GB2312250A - Staged gas turbine fuel system with a single supply manifold, to which the main burners are connected through valves. - Google Patents
Staged gas turbine fuel system with a single supply manifold, to which the main burners are connected through valves. Download PDFInfo
- Publication number
- GB2312250A GB2312250A GB9608027A GB9608027A GB2312250A GB 2312250 A GB2312250 A GB 2312250A GB 9608027 A GB9608027 A GB 9608027A GB 9608027 A GB9608027 A GB 9608027A GB 2312250 A GB2312250 A GB 2312250A
- Authority
- GB
- United Kingdom
- Prior art keywords
- fuel
- servo
- manifold
- pressure
- supply
- 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.)
- Withdrawn
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/228—Dividing fuel between various burners
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
Description
2312250 FUEL SYSTEM FOR A GAS TURBINE ENGINE The invention relates to a
fuel system for a gas turbine engine.
In particular the invention concerns a fuel system of the kind sometimes referred to as a staged fuel system in which fuel injectors or burners are, at least notionally, arranged in several groups. At least one of these groups receiving fuel continuously while the remaining groups receive fuel in a staged manner according to engine power demand.
Staged fuel systems of the kind of present interest are associated most commonly, but not exclusively, with annular combustors. However, such annular combustors may be of the single annular type, or the double annular type and in the latter instance may be axially staged or radially staged or a combination. Typically in single annular combustors a multiplicity of fuel injector means are spaced apart circumferentially around the combustor at a single radius. For staged operation these injector means may be notionally grouped in a variety of patterns; for example in a low power operating condition fuel may be supplied to alternate injector means, or every third or fourth injector an so on, or still further they may be grouped together in multiples as is already known in the art. It has to be mentioned here also that the term "injector means" or "injector" or "burner" is not intended to be construed narrowly, rather it is to be understood to include any of the presently known means of introducing fuel or fuel/air mixture Into a continuous burn combustion chamber.
The objectives and principles of staged combustion processes, for example for the purpose of reduced' 2 production of hydro-carbons (HC), carbon monoxide (C0) and oxides of nitrogen (NO,) are well documented in prior art literature. No further explanation or description will be set forth hereinafter as the skilled reader will already be familiar with such literature.
In such staged fuel systems, during periods of low-power burning the noncontributing injectors or burners will be subject to heat soak so that residual fuel will be vaporised with the virtually inevitable result that trapped fuel would be reduced to a deposit capable of blocking the fuel flow passage. Thus, considerable trouble is taken in the design of the fuel systems to avoid trapped fuel by purging unused burners and even their supply manifold. Double manifold systems incur an unavoidable weight penalty and delay in re-filling the purged manifold when high power operation is demanded. The alternative of a single manifold requires valve means for controlling fuel supply to the non-continuously used injectors. These valves must remain capable of operation after prolonged period of heat soak but, preferably, should remain primed ready for virtually instantaneous operation. The present invention is intended to address these problems.
According to the present invention there is provided a fuel system for a gas turbine engine comprising a multiplicity of fuel injector means, a fuel supply manifold with which all fuel injectors means are in fuel supply communication, some of the fuel injector means being in free communication with the supply manifold to receive fuel, and further ones of the fuel injector means being connected to the fuel manifold through valve means selectively operable to stem the flow of fuel, said valve means comprising servo-operated valve means responsive to a high fuel supply demand.
Preferably, the valve means comprises a fuel system wherein the valve means comprises a plurality of servooperated valves interconnected by a fluid carrying servopressure manifold.
Furthermore, it is preferred for the servo-pressure manifold to carry a continuous flow of fuel diverted from the normal fuel supply system to the fuel injector means.
The invention and how it may be carried into practice will now be described in greater detail with particular reference to an embodiment illustrated in the accompanying drawings, in which:
Figure 1 is a schematic illustration of the fuel supply manifold, fuel injector means and servo-valve system of a staged fuel system according to the invention, Figure 2 illustrates a sectioned view of a servovalve for controlling fuel flow to a staged fuel injector, and Figure 3 is a schematic diagram showing how the arrangement of Figure 1 might be incorporated in a typical, known fuel system.
In Figure 1 twenty fuel injector means 2 are circumferentially spaced apart around the interior of an annular combustion chamber 4. A metered fuel supply (see Figure 3) is delivered at 10 to a fuel manifold 12. Normally the fuel manifold, as in this embodiment, extends circumferentially around the exterior of the combustion chamber casing, ie it is located in the bypass duct of a bypass engine, and fuel Is delivered to each of the fuel injector means 2 through a radial, inwardly directed spur 14.
The particular fuel system is of the kind known generally as a staged system, that is, a system in which the totality of fuel injector means are divided into two groups, at least, termed pilot and main burners. In one group the pilot burners 20 are operated continuously and when necessary, such as during high power requirements, these are supplemented by the main burners 22 of the second group to increase the flow of fuel into the combustion chamber. In the drawing the pilot burners 20 are denoted by plain, circular discs and the main burners 22 by quartered discs. As shown, in the illustrated system, the main burners 22 are grouped in pairs, and receive fuel through outlets 24,26 from a servocontrolled fuel supply valve 16 connected to a fuel spur 14.
Figure 2 illustrates a servo-controlled fuel supply valve generally indicated at 16, consisting of a hollow valve body 28 the interior of which is divided into a plurality of chambers 30,32 separated by a servopiston 34. The chamber 20 on one side of the piston 34 acts as a servochamber to exert pressure on the end face 36 of the piston 34. The piston 34 is arranged for axial movement within a first bore 38 formed within the valve body 28. Opposite the face 36 the piston is formed within an extension 40 of smaller diameter, than the face 36, which is a sliding fit within the bore 42 of the second chamber 32. The stroke of piston 34 is limited in the direction of servo-chamber 30 by an annular stop 44 which defines a minimum volume in the chamber and maintains uninhibited flow through the chamber between a servo-flow inlet 46 and a servo-flow outlet 48. The piston 34 is biased in this direction by a spring 50 in the interior of the valve behind the piston. At the opposite end of the valve 16 the fuel supply chamber 32 has a fuel inlet 14 and two fuel outlets 24,26, one to each of the pair of main burners. The piston extension 40 towards the other end of the piston stroke is effective to cut-off communication between the fuel inlet 14 and the two outlets 24,26 thus stemming the supply of fuel to the main burners 22. The enclosed space within the valve body and behind piston 34, the volume of which space varies in accordance with movement of the piston, Is vented into the fuel path through a by-pass passage 52.
It will be apparent from Figure 1 that there are a plurality of servooperated fuel valves 16 distributed around the combustion chamber. The servo-flow inlets 46 and outlets 48 of these valves are connected In series by a closed-loop servo manifold 54. This manifold 54 has an inlet connected through a flow restrictor 56 to a fuel feed 58 tapped from a high pressure fuel pump outlet, and a servo-return 6 through a variable valve 62 to a point in the fuel system of relatively low pressure. The valve 62 may be a solenoid valve electrically actuated by a signal on control line 63. Preferably, the servomanifold, servo-valves and associated pipework is also located within the bypass duct.
The diagram of Figure 3 shows how this system may be incorporated Into a typical fuel system of a gas turbine engine. The major elements of the fuel system comprise a first stage, or low pressure, fuel pump 64 which draws fuel through an inlet 66 from a fuel tank (not shown). Fuel from pump 64 is passed through a filter 68 which has a parallel, automatic relief valve 70 in the event of the filter becoming blocked. There is also a return path 69 from the outlet of filter 68 via an ejector pump 71 to the inlet of pump 64. The main flow of fuel from filter 6 68 is passed directly to the inlet of a high pressure pump 72 and hence to a fuel metering unit 74. A digital engine control unit (DECU) 76 produces electrical signals on signal lines 78 to control operation of the metering unit 74 in accordance with various inputs (not shown) such as the pilot's speed or thrust demand and various parameter measurements and governor limits etc and on line 63 to control fuel staging. Generally, the volume flow from pump 72 exceeds the requirement of the metering unit 74. In the present arrangement the servo-supply 58 is tapped from the outlet of the pump 72, the servo requirement being easily absorbed by the flow excess, and the servo return is connected to the low pressure region in return path 69.
In operation the supply of fuel to the main burners 22 is controlled by pressure in the servo-manifold 54 acting directly on each of the servovalves 16. This servopressure is governed by the valve 62 on the lowpressure return side of the manifold. When valve 62 is closed the pressure in the manifold 54 and in the valve servochambers 30 will rise to the output pressure of pump 72. With no flow in the servo-manifold the restrictor 56 has no effect and no pressure losses occur. All the servovalves 16 will thus be actuated by pressure in chambers 30 acting on the pistons 34 to cut-off fuel flow from the manifold 12 to the main burners 22.
When valve 62 is opened and flow circulates in manifold 54 from the high pressure inlet 58 to the low pressure return 69 the flow restrictor 56 becomes effective and substantially the whole of the pressure drop occurs across the restrictor orifice. As a result the pressure in all of the servo-chambers 30 around the entire manifold system is substantially reduced. The bias force in the servo-valves is chosen to exceed this low pressure 7 so all of the valves 16 switch-over and establish fuel flow to the main burners.
This manner of staging control can be achieved with a relatively low servo-manifold flow, determined by restrictor 56, so as not to rob the metering unit 74 of fuel flow. When staging is initiated by closing valve 62 manifold flow will cease, so that fuel is trapped In the manifold. However, if the servo-manifold is located around the outer wall of the combustor chamber and in bypass duct air the ambient temperature of its surroundings will almost certainly be too low for fuel coking to be a problem. Obviously conditions vary between engines and system dispositions. If desired a small flow could be maintained through the manifold, for example by arranging a bleed bypass to valve 62, which may allow the servo-manifold to be located in the chamber head, for example. In order to avoid a problem of fuel system hammer when staging is selected and deselected the valve 62 is preferably adapted for progressive operation, as opposed to snap operation. Alternatively the ports in the servo-valves 16 may be profiled to slug their response. The servo-valves 16 preferably utilise bias springs 50 having a relatively high spring force to overcome usticktion" of the servo-pistons 34 and thereby improve reliability.
The invention is intended for use in fuel-staging systems but may be used in conjunction with the several types of staging in use, for example radial staging, axial staging or a combination of the two. Also the invention Is not limited to the manner of grouping of the staged burners. Thus, although in the described embodiment the staged burners are grouped in pairs any other of the possible arrangements could be employed. So, for example, the staged or main burners may be arranged individually, or in groups of two, three or more burners, neither need burners controlled in groups be disposed adjacent to each other in the combustion chamber.
9
Claims (1)
- A fuel system for a gas turbine engine comprising a multiplicity of fuel injector means, a fuel supply manifold with which all fuel injectors means are In fuel supply communication, some of the fuel injector means being in free communication with the supply manifold to receive fuel, and further ones of the fuel injector means being connected to the fuel manifold through valve means selectively operable to stem the flow of fuel, said valve means comprising servo-operated valve means responsive to a high fuel supply demand to supply fuel selectively to the further fuel injector means for increased fuel burning.2 A fuel system according to claim 1 wherein the valve means comprises a plurality of servo-operated valves interconnected by a fluid carrying servo-pressure manifold.3 A fuel system according to claim 1 wherein the servo-pressure manifold is arranged to carry a continuous flow of fuel diverted from the normal fuel supply system to the fuel injector means.4 A fuel system according to claim 3 wherein the servo-pressure flow of fuel is derived from a source of high pressure in the fuel supply system and is returned to a region of low pressure in the system.A fuel system according to claim 3 or claim 4 wherein the flow of fuel is regulated by throttle or restrictor means on the upstream of the servopressure manifold.- 6 A fuel system according to any one of claim s 2 to 5 further comprising a valve on the downstream side of the servo-pressure manifold to control servomanifold pressure.7 A fuel system according to any preceding claim wherein the servooperate valve means comprises a valve body having a servo-pressure chamber housing a piston movable in response to high servo-pressure to stem fuel supply to the further injector means.8 'A fuel system according to claim 7 wherein the piston is biased against pressure in the servopressure chamber.9 A fuel system according to claim 7 or 8 wherein the piston comprises a first portion located within the servo-pressure chamber and a second portion located within a fuel supply chamber and movable therein to interrupt flow between a fuel supply inlet in communication with the fuel supply manifold and an outlet in communication with the fuel injector means.A fuel system as claimed in any preceding claim wherein the servooperated valve means is arranged to control fuel supply to a plurality of further fuel injector means.11 A fuel system as claimed in claim 10 wherein the further fuel injector means are grouped in pairs and fuel supply to each pair is controlled by a single servo-operated valve means.12 A fuel system for a gas turbine engine substantially as hereinbefore described with reference to the accompanying drawings.
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB9608027A GB2312250A (en) | 1996-04-18 | 1996-04-18 | Staged gas turbine fuel system with a single supply manifold, to which the main burners are connected through valves. |
DE69719588T DE69719588T2 (en) | 1996-04-18 | 1997-04-07 | Fuel supply system for a gas turbine |
EP97302387A EP0802310B1 (en) | 1996-04-18 | 1997-04-07 | Fuel system for a gas turbine engine |
US08/834,433 US5884483A (en) | 1996-04-18 | 1997-04-16 | Fuel system for a gas turbine engine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB9608027A GB2312250A (en) | 1996-04-18 | 1996-04-18 | Staged gas turbine fuel system with a single supply manifold, to which the main burners are connected through valves. |
Publications (2)
Publication Number | Publication Date |
---|---|
GB9608027D0 GB9608027D0 (en) | 1996-06-19 |
GB2312250A true GB2312250A (en) | 1997-10-22 |
Family
ID=10792268
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB9608027A Withdrawn GB2312250A (en) | 1996-04-18 | 1996-04-18 | Staged gas turbine fuel system with a single supply manifold, to which the main burners are connected through valves. |
Country Status (4)
Country | Link |
---|---|
US (1) | US5884483A (en) |
EP (1) | EP0802310B1 (en) |
DE (1) | DE69719588T2 (en) |
GB (1) | GB2312250A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6857272B2 (en) | 2001-07-18 | 2005-02-22 | Rolls-Royce Plc | Fuel delivery system |
US10288294B2 (en) | 2015-03-20 | 2019-05-14 | Rolls-Royce Plc | Combustion staging system |
Families Citing this family (41)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0976982B1 (en) * | 1998-07-27 | 2003-12-03 | ALSTOM (Switzerland) Ltd | Method of operating the combustion chamber of a liquid-fuel gas turbine |
US6711898B2 (en) * | 1999-04-01 | 2004-03-30 | Parker-Hannifin Corporation | Fuel manifold block and ring with macrolaminate layers |
GB0019533D0 (en) * | 2000-08-10 | 2000-09-27 | Rolls Royce Plc | A combustion chamber |
EP1270902B1 (en) | 2001-06-22 | 2009-10-21 | ALSTOM Technology Ltd | Procedure for the start of a gas turbine system |
GB2378224B (en) * | 2001-07-18 | 2005-10-12 | Rolls Royce Plc | Gas turbine engine fuel delivery system |
FR2832458B1 (en) * | 2001-11-19 | 2004-07-09 | Snecma Moteurs | FUEL INJECTION SYSTEM IN A TURBOMACHINE |
DE10160997A1 (en) * | 2001-12-12 | 2003-07-03 | Rolls Royce Deutschland | Lean premix burner for a gas turbine and method for operating a lean premix burner |
US6786049B2 (en) * | 2002-05-22 | 2004-09-07 | Hamilton Sundstrand | Fuel supply control for a gas turbine including multiple solenoid valves |
JP3978086B2 (en) * | 2002-05-31 | 2007-09-19 | 三菱重工業株式会社 | Aircraft gas turbine system, gas turbine system, and operation method thereof |
US6931831B2 (en) * | 2002-06-18 | 2005-08-23 | Jansen's Aircraft Systems Controls, Inc. | Distributor purge valve |
US7527068B2 (en) | 2002-06-18 | 2009-05-05 | Jansen's Aircraft Systems Controls, Inc. | Valve with swirling coolant |
US6868676B1 (en) | 2002-12-20 | 2005-03-22 | General Electric Company | Turbine containing system and an injector therefor |
US6968699B2 (en) * | 2003-05-08 | 2005-11-29 | General Electric Company | Sector staging combustor |
US6996991B2 (en) * | 2003-08-15 | 2006-02-14 | Siemens Westinghouse Power Corporation | Fuel injection system for a turbine engine |
US7506511B2 (en) * | 2003-12-23 | 2009-03-24 | Honeywell International Inc. | Reduced exhaust emissions gas turbine engine combustor |
DE102004002631A1 (en) * | 2004-01-19 | 2005-08-11 | Alstom Technology Ltd | A method of operating a gas turbine combustor |
US7654088B2 (en) * | 2004-02-27 | 2010-02-02 | Pratt & Whitney Canada Corp. | Dual conduit fuel manifold for gas turbine engine |
US7377114B1 (en) * | 2004-06-02 | 2008-05-27 | Kevin P Pearce | Turbine engine pulsed fuel injection utilizing stagger injector operation |
US7533531B2 (en) * | 2005-04-01 | 2009-05-19 | Pratt & Whitney Canada Corp. | Internal fuel manifold with airblast nozzles |
GB0811741D0 (en) * | 2008-06-27 | 2008-07-30 | Rolls Royce Plc | A fuel control arrangement |
JP4838888B2 (en) * | 2009-05-27 | 2011-12-14 | 川崎重工業株式会社 | Gas turbine combustor |
EP2480773B1 (en) * | 2009-09-24 | 2014-12-31 | Siemens Aktiengesellschaft | Fuel line system, method for operating a gas turbine, and method for purging the fuel line system of a gas turbine |
FR2958975B1 (en) | 2010-04-15 | 2012-04-27 | Snecma | FUEL SUPPLY DEVICE OF AN AERONAUTICAL ENGINE |
US9557050B2 (en) | 2010-07-30 | 2017-01-31 | General Electric Company | Fuel nozzle and assembly and gas turbine comprising the same |
US8776529B2 (en) | 2010-09-27 | 2014-07-15 | Hamilton Sundstrand Corporation | Critical flow nozzle for controlling fuel distribution and burner stability |
US8479521B2 (en) | 2011-01-24 | 2013-07-09 | United Technologies Corporation | Gas turbine combustor with liner air admission holes associated with interspersed main and pilot swirler assemblies |
US9957891B2 (en) | 2011-09-09 | 2018-05-01 | General Electric Company | Fuel manifold cooling flow recirculation |
US10240533B2 (en) * | 2011-11-22 | 2019-03-26 | United Technologies Corporation | Fuel distribution within a gas turbine engine combustor |
US20130219911A1 (en) * | 2012-02-28 | 2013-08-29 | Honeywell International Inc. | Combustion system for a gas turbine engine and method for directing fuel flow within the same |
US20140338341A1 (en) * | 2012-06-22 | 2014-11-20 | Solar Turbines Incorporated | Liquid fuel turbine engine for reduced oscillations |
US20130340438A1 (en) * | 2012-06-22 | 2013-12-26 | Solar Turbines Incorporated | Method of reducing combustion induced oscillations in a turbine engine |
US20130340436A1 (en) * | 2012-06-22 | 2013-12-26 | Solar Turbines Incorporated | Gas fuel turbine engine for reduced oscillations |
US9310072B2 (en) | 2012-07-06 | 2016-04-12 | Hamilton Sundstrand Corporation | Non-symmetric arrangement of fuel nozzles in a combustor |
FR3001497B1 (en) * | 2013-01-29 | 2016-05-13 | Turbomeca | TURBOMACHINE COMBUSTION ASSEMBLY COMPRISING AN IMPROVED FUEL SUPPLY CIRCUIT |
US9388778B2 (en) | 2013-07-19 | 2016-07-12 | Woodward, Inc. | Servo flow recirculation for an advanced thermal efficient aircraft engine fuel system |
US10330321B2 (en) * | 2013-10-24 | 2019-06-25 | United Technologies Corporation | Circumferentially and axially staged can combustor for gas turbine engine |
US10330320B2 (en) * | 2013-10-24 | 2019-06-25 | United Technologies Corporation | Circumferentially and axially staged annular combustor for gas turbine engine |
US9995220B2 (en) * | 2013-12-20 | 2018-06-12 | Pratt & Whitney Canada Corp. | Fluid manifold for gas turbine engine and method for delivering fuel to a combustor using same |
GB201604379D0 (en) * | 2016-03-15 | 2016-04-27 | Rolls Royce Plc | A combustion chamber system and a method of operating a combustion chamber system |
US10428738B2 (en) * | 2016-12-14 | 2019-10-01 | Solar Turbines Incorporated | Start biased liquid fuel manifold for a gas turbine engine |
GB2574615B (en) * | 2018-06-12 | 2020-09-30 | Gabrielle Engine Ltd | Combustion engine |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1437397A (en) * | 1972-09-05 | 1976-05-26 | Gen Electric | Gas turbine engine fuel distribution systems |
US4305255A (en) * | 1978-11-20 | 1981-12-15 | Rolls-Royce Limited | Combined pilot and main burner |
US5289685A (en) * | 1992-11-16 | 1994-03-01 | General Electric Company | Fuel supply system for a gas turbine engine |
GB2285285A (en) * | 1993-12-09 | 1995-07-05 | United Technologies Corp | Fuel staging system |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3106934A (en) * | 1958-12-24 | 1963-10-15 | Bendix Corp | Integrating and proportional flow control apparatus |
BE790239A (en) * | 1971-11-01 | 1973-02-15 | Gen Electric | VORTEX VALVE FUEL DISTRIBUTION SYSTEM FOR GAS TURBINE ENGINES |
US4027473A (en) * | 1976-03-05 | 1977-06-07 | United Technologies Corporation | Fuel distribution valve |
GB2086482B (en) * | 1980-10-30 | 1984-02-08 | Rolls Royce | Priming device for burner manifolds of gas turbine engines |
GB2174147B (en) * | 1985-04-25 | 1989-02-01 | Rolls Royce | Improvements in or relating to the operation of gas turbine engine fuel systems |
US4817389A (en) * | 1987-09-24 | 1989-04-04 | United Technologies Corporation | Fuel injection system |
US4920740A (en) * | 1987-11-23 | 1990-05-01 | Sundstrand Corporation | Starting of turbine engines |
US5321949A (en) * | 1991-07-12 | 1994-06-21 | General Electric Company | Staged fuel delivery system with secondary distribution valve |
US5339636A (en) * | 1992-12-04 | 1994-08-23 | United Technologies Corporation | Fuel splitter valve assembly for gas turbine |
-
1996
- 1996-04-18 GB GB9608027A patent/GB2312250A/en not_active Withdrawn
-
1997
- 1997-04-07 DE DE69719588T patent/DE69719588T2/en not_active Expired - Lifetime
- 1997-04-07 EP EP97302387A patent/EP0802310B1/en not_active Expired - Lifetime
- 1997-04-16 US US08/834,433 patent/US5884483A/en not_active Expired - Lifetime
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1437397A (en) * | 1972-09-05 | 1976-05-26 | Gen Electric | Gas turbine engine fuel distribution systems |
US4305255A (en) * | 1978-11-20 | 1981-12-15 | Rolls-Royce Limited | Combined pilot and main burner |
US5289685A (en) * | 1992-11-16 | 1994-03-01 | General Electric Company | Fuel supply system for a gas turbine engine |
GB2285285A (en) * | 1993-12-09 | 1995-07-05 | United Technologies Corp | Fuel staging system |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6857272B2 (en) | 2001-07-18 | 2005-02-22 | Rolls-Royce Plc | Fuel delivery system |
US10288294B2 (en) | 2015-03-20 | 2019-05-14 | Rolls-Royce Plc | Combustion staging system |
Also Published As
Publication number | Publication date |
---|---|
EP0802310B1 (en) | 2003-03-12 |
EP0802310A3 (en) | 1999-10-06 |
EP0802310A2 (en) | 1997-10-22 |
GB9608027D0 (en) | 1996-06-19 |
US5884483A (en) | 1999-03-23 |
DE69719588D1 (en) | 2003-04-17 |
DE69719588T2 (en) | 2003-12-11 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US5884483A (en) | Fuel system for a gas turbine engine | |
US4305255A (en) | Combined pilot and main burner | |
US5339636A (en) | Fuel splitter valve assembly for gas turbine | |
GB2563660B (en) | Combustion staging system for fuel injectors of a gas turbine engine | |
US20200393128A1 (en) | Variable geometry rotating detonation combustor | |
US5003771A (en) | Fuel distribution valve for a combustion chamber | |
GB2563659B (en) | Combustion staging system for fuel injectors of a gas turbine engine | |
CN111788431B (en) | Combustor assembly fuel control | |
US2693675A (en) | Jet engine fuel control system | |
US11131461B2 (en) | Effervescent atomizing structure and method of operation for rotating detonation propulsion system | |
US2933887A (en) | Compound gas turbine engine with control for low-pressure rotor | |
US20180163630A1 (en) | Fuel supply system | |
US10830444B2 (en) | Combustion staging system | |
US10982858B2 (en) | Combustion staging system | |
US3420055A (en) | Fuel control systems | |
EP0734489A1 (en) | Pilot fuel cooled flow divider valve for a staged combustor | |
US3991569A (en) | Fuel control system for gas turbine engine | |
US2989842A (en) | Fuel pumping system for engines having afterburners | |
US6848250B2 (en) | Fuel injection system for a combustion engine | |
GB1232318A (en) | ||
US2941358A (en) | Compressor pressure limiter for gas turbine engines | |
US3714784A (en) | Fuel supply systems for jet aircraft engines | |
US3604210A (en) | Gas turbine engine | |
GB1513738A (en) | Fuel control system for a gas turbine engine | |
GB760806A (en) | Improvements in or relating to gas-turbine engines |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |