | Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif |
FR2920032B1 (fr) * | 2007-08-13 | 2014-08-22 | Snecma | Diffuseur d'une turbomachine |
US9027350B2 (en) * | 2009-12-30 | 2015-05-12 | Rolls-Royce Corporation | Gas turbine engine having dome panel assembly with bifurcated swirler flow |
US10317081B2 (en) * | 2011-01-26 | 2019-06-11 | United Technologies Corporation | Fuel injector assembly |
FR2986856B1 (fr) * | 2012-02-15 | 2018-05-04 | Safran Aircraft Engines | Dispositif d'injection d'air et de carburant pour une chambre de combustion d'une turbomachine |
CN103836647B (zh) * | 2014-02-27 | 2015-07-29 | 中国科学院工程热物理研究所 | 一种文丘里管流道壁面结构 |
FR3029608B1 (fr) * | 2014-12-03 | 2017-01-13 | Snecma | Couronne d'admission d'air pour systeme d'injection de chambre de combustion de turbomachine et procede d'atomisation de carburant dans un systeme d'injection comprenant ladite couronne d'admission d'air |
CN104676647A (zh) * | 2014-12-15 | 2015-06-03 | 西北工业大学 | 一种强化液膜破碎效果的文氏管装置 |
CN104566467B (zh) * | 2014-12-31 | 2018-02-23 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | 一种防回火型喷嘴 |
FR3038699B1 (fr) * | 2015-07-08 | 2022-06-24 | Snecma | Chambre de combustion coudee d'une turbomachine |
US10801726B2 (en) | 2017-09-21 | 2020-10-13 | General Electric Company | Combustor mixer purge cooling structure |
FR3080437B1 (fr) * | 2018-04-24 | 2020-04-17 | Safran Aircraft Engines | Systeme d'injection pour une chambre annulaire de combustion de turbomachine |
US11378275B2 (en) * | 2019-12-06 | 2022-07-05 | Raytheon Technologies Corporation | High shear swirler with recessed fuel filmer for a gas turbine engine |
US11428411B1 (en) * | 2021-05-18 | 2022-08-30 | General Electric Company | Swirler with rifled venturi for dynamics mitigation |
CN115711176A (zh) | 2021-08-23 | 2023-02-24 | 通用电气公司 | 具有集成喇叭形旋流器的圆顶 |
GB2611115A (en) * | 2021-09-23 | 2023-03-29 | Gen Electric | Floating primary vane swirler |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3703259A (en) * | 1971-05-03 | 1972-11-21 | Gen Electric | Air blast fuel atomizer |
US3946552A (en) * | 1973-09-10 | 1976-03-30 | General Electric Company | Fuel injection apparatus |
US3853273A (en) * | 1973-10-01 | 1974-12-10 | Gen Electric | Axial swirler central injection carburetor |
US5117637A (en) * | 1990-08-02 | 1992-06-02 | General Electric Company | Combustor dome assembly |
GB9023004D0 (en) * | 1990-10-23 | 1990-12-05 | Rolls Royce Plc | A gas turbine engine combustion chamber and a method of operating a gas turbine engine combustion chamber |
DE4110507C2 (de) | 1991-03-30 | 1994-04-07 | Mtu Muenchen Gmbh | Brenner für Gasturbinentriebwerke mit mindestens einer für die Zufuhr von Verbrennungsluft lastabhängig regulierbaren Dralleinrichtung |
GB2272756B (en) * | 1992-11-24 | 1995-05-31 | Rolls Royce Plc | Fuel injection apparatus |
DE4444961A1 (de) | 1994-12-16 | 1996-06-20 | Mtu Muenchen Gmbh | Einrichtung zur Kühlung insbesondere der Rückwand des Flammrohrs einer Brennkammer für Gasturbinentriebwerke |
FR2753779B1 (fr) * | 1996-09-26 | 1998-10-16 | Systeme d'injection aerodynamique d'un melange air carburant | |
US5966937A (en) * | 1997-10-09 | 1999-10-19 | United Technologies Corporation | Radial inlet swirler with twisted vanes for fuel injector |
US6571559B1 (en) * | 1998-04-03 | 2003-06-03 | General Electric Company | Anti-carboning fuel-air mixer for a gas turbine engine combustor |
US6314739B1 (en) * | 2000-01-13 | 2001-11-13 | General Electric Company | Brazeless combustor dome assembly |
US6735950B1 (en) * | 2000-03-31 | 2004-05-18 | General Electric Company | Combustor dome plate and method of making the same |
US6427435B1 (en) * | 2000-05-20 | 2002-08-06 | General Electric Company | Retainer segment for swirler assembly |
-
2001
- 2001-07-16 FR FR0109456A patent/FR2827367B1/fr not_active Expired - Fee Related
-
2002
- 2002-07-10 RU RU2002118252/06A patent/RU2295645C2/ru active
- 2002-07-10 CA CA2393082A patent/CA2393082C/fr not_active Expired - Lifetime
- 2002-07-12 ES ES02291767T patent/ES2272650T3/es not_active Expired - Lifetime
- 2002-07-12 JP JP2002203572A patent/JP4066241B2/ja not_active Expired - Lifetime
- 2002-07-12 DE DE60215589T patent/DE60215589T2/de not_active Expired - Lifetime
- 2002-07-12 EP EP02291767A patent/EP1278012B1/fr not_active Expired - Lifetime
- 2002-07-15 US US10/194,230 patent/US6959551B2/en not_active Expired - Lifetime
- 2002-07-15 UA UA2002075852A patent/UA76709C2/uk unknown
- 2002-07-16 CN CN02126114.8A patent/CN1230650C/zh not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
UA76709C2 (uk) | 2006-09-15 |
CN1407280A (zh) | 2003-04-02 |
FR2827367A1 (fr) | 2003-01-17 |
FR2827367B1 (fr) | 2003-10-17 |
DE60215589T2 (de) | 2007-08-30 |
JP4066241B2 (ja) | 2008-03-26 |
DE60215589D1 (de) | 2006-12-07 |
EP1278012A2 (fr) | 2003-01-22 |
CN1230650C (zh) | 2005-12-07 |
CA2393082A1 (fr) | 2003-01-16 |
RU2002118252A (ru) | 2004-02-10 |
US6959551B2 (en) | 2005-11-01 |
ES2272650T3 (es) | 2007-05-01 |
CA2393082C (fr) | 2010-10-19 |
US20030010034A1 (en) | 2003-01-16 |
EP1278012A3 (fr) | 2003-11-19 |
JP2003042452A (ja) | 2003-02-13 |
RU2295645C2 (ru) | 2007-03-20 |
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