EP0689007B1 - Cooling the take-off injector in a combustion chamber with two burner heads - Google Patents
Cooling the take-off injector in a combustion chamber with two burner heads Download PDFInfo
- Publication number
- EP0689007B1 EP0689007B1 EP95401466A EP95401466A EP0689007B1 EP 0689007 B1 EP0689007 B1 EP 0689007B1 EP 95401466 A EP95401466 A EP 95401466A EP 95401466 A EP95401466 A EP 95401466A EP 0689007 B1 EP0689007 B1 EP 0689007B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- injector
- fuel
- take
- pipe
- double
- 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
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Classifications
-
- 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
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
Definitions
- the present invention relates to the cooling of the injector of take-off from a two-head combustion chamber.
- the idle head In two-head combustion chambers, the idle head is permanently supplied with fuel, whatever the speed of the turbomachine.
- the take-off head is supplied with fuel only beyond a determined minimum speed which corresponds to approximately 20% of the nominal speed. In idling phase it is therefore necessary to cool the injector properly take-off and in particular the nozzle of the injector which includes the injection orifices of fuel, in order to avoid any problem of coking of the fuel circuits and any problem with fuel vapor plug formation.
- the CFM56-5B turbojet a solution of cooling which consists in circulating the flow of fuel which feeds the idle injector in the take-off injector.
- This fuel circulation this take-off injector cools in passing, thus avoiding coking.
- the injectors of the CFM56-5B are aeromechanical type with double flow per module.
- the idle injector fuel supply system has two tubes coaxial, and the take-off injector is supplied by a third tube placed at the center of the first two and communicating with the interior of the room combustion through the injection orifices provided in the nozzle. These holes are thus arranged at a relatively great distance from the passage between the ends of the first two tubes.
- the object of the present invention is to improve the cooling of the take-off injector and in particular its tip.
- the present invention therefore relates to the improvement a double injector fitted to a combustion chamber for two heads of a turbomachine, said double injector comprising a take-off injector comprising a cooling device and furthermore an injector which is supplied with fuel by a first circuit, said injector takeoff having a nozzle provided with fuel injection ports which are fueled by a second circuit separate from the first circuit, double injector in which the first fuel circuit has a first duct which directs the entire flow of fuel supplying said idle injector to the nozzle of the takeoff and a second annular duct which is coaxial with the first duct and which returns said fuel flow to the idle injector, as known from WO-A-94/08179.
- Reference 1 represents a double injector intended for supplying a double-headed annular combustion chamber of a turbomachine, which comprises a head 2 for its attachment to the outer casing of the turbomachine, an injector takeoff 3, away from the head 2 and an idle injector 4 or pilot disposed at mid-distance between the head 2 and the take-off injector 3.
- the take-off injector 3 has at its end a take-off nozzle 5 comprising orifices 6 for inject, into the combustion chamber, a flow of fuel introduced into the head 2 through a feed port 7.
- the idle injector 4 also includes an idle nozzle 8 supplied with a fuel flow introduced into the head 2 through a supply port 9.
- the take-off nozzle 5 comprises a nozzle 10 mounted in the bore internal 11 of a socket 12, this socket 12 being itself mounted at the end of the hollow body 13 which forms the external wall of the double injector 1.
- the end piece 10, of axis 14, has a blind axial bore 15 which communicates with the head orifice 9 by a first tube 16, and an annular cavity 17 which communicates with the injection orifices 6.
- the annular cavity 17 surrounds the blind bore 15 and is separated from the latter by a cylindrical sleeve 18 to the upstream end of which is fixed the end of the first tube 16.
- This second tube 19 surrounds the first tube 16.
- An annular space 20 is delimited by the second tube 19, on the one hand, and the sleeve and the hollow body 13, on the other hand. Channels 21 are provided in the end piece 10 in order to put in communication with the blind bore 15 with the annular space 20.
- the annular space 20 extends from the nozzle 3 to the head 2 of the double injector 1, where it is in permanent communication with the supply channel 22 of the idle head 4. It is externally delimited by a third tube 23 of which the downstream end 24 is tightly fixed to the bush 12.
- the idle injector 4 supply circuit includes the orifice inlet 9, the internal passage of the first tube 16, the blind bore 15, the channels 21, the annular space 20 and the supply channel 22. Thus, all the flow of fuel Q1 which feeds through the idle injector 4 passes through the channels 21 located in the nozzle 10.
- the take-off injector 2 supply circuit includes the orifice inlet 7, the annular space 25 delimited by the first tube 16 and the second tube 19, the annular cavity 17 and the injection orifices 6.
- the orifices injection 6 comprise, from the annular cavity 17, a first portion 6a axial and a second portion 6b inclined radially and tangentially which opens into the combustion chamber.
- These injection ports 6 are at number six in the example shown in the drawings, but this number could be different from six.
- the nozzle 10 which constitutes the most hot of the double injector 1 and therefore the part most sensitive to the phenomena of coking, has a large heat exchange surface with all of the fuel flow Q1 of the idle injector 4. This leads to a reduction significant risk of coking residual fuel in the fuel system take-off module by decreasing the temperatures of the circuit circuit walls lift-off. Thermal calculations have shown a substantial gain of 68% over the surface of the walls at risk, in terms of coking, that is to say with a temperature above 200 ° C.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Description
La présente invention concerne le refroidissement de l'injecteur de décollage d'une chambre de combustion à deux têtes.The present invention relates to the cooling of the injector of take-off from a two-head combustion chamber.
Dans les avions modernes, la lutte contre la pollution atmosphérique, d'une part, et la recherche de performances optimales, d'autre part, peuvent conduire à l'utilisation de chambres de combustion à deux têtes alimentées en carburant par un double injecteur qui comporte une première alimentation pour la tête pilote ou tête de ralenti et une deuxième alimentation pour la tête de décollage.In modern airplanes, the fight against air pollution, on the other hand, and the search for optimal performance, on the other hand, can lead to the use of two-head combustion chambers supplied with fuel by a double injector which includes a first supply for the pilot head or head and a second power supply for the take-off head.
Dans les chambres de combustion à deux têtes, la tête de ralenti est alimentée en permanence en carburant, quel que soit le régime de la turbomachine. En revanche, la tête de décollage n'est alimentée en carburant qu'au delà d'un régime minimum déterminé qui correspond à environ 20 % du régime nominal. En phase de ralenti il est donc nécessaire de refroidir convenablement l'injecteur de décollage et notamment l'embout de l'injecteur qui comporte les orifices d'injection de carburant, afin d'éviter tout problème de cokéfaction des circuits de carburant et tout problème de formation de bouchon de vapeur de carburant.In two-head combustion chambers, the idle head is permanently supplied with fuel, whatever the speed of the turbomachine. On the other hand, the take-off head is supplied with fuel only beyond a determined minimum speed which corresponds to approximately 20% of the nominal speed. In idling phase it is therefore necessary to cool the injector properly take-off and in particular the nozzle of the injector which includes the injection orifices of fuel, in order to avoid any problem of coking of the fuel circuits and any problem with fuel vapor plug formation.
Il a déjà été adopté sur le turboréacteur CFM56-5B une solution de refroidissement qui consiste à faire circuler le débit de carburant qui alimente l'injecteur de ralenti dans l'injecteur de décollage. Cette circulation de carburant refroidit au passage cet injecteur de décollage évitant ainsi la cokéfaction. Cependant, dans cette application particulière, seul le carburant du circuit primaire du circuit de ralenti circule dans la tête de décollage. En effet, les injecteurs du CFM56-5B sont de type aéromécanique à double débit par module. En outre, le circuit d'alimentation du carburant de l'injecteur de ralenti comporte deux tubes coaxiaux, et l'injecteur de décollage est alimenté par un troisième tube disposé au centre des deux premiers et communiquant avec l'intérieur de la chambre de combustion par les orifices d'injection ménagés dans l'embout. Ces orifices sont ainsi disposés à une distance relativement grande du passage entre les extrémités des deux premiers tubes.It has already been adopted on the CFM56-5B turbojet a solution of cooling which consists in circulating the flow of fuel which feeds the idle injector in the take-off injector. This fuel circulation this take-off injector cools in passing, thus avoiding coking. However, in this particular application, only the fuel of the primary circuit of the idling circuit circulates in the take-off head. Indeed, the injectors of the CFM56-5B are aeromechanical type with double flow per module. In addition, the the idle injector fuel supply system has two tubes coaxial, and the take-off injector is supplied by a third tube placed at the center of the first two and communicating with the interior of the room combustion through the injection orifices provided in the nozzle. These holes are thus arranged at a relatively great distance from the passage between the ends of the first two tubes.
Le but de la présente invention est d'améliorer le refroidissement de l'injecteur de décollage et notamment de son embout.The object of the present invention is to improve the cooling of the take-off injector and in particular its tip.
La présente invention concerne donc l'amélioration d'un double injecteur équipant une chambre de combustion à deux têtes d'une turbomachine, ledit double injecteur comportant un injecteur de décollage comprenant un dispositif de refroidissement et en outre un injecteur de ralenti qui est alimenté en carburant par un premier circuit, ledit injecteur de décollage présentant un embout pourvu d'orifices d'injection de carburant qui sont alimentés en carburant par un deuxième circuit séparé du premier circuit, double injecteur dans lequel le premier circuit de carburant comporte un premier conduit qui dirige la totalité du débit de carburant alimentant ledit injecteur de ralenti jusqu'à l'embout de l'injecteur de décollage et un deuxième conduit annulaire qui est coaxial au premier conduit et qui retourne ledit débit de carburant vers l'injecteur de ralenti, tel qu'il est connu par WO-A-94/08179.The present invention therefore relates to the improvement a double injector fitted to a combustion chamber for two heads of a turbomachine, said double injector comprising a take-off injector comprising a cooling device and furthermore an injector which is supplied with fuel by a first circuit, said injector takeoff having a nozzle provided with fuel injection ports which are fueled by a second circuit separate from the first circuit, double injector in which the first fuel circuit has a first duct which directs the entire flow of fuel supplying said idle injector to the nozzle of the takeoff and a second annular duct which is coaxial with the first duct and which returns said fuel flow to the idle injector, as known from WO-A-94/08179.
Selon l'invention, le double injecteur est caractérisé
Grâce à cette disposition, la valeur du débit de carburant de refroidissement est augmentée et les surfaces d'échange thermique dans l'embout sont optimisées.Thanks to this arrangement, the value of the cooling fuel flow is increased and the heat exchange surfaces in the nozzle are optimized.
D'autres caractéristiques et avantages de l'invention ressortiront à la lecture
de la description suivante faite à titre d'exemple et en référence aux dessins
annexés dans lesquels :
La référence 1 représente un double injecteur destiné à l'alimentation d'une
chambre de combustion annulaire à double tête d'une turbomachine, qui comporte
une tête 2 pour sa fixation sur le carter extérieur de la turbomachine, un injecteur
de décollage 3, éloigné de la tête 2 et un injecteur de ralenti 4 ou pilote disposé à
mi-distance entre la tête 2 et l'injecteur de décollage 3. L'injecteur de décollage 3
comporte à son extrémité une buse de décollage 5 comportant des orifices 6 pour
injecter, dans la chambre de combustion, un débit de carburant introduit dans la
tête 2 par un orifice d'alimentation 7. L'injecteur de ralenti 4 comporte également
une buse de ralenti 8 alimentée par un débit de carburant intrtroduit dans la tête 2
par un orifice d'alimentation 9.
La buse de décollage 5 comporte un embout 10 monté dans l'alésage
interne 11 d'une douille 12, cette douille 12 étant elle-même montée à l'extrémité
du corps creux 13 qui forme la paroi externe du double injecteur 1.The take-
L'embout 10, d'axe 14, présente un alésage axial borgne 15 qui
communique avec l'orifice de tête 9 par un premier tube 16, et une cavité annulaire
17 qui communique avec les orifices d'injection 6. La cavité annulaire 17 entoure
l'alésage borgne 15 et est séparée de ce dernier par un manchon cylindrique 18 à
l'extrémité amont duquel est fixé l'extrémité du premier tube 16. Un deuxième tube
19, fixé à l'extrémité amont de la paroi annulaire qui sépare la cavité annulaire 17
de la douille 12, met en communication la cavité annulaire 17 avec l'orifice de tête
7. Ce deuxième tube 19 entoure le premier tube 16. Un espace annulaire 20 est
délimité par le deuxième tube 19, d'une part, et la douille et le corps creux 13,
d'autre part. Des canaux 21 sont ménagés dans l'embout 10 afin de mettre en
communication l'alésage borgne 15 avec l'espace annulaire 20.The
L'espace annulaire 20 s'étend depuis l'embout 3 jusqu'à la tête 2 du double
injecteur 1, où il est en communication permanente avec le canal 22 d'alimentation
de la tête de ralenti 4. Il est délimité extérieurement par un troisième tube 23 dont
l'extrémité aval 24 est fixée de manière étanche à la douille 12.The
Le circuit d'alimentation de l'injecteur de ralenti 4 comprend l'orifice
d'entrée 9, le passage interne du premier tube 16, l'alésage borgne 15, les canaux
21, l'espace annulaire 20 et le canal d'alimentation 22. Ainsi, tout le débit de
carburant Q1 qui alimente par l'injecteur de ralenti 4 transite par les canaux 21
situés dans l'embout 10.The
Le circuit d'alimentation de l'injecteur de décollage 2 comprend l'orifice
d'entrée 7, l'espace annulaire 25 délimité par le premier tube 16 et le deuxième
tube 19, la cavité annulaire 17 et les orifices d'injection 6.The take-
Comme on le voit plus clairement sur les figures 2 et 3, les orifices
d'injection 6 comportent, à partir de la cavité annulaire 17, une première portion 6a
axiale et une deuxième portion 6b inclinée radialement et tangentiellement qui
débouche dans la chambre de combustion. Ces orifices d'injection 6 sont au
nombre de six dans l'exemple montré sur les dessins, mais ce nombre pourrait être
différent de six.As can be seen more clearly in FIGS. 2 and 3, the
Les canaux 21, également au nombre de six, alternent circonférentiellement
avec les orifices d'injection 6. Ainsi, l'embout 10, qui constitue la partie la plus
chaude du double injecteur 1 et donc la partie la plus sensible aux phénomènes de
cokéfaction, comporte une surface d'échange thermique importante avec la totalité
du débit de carburant Q1 de l'injecteur de ralenti 4. Ceci conduit à une diminution
importante des risques de cokéfaction du carburant résiduel dans le circuit du
module de décollage par diminution des températures des parois du circuit de
décollage. Des calculs de thermique ont démontré un gain substantiel de 68 % sur
la surface des parois à risques, en termes de cokéfaction, c'est-à-dire avec une
température supérieure à 200°C.
Claims (1)
- Double injector (1) for a turbomachine two-head combustion chamber, the said double injector (1) comprising a take-off injector (3) comprising a cooling device and also comprising an idling injector (4) which is supplied with fuel by a first circuit, the said take-off injector (3) having a tip (10) with fuel-injection orifices (6) which are supplied with fuel by a second circuit separate from the first circuit, the first fuel circuit comprising a first pipe (16, 15) which conveys all of the fuel flow (Q1) supplying the said idling injector (4) as far as the tip (10) of the take-off injector (3) and a second, annular, pipe (20) which is coaxial with the first pipe (16) and which returns the said fuel flow (Q1) to the idling injector (4), characterized in that the second fuel circuit comprises a third, annular, pipe (25, 27) inserted between the first pipe (16, 15) and the second pipe (20), and in that ducts (21) are formed in the tip (10), to allow the fuel to pass between the first pipe (16) and the second pipe (20), the said ducts (21) alternating with the injection orifices (6) of the said tip (10).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9407624A FR2721694B1 (en) | 1994-06-22 | 1994-06-22 | Cooling of the take-off injector of a combustion chamber with two heads. |
FR9407624 | 1994-06-22 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0689007A1 EP0689007A1 (en) | 1995-12-27 |
EP0689007B1 true EP0689007B1 (en) | 1998-11-11 |
Family
ID=9464487
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP95401466A Expired - Lifetime EP0689007B1 (en) | 1994-06-22 | 1995-06-21 | Cooling the take-off injector in a combustion chamber with two burner heads |
Country Status (5)
Country | Link |
---|---|
US (1) | US5577386A (en) |
EP (1) | EP0689007B1 (en) |
JP (1) | JP2992456B2 (en) |
DE (1) | DE69505895T2 (en) |
FR (1) | FR2721694B1 (en) |
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FR2770283B1 (en) * | 1997-10-29 | 1999-11-19 | Snecma | COMBUSTION CHAMBER FOR TURBOMACHINE |
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US6082113A (en) * | 1998-05-22 | 2000-07-04 | Pratt & Whitney Canada Corp. | Gas turbine fuel injector |
US6289676B1 (en) | 1998-06-26 | 2001-09-18 | Pratt & Whitney Canada Corp. | Simplex and duplex injector having primary and secondary annular lud channels and primary and secondary lud nozzles |
US6357237B1 (en) * | 1998-10-09 | 2002-03-19 | General Electric Company | Fuel injection assembly for gas turbine engine combustor |
DE69932318T2 (en) * | 1998-10-09 | 2007-07-05 | General Electric Co. | FUEL INJECTION DEVICE FOR A GAS TURBINE BURNING CHAMBER |
US6321541B1 (en) * | 1999-04-01 | 2001-11-27 | Parker-Hannifin Corporation | Multi-circuit multi-injection point atomizer |
US6711898B2 (en) | 1999-04-01 | 2004-03-30 | Parker-Hannifin Corporation | Fuel manifold block and ring with macrolaminate layers |
US6256995B1 (en) | 1999-11-29 | 2001-07-10 | Pratt & Whitney Canada Corp. | Simple low cost fuel nozzle support |
US6351948B1 (en) * | 1999-12-02 | 2002-03-05 | Woodward Fst, Inc. | Gas turbine engine fuel injector |
FR2817017B1 (en) * | 2000-11-21 | 2003-03-07 | Snecma Moteurs | COMPLETE COOLING OF THE TAKE-OFF INJECTORS OF A TWO-HEAD COMBUSTION CHAMBER |
US6718770B2 (en) * | 2002-06-04 | 2004-04-13 | General Electric Company | Fuel injector laminated fuel strip |
US7061077B2 (en) * | 2002-08-30 | 2006-06-13 | Fairchild Semiconductor Corporation | Substrate based unmolded package including lead frame structure and semiconductor die |
US6959535B2 (en) * | 2003-01-31 | 2005-11-01 | General Electric Company | Differential pressure induced purging fuel injectors |
US6898926B2 (en) * | 2003-01-31 | 2005-05-31 | General Electric Company | Cooled purging fuel injectors |
US6898938B2 (en) | 2003-04-24 | 2005-05-31 | General Electric Company | Differential pressure induced purging fuel injector with asymmetric cyclone |
DE10324985B4 (en) * | 2003-06-03 | 2005-06-16 | Man B & W Diesel Ag | fuel Injector |
US7104464B2 (en) * | 2003-12-25 | 2006-09-12 | Kawasaki Jukogyo Kabushiki Kaisha | Fuel supply method and fuel supply system |
US7654088B2 (en) * | 2004-02-27 | 2010-02-02 | Pratt & Whitney Canada Corp. | Dual conduit fuel manifold for gas turbine engine |
JP2008520063A (en) | 2004-11-09 | 2008-06-12 | コーニンクレッカ フィリップス エレクトロニクス エヌ ヴィ | Fluorescent lamp capable of sustained release of organic evaporating materials at low temperature |
US20070033945A1 (en) * | 2005-08-10 | 2007-02-15 | Goldmeer Jeffrey S | Gas turbine system and method of operation |
US20070119179A1 (en) * | 2005-11-30 | 2007-05-31 | Haynes Joel M | Opposed flow combustor |
US8387390B2 (en) * | 2006-01-03 | 2013-03-05 | General Electric Company | Gas turbine combustor having counterflow injection mechanism |
US20070151251A1 (en) * | 2006-01-03 | 2007-07-05 | Haynes Joel M | Counterflow injection mechanism having coaxial fuel-air passages |
FR2896030B1 (en) * | 2006-01-09 | 2008-04-18 | Snecma Sa | COOLING A MULTIMODE INJECTION DEVICE FOR A COMBUSTION CHAMBER, IN PARTICULAR A TURBOREACTOR |
US8056326B2 (en) | 2007-05-31 | 2011-11-15 | Caterpillar Inc. | Regeneration device having cooled injection housing |
FR2920525B1 (en) * | 2007-08-31 | 2014-06-13 | Snecma | SEPARATOR FOR SUPPLYING THE COOLING AIR OF A TURBINE |
US8151716B2 (en) * | 2007-09-13 | 2012-04-10 | General Electric Company | Feed injector cooling apparatus and method of assembly |
US7992390B2 (en) * | 2008-09-23 | 2011-08-09 | Pratt & Whitney Canada Corp. | External rigid fuel manifold |
US8393154B2 (en) * | 2009-02-12 | 2013-03-12 | Pratt & Whitney Canada Corp. | Fuel delivery system with reduced heat transfer to fuel manifold seal |
US9221704B2 (en) * | 2009-06-08 | 2015-12-29 | Air Products And Chemicals, Inc. | Through-port oxy-fuel burner |
BR112012011509A2 (en) * | 2009-11-16 | 2016-05-10 | Bell Helicopter Textron Inc | dual way fluid injection nozzle |
US8205598B2 (en) * | 2010-02-08 | 2012-06-26 | International Engine Intellectual Property Company, Llc | Fuel injector nozzle |
EP2362142A1 (en) * | 2010-02-19 | 2011-08-31 | Siemens Aktiengesellschaft | Burner assembly |
US8590311B2 (en) | 2010-04-28 | 2013-11-26 | General Electric Company | Pocketed air and fuel mixing tube |
US20110265485A1 (en) * | 2010-04-30 | 2011-11-03 | General Electric Company | Fluid cooled injection nozzle assembly for a gas turbomachine |
DE112011102685T5 (en) | 2010-08-11 | 2013-06-20 | Cummins Intellectual Properties, Inc. | Engine with injector mounting and cooling arrangement |
EP2520858A1 (en) * | 2011-05-03 | 2012-11-07 | Siemens Aktiengesellschaft | Fuel cooled pilot fuel lance for a gas turbine |
US9188063B2 (en) | 2011-11-03 | 2015-11-17 | Delavan Inc. | Injectors for multipoint injection |
US9400104B2 (en) | 2012-09-28 | 2016-07-26 | United Technologies Corporation | Flow modifier for combustor fuel nozzle tip |
US20150292737A1 (en) * | 2012-10-11 | 2015-10-15 | Ecomb Ab (Publ) | Supply device for a combustion chamber |
US10400674B2 (en) | 2014-05-09 | 2019-09-03 | United Technologies Corporation | Cooled fuel injector system for a gas turbine engine and method for operating the same |
US10385809B2 (en) * | 2015-03-31 | 2019-08-20 | Delavan Inc. | Fuel nozzles |
US9897321B2 (en) | 2015-03-31 | 2018-02-20 | Delavan Inc. | Fuel nozzles |
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GB819042A (en) * | 1956-09-27 | 1959-08-26 | Dowty Fuel Syst Ltd | Improvements relating to liquid fuel burners |
GB2036296B (en) * | 1978-11-20 | 1982-12-01 | Rolls Royce | Gas turbine |
US5269468A (en) * | 1992-06-22 | 1993-12-14 | General Electric Company | Fuel nozzle |
US5423178A (en) * | 1992-09-28 | 1995-06-13 | Parker-Hannifin Corporation | Multiple passage cooling circuit method and device for gas turbine engine fuel nozzle |
FR2712379B1 (en) * | 1993-11-10 | 1995-12-29 | Snecma | Combustion chamber for a turbomachine provided with a gas separator. |
-
1994
- 1994-06-22 FR FR9407624A patent/FR2721694B1/en not_active Expired - Fee Related
-
1995
- 1995-06-20 US US08/493,206 patent/US5577386A/en not_active Expired - Lifetime
- 1995-06-21 EP EP95401466A patent/EP0689007B1/en not_active Expired - Lifetime
- 1995-06-21 DE DE69505895T patent/DE69505895T2/en not_active Expired - Lifetime
- 1995-06-22 JP JP7156099A patent/JP2992456B2/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
EP0689007A1 (en) | 1995-12-27 |
DE69505895D1 (en) | 1998-12-17 |
FR2721694A1 (en) | 1995-12-29 |
JP2992456B2 (en) | 1999-12-20 |
FR2721694B1 (en) | 1996-07-19 |
JPH0814063A (en) | 1996-01-16 |
DE69505895T2 (en) | 1999-06-02 |
US5577386A (en) | 1996-11-26 |
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