US20060260317A1 - Nested channel ducts for nozzle construction and the like - Google Patents
Nested channel ducts for nozzle construction and the like Download PDFInfo
- Publication number
- US20060260317A1 US20060260317A1 US11/338,827 US33882706A US2006260317A1 US 20060260317 A1 US20060260317 A1 US 20060260317A1 US 33882706 A US33882706 A US 33882706A US 2006260317 A1 US2006260317 A1 US 2006260317A1
- Authority
- US
- United States
- Prior art keywords
- fuel
- conduit
- coolant
- manifold
- channel
- 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.)
- Abandoned
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23K—FEEDING FUEL TO COMBUSTION APPARATUS
- F23K5/00—Feeding or distributing other fuel to combustion apparatus
- F23K5/02—Liquid fuel
- F23K5/06—Liquid fuel from a central source to a plurality of 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
- F02C7/222—Fuel flow conduits, e.g. manifolds
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
Definitions
- the present invention relates generally to gas turbine engines, and more particularly to a nested channel configuration for use in fuel manifolds, nozzle stems and the like.
- Fuel nozzles which supply fuel to a combustion chamber in a gas turbine engine are well known in the art. Generally, a plurality of circumferentially distributed fuel nozzles forming a nozzle array in the combustion chamber are used to ensure sufficient distribution of the fuel.
- the fuel nozzle array typically comprises a plurality of injector tip assemblies for atomizing fuel into the combustion chamber, the injector tips being connected to an outer fuel manifold via nozzle stems.
- Some conventional nozzle systems define duel adjacent fuel passages, sometimes concentrically disposed within an outer tube.
- a stem comprised of a solid piece of material having adjacent slotted fuel conduits.
- the distinct slots, formed side by side, define primary and secondary fuel conduits extending between the inlet and outlet of the nozzle stem, and are sealed by a brazed cover plate.
- a gas turbine engine fuel nozzle having a spray tip assembly in flow communication with a fuel source
- the fuel nozzle comprising: a fuel-conveying member comprising a stepped channel formed in a surface of the fuel-conveying member for providing fuel flow to the spray tip assembly; at least a first inner sealing plate being disposed within the stepped channel and dividing the stepped channel into at least a primary and a secondary discrete nested conduit; and an outer sealing plate being engaged with the surface for enclosing the stepped channel; whereby each discrete nested conduit is adapted for directing an independent fuel flow from the fuel source to the spray tip assembly.
- a method of manufacturing a gas turbine engine fuel nozzle having multiple discrete fuel conduits for directing independent fuel flows from a fuel source to a spray tip assembly comprising: providing a fuel-conveying member formed from a single solid piece of material; machining a single stepped channel in a surface of the fuel-conveying member, the stepped channel defining at least primary and secondary nested slots, the secondary slot defining a larger cross-sectional area than the primary slot and being immediately open to the surface; fixing at least a first inner sealing plate having a width greater than a width of the primary slot, within the secondary slot with the first inner sealing plate abutting a shoulder formed by the stepped channel, thereby dividing the stepped channel into a primary discrete nested fuel conduit and the nested secondary slot; and fixing an outer channel sealing plate to the fuel-conveying member to enclose the secondary slot thereby forming a secondary discrete nested fuel conduit.
- FIG. 1 is a cross-sectional view of a gas turbine engine comprising a fuel injection system according to the present invention.
- FIG. 2 is a perspective view of a first embodiment of a fuel injection system according to the present invention comprising an annular, nested channel fuel manifold ring.
- FIG. 3 is a cross-sectional view of the nested channel fuel manifold ring of FIG. 2 .
- FIG. 4 is a cross-sectional view of an alternate fuel manifold ring having an additional nested channel.
- FIG. 5 is a perspective view of a second embodiment of a fuel injection system according to the present invention comprising a fuel nozzle stem having nested fuel channels formed therein.
- FIG. 6 is a cross-sectional view of the nested channel fuel nozzle stem of FIG. 5 .
- FIG. 1 illustrates a gas turbine engine 10 generally comprising, in serial flow communication, a fan 12 through which ambient air is propelled, a multistage compressor section 14 for pressurizing the air, a combustion section 16 in which the compressed air is mixed with fuel atomized into a combustion chamber 17 by a fuel injection system comprising a fuel injection nozzle assembly 20 , the mixture being subsequently ignited for generating hot combustion gases before passing through a turbine section 18 for extracting energy from the combustion gases.
- the fuel injection nozzle assembly 20 comprises an annular fuel manifold ring 22 generally disposed within the combustion chamber 17 of the engine, and mounted via several integral attachment lugs 28 for fixing the annular ring 22 to an appropriate support structure.
- the annular fuel manifold ring 22 comprises a plurality of fuel injector spray tip assemblies 24 thereon, which atomize the fuel for combustion.
- the exterior of the annular ring 22 comprises an outer heat shield 26 covering the ring. This provides the fuel manifold ring thermal protection from the high temperature environment of the combustion chamber.
- a primary fuel inlet pipe 30 and a secondary fuel inlet pipe 32 provide dual, independent fuel feeds to the manifold, which distributes the two fuel supplies to the spray tip assemblies.
- the spray tip assemblies 24 are directly mounted to the annular fuel manifold ring, without requiring conventionally used nozzle stems which are traditionally required to link, in fluid flow communication, the spray tip assemblies with each distinct fuel manifold for each fuel inlet source.
- the above features are generally known in the art.
- the annular fuel manifold ring 22 is preferably formed from a single solid piece of material and comprises a single stepped channel 36 formed in an outer peripheral surface 38 of the manifold ring which is covered by a protective outer heat shield 26 .
- the stepped channel 36 is preferably formed by a single machining operation, for example by a single milling or routing step using a multi-diametered bit of a predetermined size to create the number and size of the nested slots comprising the entire stepped channel 36 .
- the nested slots defined by the stepped slot that is machined, or otherwise formed, in the fuel manifold ring, create annular fuel galleries which permit circumferential distribution of independently controllable fuel supplies to be fed to each spray tip assembly.
- the channel 36 has a length which is defined as the circumferential length or circumference of the channel.
- the annular stepped channel 36 comprises at least two nested fuel conduits; namely a primary nested fuel conduit 40 and secondary nested fuel conduit 42 .
- the annular primary fuel conduit is located in the manifold ring closest to the spray tip assemblies, and preferably (to facilitate manufacture) is much smaller in cross-sectional area than the annular secondary nested fuel conduit 42 , which opens immediately to the peripheral surface 38 in which the stepped channel 36 is formed.
- a first inner sealing member or plate 44 sized such that it fits within the secondary conduit portion of the stepped channel and is larger than the width of the primary conduit (i.e.
- the first inner sealing plate 44 for the annular fuel manifold ring 22 is preferably also an annular ring plate, substantially extending around the full circumference of manifold ring.
- An outer stepped channel sealing member or plate 46 is similarly fixed to the fuel manifold ring 22 by brazing or other similar fastening method, against a second shoulder 45 formed within the stepped channel for receiving the annular outer sealing plate ring 46 abutted therein.
- the outer sealing ring plate 46 could also be brazed directly to the outer peripheral surface 38 of the manifold ring, without the need for the second shoulder 45 in the stepped channel 36 .
- the two sealing plates thereby divide the single stepped channel 36 into two discrete, nested fuel conduits that are sealed from one another and which can supply independent fuel supplies to the spray tip assemblies, primary nested fuel conduit 40 and secondary nested fuel conduit 42 .
- This therefore permits the use of a single-piece fuel manifold, having at least two discrete fuel galleries formed therein in a simple and cost effective manner. This eliminates the need for employing fuel nozzle stems and conventional fuel nozzle injector arrays comprising hundreds of sub-components merely to connect an exteriorly located fuel manifold to the spray tip assemblies in the combustion chamber.
- the primary and secondary annular nested fuel conduits 40 and 42 permit circumferential distribution of the primary and secondary fuel supply around the fuel manifold ring.
- fuel outlet passage holes are formed, by drilling or otherwise, in the manifold ring body substantially perpendicularly to the outer peripheral surface 38 , to enable fluid flow communication between the nested fuel conduits and the spray tip assembly 24 .
- primary fuel conduit outlet passage 48 permits primary fuel flow from the primary fuel conduit 40 to be fed into the primary distributor 54 of the spray tip assembly
- secondary fuel conduit outlet passage 50 permits secondary fuel flow from the secondary fuel conduit 42 to be fed into the annular secondary fuel swirling cavity 63 of the spray tip assembly 24 .
- Such spray tip assemblies typically also comprise a valve member 52 disposed within the primary distributor 54 for regulating primary fuel flow through a primary cone 56 , protected by a primary heat shield 58 , before being ejected by a primary fuel nozzle tip 59 .
- a secondary fuel swirler 60 disposed substantially concentrically about the primary distributor, comprises an annular secondary fuel swirling cavity, which swirls the secondary fuel flow before it is ejected through annular secondary fuel nozzle tip 61 .
- An outer air swirler 62 comprises a plurality of circumferentially spaced air passages 64 which convey air flow for blending with the primary and secondary fuel sprays issuing from the primary and secondary spray orifices, 59 and 61 respectively, of the spray tip assembly.
- this embodiment of an annular fuel manifold ring 122 comprises an alternately-shaped stepped channel 136 machined in the solid, one-piece material of the manifold ring.
- the stepped channel 136 comprises an additional or auxiliary channel 172 , therein.
- a primary nested fuel conduit 140 is formed by fixing the first inner annular sealing member or plate 144 against a first shoulder 143 , thereby dividing the primary fuel conduit 140 from the secondary nested fuel conduit 142 .
- the secondary nested fuel conduit 142 is enclosed by a second inner sealing member or plate 170 abutted with, and fixed against, second shoulder 145 within the stepped channel 136 .
- annular auxiliary channel 172 is further axially enclosed by an outer sealing member or plate 146 , fixed against the outer peripheral surface 138 of the annular fuel manifold ring 122 .
- a primary conduit outlet passage 148 and a secondary conduit outlet passage 150 formed in the manifold ring perpendicularly to the outer peripheral surface 138 at predetermined circumferential locations of the manifold ring corresponding to location of the spray tip assemblies, provide dual independent fuel feeds to each spray tip assembly.
- the auxiliary channel 172 can be used to carry a coolant, such as for example recirculated fuel, which will draw heat from the ring.
- the coolant flow in the auxiliary channel 172 is independent of the quantity of fuel being delivered to the engine. This is particularly needed during low power operation, when less fuel flows through the conduits of the manifold, and therefore more heat is absorbed from the combustion chamber by the entire manifold ring. This reduces fuel coking within the fuel manifold, which can occur if sufficient fuel flow is not maintained to cool the manifold ring.
- Each conduit, namely the primary fuel conduit 140 , the secondary fuel conduit 142 and the auxiliary cooling conduit 172 each has its own inlet feed line, such that the fuel rates and the coolant flow rate can be independently controlled. Independent control of the primary and secondary fuel flows and independent feeding of each spray tip from the annular conduits providing circumferential fuel distribution, also permits fuel staging, wherein specific amounts of fuel are partitioned to specific circumferential locations of the combustion chamber to enhance ignition or to control emissions.
- the present invention may also be used to provide multiple nested channels for providing discrete fuel conduits in a fuel nozzle stem.
- a fuel nozzle stem 200 comprises a central stem body 202 and a stem inlet end 204 and a stem outlet end 206 .
- a stepped channel 236 is formed in a first outer surface 238 of the stem body 202 .
- the channel is divided by an inner sealing member or plate 244 , abutted with, and preferably brazed to, shoulder 243 within the stepped channel, thereby defining a primary nested fuel conduit 240 and a preferably larger secondary nested fuel conduit 242 .
- the primary and secondary conduits 240 and 242 are substantially linear, rather than being annular.
- the channel 236 has a length which is defined as the linear or longitudinal length of the channel.
- the secondary nested fuel conduit 242 is enclosed by an outer sealing member or plate 246 , preferably fixed to the outer surface 238 of the stem body, again preferably by brazing.
- the primary and secondary fuel conduits thereby provide discrete fuel flow passages between the inlet end 204 and the outlet end 206 of the stem, which are adapted to be engaged with a fuel manifold adapter and a nozzle spray tip assembly, respectively. This permits at least two discrete fuel flows through the nozzle stem to a spray tip assembly.
- the entire fuel nozzle stem 200 is fitted within a surrounding cylindrical outer shield 278 , which is can be brazed to the stem member to provide an element of heat protection.
- the stem body 202 can also comprise auxiliary cooling channels 272 formed therein according to the present invention.
- the auxiliary cooling channels 272 are on opposing sides of the stem body in outer lateral surfaces 280 of the stem body, substantially perpendicular to the first outer surface 238 with the stepped channel 236 formed therein.
- Auxiliary channel outer sealing plates 273 enclose the auxiliary cooling channels.
- the two opposing auxiliary coolant channels 272 are in fluid flow communication at the outlet end 206 of the stem, such that they can provide inlet and outlet passages for coolant flowing through to stem to provide cooling thereof.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
A multiple conduit system for a gas turbine engine, the multiple conduit system extending between a plurality of conduit inlet and outlets. A channel, adapted for conveying fuel flow, is formed in a surface of a gas turbine engine component. The channel includes at least a first discrete conduit and a second discrete conduit. The first and second discrete conduits are each adapted to direct an independent fluid flow from respective inlets to respective outlets.
Description
- This application is a continuation of U.S. patent application Ser. No. 10/231,334 filed Aug. 30, 2002, which was allowed on Oct. 25, 2005, and the specification of which is incorporated herein by reference.
- The present invention relates generally to gas turbine engines, and more particularly to a nested channel configuration for use in fuel manifolds, nozzle stems and the like.
- Fuel nozzles which supply fuel to a combustion chamber in a gas turbine engine are well known in the art. Generally, a plurality of circumferentially distributed fuel nozzles forming a nozzle array in the combustion chamber are used to ensure sufficient distribution of the fuel. The fuel nozzle array typically comprises a plurality of injector tip assemblies for atomizing fuel into the combustion chamber, the injector tips being connected to an outer fuel manifold via nozzle stems.
- Some conventional nozzle systems define duel adjacent fuel passages, sometimes concentrically disposed within an outer tube. In an effort to provide a dual passage stem member which is relatively simpler and more economical to manufacture, it is also known to use a stem comprised of a solid piece of material having adjacent slotted fuel conduits. The distinct slots, formed side by side, define primary and secondary fuel conduits extending between the inlet and outlet of the nozzle stem, and are sealed by a brazed cover plate.
- Prior art multiple channel systems are cumbersome, difficult to manufacture and maintain, and heavy. Accordingly, improvements are desirable.
- It is an object of the present invention to provide an improved fuel injection system that is simpler and more economical to manufacture.
- It is a further object of the present invention to provide a fuel injection system that, among other things, eliminates the need for multiple independent fuel manifolds and for complex fuel nozzle stems.
- Therefore, in accordance with the present invention, there is provided a gas turbine engine fuel nozzle having a spray tip assembly in flow communication with a fuel source, the fuel nozzle comprising: a fuel-conveying member comprising a stepped channel formed in a surface of the fuel-conveying member for providing fuel flow to the spray tip assembly; at least a first inner sealing plate being disposed within the stepped channel and dividing the stepped channel into at least a primary and a secondary discrete nested conduit; and an outer sealing plate being engaged with the surface for enclosing the stepped channel; whereby each discrete nested conduit is adapted for directing an independent fuel flow from the fuel source to the spray tip assembly.
- There is also provided, in accordance with the present invention, a method of manufacturing a gas turbine engine fuel nozzle having multiple discrete fuel conduits for directing independent fuel flows from a fuel source to a spray tip assembly, the method comprising: providing a fuel-conveying member formed from a single solid piece of material; machining a single stepped channel in a surface of the fuel-conveying member, the stepped channel defining at least primary and secondary nested slots, the secondary slot defining a larger cross-sectional area than the primary slot and being immediately open to the surface; fixing at least a first inner sealing plate having a width greater than a width of the primary slot, within the secondary slot with the first inner sealing plate abutting a shoulder formed by the stepped channel, thereby dividing the stepped channel into a primary discrete nested fuel conduit and the nested secondary slot; and fixing an outer channel sealing plate to the fuel-conveying member to enclose the secondary slot thereby forming a secondary discrete nested fuel conduit.
- Further features and advantages of the present invention will become apparent from the following detailed description, taken in combination with the appended drawings, in which:
-
FIG. 1 is a cross-sectional view of a gas turbine engine comprising a fuel injection system according to the present invention. -
FIG. 2 is a perspective view of a first embodiment of a fuel injection system according to the present invention comprising an annular, nested channel fuel manifold ring. -
FIG. 3 is a cross-sectional view of the nested channel fuel manifold ring ofFIG. 2 . -
FIG. 4 is a cross-sectional view of an alternate fuel manifold ring having an additional nested channel. -
FIG. 5 is a perspective view of a second embodiment of a fuel injection system according to the present invention comprising a fuel nozzle stem having nested fuel channels formed therein. -
FIG. 6 is a cross-sectional view of the nested channel fuel nozzle stem ofFIG. 5 . -
FIG. 1 illustrates agas turbine engine 10 generally comprising, in serial flow communication, afan 12 through which ambient air is propelled, amultistage compressor section 14 for pressurizing the air, acombustion section 16 in which the compressed air is mixed with fuel atomized into acombustion chamber 17 by a fuel injection system comprising a fuelinjection nozzle assembly 20, the mixture being subsequently ignited for generating hot combustion gases before passing through aturbine section 18 for extracting energy from the combustion gases. - Referring to
FIG. 2 , the fuelinjection nozzle assembly 20 comprises an annularfuel manifold ring 22 generally disposed within thecombustion chamber 17 of the engine, and mounted via severalintegral attachment lugs 28 for fixing theannular ring 22 to an appropriate support structure. The annularfuel manifold ring 22 comprises a plurality of fuel injectorspray tip assemblies 24 thereon, which atomize the fuel for combustion. The exterior of theannular ring 22 comprises anouter heat shield 26 covering the ring. This provides the fuel manifold ring thermal protection from the high temperature environment of the combustion chamber. A primaryfuel inlet pipe 30 and a secondaryfuel inlet pipe 32 provide dual, independent fuel feeds to the manifold, which distributes the two fuel supplies to the spray tip assemblies. Thespray tip assemblies 24 are directly mounted to the annular fuel manifold ring, without requiring conventionally used nozzle stems which are traditionally required to link, in fluid flow communication, the spray tip assemblies with each distinct fuel manifold for each fuel inlet source. The above features are generally known in the art. - Referring now to
FIG. 3 more clearly showing the details of the fuelinjection nozzle assembly 20 according to the present invention, the annularfuel manifold ring 22 is preferably formed from a single solid piece of material and comprises a single steppedchannel 36 formed in an outerperipheral surface 38 of the manifold ring which is covered by a protectiveouter heat shield 26. Thestepped channel 36 is preferably formed by a single machining operation, for example by a single milling or routing step using a multi-diametered bit of a predetermined size to create the number and size of the nested slots comprising the entirestepped channel 36. Once provided, as described below, the nested slots, defined by the stepped slot that is machined, or otherwise formed, in the fuel manifold ring, create annular fuel galleries which permit circumferential distribution of independently controllable fuel supplies to be fed to each spray tip assembly. Thechannel 36 has a length which is defined as the circumferential length or circumference of the channel. - The annular
stepped channel 36 comprises at least two nested fuel conduits; namely a primarynested fuel conduit 40 and secondarynested fuel conduit 42. The annular primary fuel conduit is located in the manifold ring closest to the spray tip assemblies, and preferably (to facilitate manufacture) is much smaller in cross-sectional area than the annular secondarynested fuel conduit 42, which opens immediately to theperipheral surface 38 in which thestepped channel 36 is formed. A first inner sealing member orplate 44, sized such that it fits within the secondary conduit portion of the stepped channel and is larger than the width of the primary conduit (i.e. to seal it), is fixed against afirst shoulder 43 formed in the stepped channel between the primary and secondary nested conduits, by way of brazing or another fastening/sealing method. The firstinner sealing plate 44 for the annularfuel manifold ring 22, is preferably also an annular ring plate, substantially extending around the full circumference of manifold ring. An outer stepped channel sealing member orplate 46 is similarly fixed to thefuel manifold ring 22 by brazing or other similar fastening method, against asecond shoulder 45 formed within the stepped channel for receiving the annular outersealing plate ring 46 abutted therein. The outersealing ring plate 46 could also be brazed directly to the outerperipheral surface 38 of the manifold ring, without the need for thesecond shoulder 45 in thestepped channel 36. The two sealing plates thereby divide the single steppedchannel 36 into two discrete, nested fuel conduits that are sealed from one another and which can supply independent fuel supplies to the spray tip assemblies, primarynested fuel conduit 40 and secondarynested fuel conduit 42. This therefore permits the use of a single-piece fuel manifold, having at least two discrete fuel galleries formed therein in a simple and cost effective manner. This eliminates the need for employing fuel nozzle stems and conventional fuel nozzle injector arrays comprising hundreds of sub-components merely to connect an exteriorly located fuel manifold to the spray tip assemblies in the combustion chamber. - The primary and secondary annular
nested fuel conduits spray tip assembly 24 mounted to theannular manifold ring 22, fuel outlet passage holes are formed, by drilling or otherwise, in the manifold ring body substantially perpendicularly to the outerperipheral surface 38, to enable fluid flow communication between the nested fuel conduits and thespray tip assembly 24. Specifically, primary fuelconduit outlet passage 48 permits primary fuel flow from theprimary fuel conduit 40 to be fed into theprimary distributor 54 of the spray tip assembly, and secondary fuelconduit outlet passage 50 permits secondary fuel flow from thesecondary fuel conduit 42 to be fed into the annular secondaryfuel swirling cavity 63 of thespray tip assembly 24. - Such spray tip assemblies typically also comprise a
valve member 52 disposed within theprimary distributor 54 for regulating primary fuel flow through aprimary cone 56, protected by aprimary heat shield 58, before being ejected by a primaryfuel nozzle tip 59. Asecondary fuel swirler 60 disposed substantially concentrically about the primary distributor, comprises an annular secondary fuel swirling cavity, which swirls the secondary fuel flow before it is ejected through annular secondaryfuel nozzle tip 61. Anouter air swirler 62 comprises a plurality of circumferentially spacedair passages 64 which convey air flow for blending with the primary and secondary fuel sprays issuing from the primary and secondary spray orifices, 59 and 61 respectively, of the spray tip assembly. - Referring to
FIG. 4 , this embodiment of an annularfuel manifold ring 122 comprises an alternately-shapedstepped channel 136 machined in the solid, one-piece material of the manifold ring. Thestepped channel 136 comprises an additional orauxiliary channel 172, therein. As above, a primarynested fuel conduit 140 is formed by fixing the first inner annular sealing member orplate 144 against afirst shoulder 143, thereby dividing theprimary fuel conduit 140 from the secondarynested fuel conduit 142. The secondarynested fuel conduit 142 is enclosed by a second inner sealing member orplate 170 abutted with, and fixed against,second shoulder 145 within thestepped channel 136. As described above, although several attachment and sealing methods for fixing the sealing plates to the manifold ring can be used, they are preferably brazed thereto. The annularauxiliary channel 172 is further axially enclosed by an outer sealing member orplate 146, fixed against the outerperipheral surface 138 of the annularfuel manifold ring 122. As described above, a primaryconduit outlet passage 148 and a secondaryconduit outlet passage 150, formed in the manifold ring perpendicularly to the outerperipheral surface 138 at predetermined circumferential locations of the manifold ring corresponding to location of the spray tip assemblies, provide dual independent fuel feeds to each spray tip assembly. - The
auxiliary channel 172 can be used to carry a coolant, such as for example recirculated fuel, which will draw heat from the ring. The coolant flow in theauxiliary channel 172 is independent of the quantity of fuel being delivered to the engine. This is particularly needed during low power operation, when less fuel flows through the conduits of the manifold, and therefore more heat is absorbed from the combustion chamber by the entire manifold ring. This reduces fuel coking within the fuel manifold, which can occur if sufficient fuel flow is not maintained to cool the manifold ring. Each conduit, namely theprimary fuel conduit 140, thesecondary fuel conduit 142 and theauxiliary cooling conduit 172, each has its own inlet feed line, such that the fuel rates and the coolant flow rate can be independently controlled. Independent control of the primary and secondary fuel flows and independent feeding of each spray tip from the annular conduits providing circumferential fuel distribution, also permits fuel staging, wherein specific amounts of fuel are partitioned to specific circumferential locations of the combustion chamber to enhance ignition or to control emissions. - The present invention may also be used to provide multiple nested channels for providing discrete fuel conduits in a fuel nozzle stem.
- Referring to
FIG. 5 andFIG. 6 , afuel nozzle stem 200 comprises acentral stem body 202 and astem inlet end 204 and astem outlet end 206. A steppedchannel 236 is formed in a firstouter surface 238 of thestem body 202. The channel is divided by an inner sealing member orplate 244, abutted with, and preferably brazed to,shoulder 243 within the stepped channel, thereby defining a primary nestedfuel conduit 240 and a preferably larger secondary nestedfuel conduit 242. Unlike the nested fuel conduits described previously, the primary andsecondary conduits channel 236 has a length which is defined as the linear or longitudinal length of the channel. The secondary nestedfuel conduit 242 is enclosed by an outer sealing member orplate 246, preferably fixed to theouter surface 238 of the stem body, again preferably by brazing. The primary and secondary fuel conduits thereby provide discrete fuel flow passages between theinlet end 204 and theoutlet end 206 of the stem, which are adapted to be engaged with a fuel manifold adapter and a nozzle spray tip assembly, respectively. This permits at least two discrete fuel flows through the nozzle stem to a spray tip assembly. Typically, the entirefuel nozzle stem 200 is fitted within a surrounding cylindricalouter shield 278, which is can be brazed to the stem member to provide an element of heat protection. Thestem body 202 can also compriseauxiliary cooling channels 272 formed therein according to the present invention. In the example shown, theauxiliary cooling channels 272 are on opposing sides of the stem body in outerlateral surfaces 280 of the stem body, substantially perpendicular to the firstouter surface 238 with the steppedchannel 236 formed therein. Auxiliary channel outer sealing plates 273 enclose the auxiliary cooling channels. The two opposingauxiliary coolant channels 272 are in fluid flow communication at theoutlet end 206 of the stem, such that they can provide inlet and outlet passages for coolant flowing through to stem to provide cooling thereof. - While the above description constitutes the preferred embodiments, it will be appreciated that the present invention is susceptible to modification and change without departing from the fair meaning of the accompanying claims. For example, the present invention can offer reliability and weight benefits in any gas turbine engine application wherever multiple hydraulic or other fluid conduits are required or desired. Also, the stepped construction of the channel is preferred, but other configurations will be apparent to those skilled in the art. Still other modifications and applications beyond those described will be apparent to those skilled in the art.
Claims (20)
1-20. (canceled)
21. A fuel manifold for a gas turbine engine, the fuel manifold comprising an annular body defining at least one fuel conduit therein, the fuel conduit having a fuel inlet defined in the body in communication with a fuel source and a fuel outlet defined in the body in communication with at least one fuel nozzle, a coolant conduit being defined within the body in heat transfer communication with the fuel conduit, the coolant conduit having at least one coolant inlet and at least one coolant outlet defined in the body, the fuel and coolant conduits being fed independently from each other such as to respectively direct fluid flow therethrough independently of each other.
22. The fuel manifold as defined in claim 21 , wherein the body includes a channel formed therein, the channel defining at least one shoulder along a length thereof corresponding to a change in width of the channel, at least a first inner sealing member being disposed within the channel and mounted to the shoulder substantially along the length of the channel, the fuel and coolant conduits being defined in nested relationship in the channel and sealingly separated from one another by the first inner sealing member, and an outer sealing member enclosing the channel substantially along its length to define an outer one of the fuel and coolant conduits.
23. The fuel manifold as defined in claim 22 , wherein the first inner sealing member abuts the shoulder.
24. The fuel manifold as defined in claim 22 , wherein the outer sealing member is engaged to an outer surface of the body.
25. The fuel manifold as defined in claim 21 , wherein the coolant conduit has a larger cross-sectional area than the fuel conduit.
26. The fuel manifold as defined in claim 21 , wherein the body includes an additional fuel conduit defined therein, the additional fuel conduit having an additional fuel inlet and an additional fuel outlet defined in the body, the coolant conduit being in heat transfer communication with the additional fuel conduit, the additional fuel conduit being fed independently from the fuel and coolant conduits such as to direct fluid flow independently of the fuel and coolant conduits.
27. The fuel manifold as defined in claim 22 , wherein a second inner sealing member is disposed within the channel along the length thereof and separates the fuel conduit from an additional fuel conduit also defined in the channel, the additional fuel conduit being fed independently from the fuel and coolant conduits.
28. The fuel manifold as defined in claim 21 , wherein the fuel manifold is provided in a single solid piece of material.
29. A fuel manifold for a gas turbine engine, the fuel manifold comprising:
an annular body defining at least one fuel conduit and at least one coolant conduit therein, the fuel conduit circulating fuel from a fuel inlet to at least one fuel nozzle, and the coolant conduit circulating coolant therein from a coolant inlet to a coolant outlet to absorb heat from the fuel manifold;
means for controlling a flow of the fuel in the fuel conduit; and
means for controlling a flow of the coolant in the coolant conduit;
wherein the fuel flow control means and the coolant flow control means are independent from one another.
30. The fuel manifold as defined in claim 29 , wherein the fuel flow control means includes a first inlet feed line feeding the fuel inlet and the coolant flow control means includes a second inlet feed line feeding the coolant inlet.
31. The fuel manifold as defined in claim 29 , wherein the body includes a channel formed therein, the channel defining at least one shoulder along a length thereof corresponding to a change in width of the channel, at least a first inner sealing member being disposed within the channel and mounted to the shoulder substantially along the length of the channel, the fuel and coolant conduits being defined in nested relationship in the channel and sealingly separated from one another by the first inner sealing member, and an outer sealing member enclosing the channel substantially along its length to define an outer one of the fuel and coolant conduits.
32. The fuel manifold as defined in claim 29 , wherein the coolant conduit has a larger cross-sectional area than the fuel conduit.
33. The fuel manifold as defined in claim 29 , wherein the body includes an additional fuel conduit defined therein, the fuel additional conduit circulating fuel from an additional fuel inlet to at least one additional fuel outlet, and the manifold further includes means for controlling a flow of the fuel in the additional fuel conduit, and wherein the additional fuel flow control means are independent from the fuel flow control means and the coolant flow control means.
34. The fuel manifold as defined in claim 33 , wherein the additional fuel flow control means includes a third inlet feed line feeding the additional fuel inlet, the third inlet feed line being independent from the first and second inlet feed lines.
35. The fuel manifold as defined in claim 33 , wherein the body includes a channel formed therein, first and second inner sealing members being mounted within the channel along a length thereof in spaced apart relationship, the fuel, additional fuel and coolant conduits being defined in the channel and sealingly separated from one another by the first and second sealing members, and an outer sealing member enclosing the channel substantially along its length to define an outer one of the conduits.
36. The fuel manifold as defined in claim 29 , wherein the fuel manifold is provided in a single solid piece of material.
37. A method of drawing heat from a manifold ring in a gas turbine engine, the method comprising:
providing the manifold ring having a body with at least one fuel conduit and at least one coolant conduit defined therein, the fuel conduit being in fluid communication with at least one fuel nozzle;
circulating a coolant through the cooling conduit from an inlet to an outlet thereof to absorb heat from the manifold ring; and
controlling a flow of the coolant within the cooling conduit independently of a fuel flow to the fuel nozzle through the fuel conduit.
38. The method as defined in claim 37 , wherein controlling the flow of the coolant includes feeding the coolant through the inlet independently from a fuel feed to the fuel conduit.
39. The method as defined in claim 37 , wherein circulating the coolant through the cooling conduit includes circulating fuel through the cooling conduit.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/338,827 US20060260317A1 (en) | 2002-08-30 | 2006-01-25 | Nested channel ducts for nozzle construction and the like |
US12/124,593 US8074452B2 (en) | 2002-08-30 | 2008-05-21 | Nested channel ducts for nozzle construction and the like |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/231,334 US7028484B2 (en) | 2002-08-30 | 2002-08-30 | Nested channel ducts for nozzle construction and the like |
US11/338,827 US20060260317A1 (en) | 2002-08-30 | 2006-01-25 | Nested channel ducts for nozzle construction and the like |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/231,334 Continuation US7028484B2 (en) | 2002-08-30 | 2002-08-30 | Nested channel ducts for nozzle construction and the like |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/124,593 Division US8074452B2 (en) | 2002-08-30 | 2008-05-21 | Nested channel ducts for nozzle construction and the like |
Publications (1)
Publication Number | Publication Date |
---|---|
US20060260317A1 true US20060260317A1 (en) | 2006-11-23 |
Family
ID=31976687
Family Applications (3)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/231,334 Expired - Lifetime US7028484B2 (en) | 2002-08-30 | 2002-08-30 | Nested channel ducts for nozzle construction and the like |
US11/338,827 Abandoned US20060260317A1 (en) | 2002-08-30 | 2006-01-25 | Nested channel ducts for nozzle construction and the like |
US12/124,593 Active 2025-07-15 US8074452B2 (en) | 2002-08-30 | 2008-05-21 | Nested channel ducts for nozzle construction and the like |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/231,334 Expired - Lifetime US7028484B2 (en) | 2002-08-30 | 2002-08-30 | Nested channel ducts for nozzle construction and the like |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/124,593 Active 2025-07-15 US8074452B2 (en) | 2002-08-30 | 2008-05-21 | Nested channel ducts for nozzle construction and the like |
Country Status (6)
Country | Link |
---|---|
US (3) | US7028484B2 (en) |
EP (1) | EP1546527B1 (en) |
JP (1) | JP2005536679A (en) |
CA (1) | CA2494950C (en) |
DE (1) | DE60326611D1 (en) |
WO (1) | WO2004020805A1 (en) |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20050188699A1 (en) * | 2004-02-27 | 2005-09-01 | Pratt & Whitney Canada Corp. | Apparatus for fuel transport and the like |
US20060218926A1 (en) * | 2005-04-01 | 2006-10-05 | Pratt & Whitney Canada Corp. | Fuel conveying member with heat pipe |
US20090320483A1 (en) * | 2008-06-26 | 2009-12-31 | General Electric Company | Variable Orifice Plug for Turbine Fuel Nozzle |
US20120047900A1 (en) * | 2009-03-17 | 2012-03-01 | Boettcher Andreas | Burner Assembly |
US20120151928A1 (en) * | 2010-12-17 | 2012-06-21 | Nayan Vinodbhai Patel | Cooling flowpath dirt deflector in fuel nozzle |
CN106051824A (en) * | 2015-04-14 | 2016-10-26 | 通用电气公司 | Thermally-coupled fuel manifold |
US20160319780A1 (en) * | 2015-04-29 | 2016-11-03 | Mudassir Ahmed | Novel design of an effervescent atomizer with gas injection at reduced pressures |
US10317081B2 (en) | 2011-01-26 | 2019-06-11 | United Technologies Corporation | Fuel injector assembly |
Families Citing this family (45)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7028484B2 (en) * | 2002-08-30 | 2006-04-18 | Pratt & Whitney Canada Corp. | Nested channel ducts for nozzle construction and the like |
US7703286B2 (en) * | 2006-09-22 | 2010-04-27 | Pratt & Whitney Canada Corp. | Internal fuel manifold and fuel fairing interface |
US20060156733A1 (en) * | 2005-01-14 | 2006-07-20 | Pratt & Whitney Canada Corp. | Integral heater for fuel conveying member |
US7565807B2 (en) * | 2005-01-18 | 2009-07-28 | Pratt & Whitney Canada Corp. | Heat shield for a fuel manifold and method |
US7533531B2 (en) * | 2005-04-01 | 2009-05-19 | Pratt & Whitney Canada Corp. | Internal fuel manifold with airblast nozzles |
US7540157B2 (en) * | 2005-06-14 | 2009-06-02 | Pratt & Whitney Canada Corp. | Internally mounted fuel manifold with support pins |
US7559201B2 (en) * | 2005-09-08 | 2009-07-14 | Pratt & Whitney Canada Corp. | Redundant fuel manifold sealing arrangement |
US7854120B2 (en) * | 2006-03-03 | 2010-12-21 | Pratt & Whitney Canada Corp. | Fuel manifold with reduced losses |
US7942002B2 (en) * | 2006-03-03 | 2011-05-17 | Pratt & Whitney Canada Corp. | Fuel conveying member with side-brazed sealing members |
US7607226B2 (en) | 2006-03-03 | 2009-10-27 | Pratt & Whitney Canada Corp. | Internal fuel manifold with turned channel having a variable cross-sectional area |
US7765808B2 (en) * | 2006-08-22 | 2010-08-03 | Pratt & Whitney Canada Corp. | Optimized internal manifold heat shield attachment |
US8033113B2 (en) * | 2006-08-31 | 2011-10-11 | Pratt & Whitney Canada Corp. | Fuel injection system for a gas turbine engine |
US20080053096A1 (en) * | 2006-08-31 | 2008-03-06 | Pratt & Whitney Canada Corp. | Fuel injection system and method of assembly |
US7743612B2 (en) * | 2006-09-22 | 2010-06-29 | Pratt & Whitney Canada Corp. | Internal fuel manifold and fuel inlet connection |
US7926286B2 (en) * | 2006-09-26 | 2011-04-19 | Pratt & Whitney Canada Corp. | Heat shield for a fuel manifold |
US7716933B2 (en) * | 2006-10-04 | 2010-05-18 | Pratt & Whitney Canada Corp. | Multi-channel fuel manifold |
US8572976B2 (en) * | 2006-10-04 | 2013-11-05 | Pratt & Whitney Canada Corp. | Reduced stress internal manifold heat shield attachment |
US7856825B2 (en) * | 2007-05-16 | 2010-12-28 | Pratt & Whitney Canada Corp. | Redundant mounting system for an internal fuel manifold |
US7871242B2 (en) * | 2007-05-31 | 2011-01-18 | United Technologies Corporation | Single actuator controlled rotational flow balance system |
US8146365B2 (en) * | 2007-06-14 | 2012-04-03 | Pratt & Whitney Canada Corp. | Fuel nozzle providing shaped fuel spray |
US8051664B2 (en) * | 2007-07-23 | 2011-11-08 | Pratt & Whitney Canada Corp. | Pre-loaded internal fuel manifold support |
US8096131B2 (en) * | 2007-11-14 | 2012-01-17 | Pratt & Whitney Canada Corp. | Fuel inlet with crescent shaped passage for gas turbine engines |
US8578716B2 (en) * | 2008-03-22 | 2013-11-12 | United Technologies Corporation | Valve system for a gas turbine engine |
US8402744B2 (en) * | 2008-03-22 | 2013-03-26 | Pratt & Whitney Rocketdyne, Inc. | Valve system for a gas turbine engine |
US8240126B2 (en) * | 2008-03-22 | 2012-08-14 | Pratt & Whitney Rocketdyne, Inc. | Valve system for a gas turbine engine |
US8286416B2 (en) * | 2008-04-02 | 2012-10-16 | Pratt & Whitney Rocketdyne, Inc. | Valve system for a gas turbine engine |
DE102010001406B4 (en) * | 2010-01-29 | 2014-12-11 | GLOBALFOUNDRIES Dresden Module One Ltd. Liability Company & Co. KG | An exchange gate method based on an early deposited workfunction metal |
US9746185B2 (en) * | 2010-02-25 | 2017-08-29 | Siemens Energy, Inc. | Circumferential biasing and profiling of fuel injection in distribution ring |
US9188063B2 (en) | 2011-11-03 | 2015-11-17 | Delavan Inc. | Injectors for multipoint injection |
US8978383B2 (en) * | 2012-03-26 | 2015-03-17 | Pratt & Whitney Canada Corp. | Fuel manifold heat shield for a gas turbine engine |
EP2877711A1 (en) * | 2012-06-15 | 2015-06-03 | General Electric Company | Fluid conduit |
US9447974B2 (en) | 2012-09-13 | 2016-09-20 | United Technologies Corporation | Light weight swirler for gas turbine engine combustor and a method for lightening a swirler for a gas turbine engine |
US10400672B2 (en) | 2013-11-04 | 2019-09-03 | United Technologies Corporation | Cooled fuel injector system for a gas turbine engine |
US9897321B2 (en) | 2015-03-31 | 2018-02-20 | Delavan Inc. | Fuel nozzles |
US10385809B2 (en) | 2015-03-31 | 2019-08-20 | Delavan Inc. | Fuel nozzles |
US10364751B2 (en) * | 2015-08-03 | 2019-07-30 | Delavan Inc | Fuel staging |
CA2955613A1 (en) * | 2016-01-28 | 2017-07-28 | Rolls-Royce North American Technologies, Inc. | Heat exchanger integrated with fuel nozzle |
US11118784B2 (en) | 2016-01-28 | 2021-09-14 | Rolls-Royce North American Technologies Inc. | Heat exchanger integrated with fuel nozzle |
US10830150B2 (en) | 2016-01-28 | 2020-11-10 | Rolls-Royce Corporation | Fuel heat exchanger with leak management |
US10876477B2 (en) | 2016-09-16 | 2020-12-29 | Delavan Inc | Nozzles with internal manifolding |
US10775046B2 (en) | 2017-10-18 | 2020-09-15 | Rolls-Royce North American Technologies Inc. | Fuel injection assembly for gas turbine engine |
US10982856B2 (en) | 2019-02-01 | 2021-04-20 | Pratt & Whitney Canada Corp. | Fuel nozzle with sleeves for thermal protection |
US11060460B1 (en) | 2019-04-01 | 2021-07-13 | Marine Turbine Technologies, LLC | Fuel distribution system for gas turbine engine |
US11519332B1 (en) | 2021-05-11 | 2022-12-06 | Rolls-Royce North American Technologies Inc. | Fuel injector with integrated heat exchanger for use in gas turbine engines |
CN114542293B (en) * | 2022-01-17 | 2024-05-28 | 中国航发湖南动力机械研究所 | Fuel pipeline structure of gas turbine |
Family Cites Families (38)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1321976A (en) * | 1919-11-18 | Edward l | ||
US1622664A (en) * | 1923-04-21 | 1927-03-29 | Thomas E Murray | Hollow structure and method of making the same |
US2151540A (en) * | 1935-06-19 | 1939-03-21 | Varga Alexander | Heat exchanger and method of making same |
US2591880A (en) * | 1948-01-10 | 1952-04-08 | Lockheed Aircraft Corp | Liquid and vapor control valve |
US2946185A (en) * | 1953-10-29 | 1960-07-26 | Thompson Ramo Wooldridge Inc | Fuel-air manifold for an afterburner |
FR1292404A (en) * | 1961-03-24 | 1962-05-04 | Nord Aviation | Multiple injection grid for ramjet or turbojet afterburning device |
US3472025A (en) * | 1967-08-28 | 1969-10-14 | Parker Hannifin Corp | Nozzle and manifold assembly |
US3625258A (en) * | 1970-03-16 | 1971-12-07 | Warren Petroleum Corp | Multipassage pipe |
US3859787A (en) | 1974-02-04 | 1975-01-14 | Gen Motors Corp | Combustion apparatus |
US4100733A (en) * | 1976-10-04 | 1978-07-18 | United Technologies Corporation | Premix combustor |
US4322945A (en) * | 1980-04-02 | 1982-04-06 | United Technologies Corporation | Fuel nozzle guide heat shield for a gas turbine engine |
US4404806A (en) * | 1981-09-04 | 1983-09-20 | General Motors Corporation | Gas turbine prechamber and fuel manifold structure |
US5036657A (en) * | 1987-06-25 | 1991-08-06 | General Electric Company | Dual manifold fuel system |
GB9018013D0 (en) * | 1990-08-16 | 1990-10-03 | Rolls Royce Plc | Gas turbine engine combustor |
GB9018014D0 (en) * | 1990-08-16 | 1990-10-03 | Rolls Royce Plc | Gas turbine engine combustor |
GB2247522B (en) * | 1990-09-01 | 1993-11-10 | Rolls Royce Plc | Gas turbine engine combustor |
US5423178A (en) * | 1992-09-28 | 1995-06-13 | Parker-Hannifin Corporation | Multiple passage cooling circuit method and device for gas turbine engine fuel nozzle |
DE69414107T2 (en) * | 1993-06-01 | 1999-04-29 | Pratt & Whitney Canada | RADIAL AIR COMPRESSOR INJECTOR FOR FUEL |
US5400968A (en) * | 1993-08-16 | 1995-03-28 | Solar Turbines Incorporated | Injector tip cooling using fuel as the coolant |
JP3598534B2 (en) * | 1994-04-28 | 2004-12-08 | 豊田工機株式会社 | Aspherical surface processing equipment |
US5419115A (en) * | 1994-04-29 | 1995-05-30 | United Technologies Corporation | Bulkhead and fuel nozzle guide assembly for an annular combustion chamber |
DE4427222A1 (en) * | 1994-08-01 | 1996-02-08 | Bmw Rolls Royce Gmbh | Heat shield for a gas turbine combustor |
US5598696A (en) * | 1994-09-20 | 1997-02-04 | Parker-Hannifin Corporation | Clip attached heat shield |
DE19505357C1 (en) * | 1995-02-17 | 1996-05-23 | Daimler Benz Aerospace Ag | Aero engine or rocket wall cooling method |
DE19515537A1 (en) * | 1995-04-27 | 1996-10-31 | Bmw Rolls Royce Gmbh | Head part of a gas turbine annular combustion chamber |
US5848525A (en) * | 1996-08-30 | 1998-12-15 | General Electric Company | Fuel manifold staging valve |
US5771696A (en) | 1996-10-21 | 1998-06-30 | General Electric Company | Internal manifold fuel injection assembly for gas turbine |
US5983642A (en) * | 1997-10-13 | 1999-11-16 | Siemens Westinghouse Power Corporation | Combustor with two stage primary fuel tube with concentric members and flow regulating |
US6141968A (en) * | 1997-10-29 | 2000-11-07 | Pratt & Whitney Canada Corp. | Fuel nozzle for gas turbine engine with slotted fuel conduits and cover |
US5928493A (en) | 1997-11-24 | 1999-07-27 | Kaspar Electroplating Corporation | Process and apparatus for electrocoagulative treatment of industrial waste water |
CA2225263A1 (en) * | 1997-12-19 | 1999-06-19 | Rolls-Royce Plc | Fluid manifold |
US6109038A (en) | 1998-01-21 | 2000-08-29 | Siemens Westinghouse Power Corporation | Combustor with two stage primary fuel assembly |
US6149075A (en) * | 1999-09-07 | 2000-11-21 | General Electric Company | Methods and apparatus for shielding heat from a fuel nozzle stem of fuel nozzle |
US6761035B1 (en) * | 1999-10-15 | 2004-07-13 | General Electric Company | Thermally free fuel nozzle |
US6256995B1 (en) * | 1999-11-29 | 2001-07-10 | Pratt & Whitney Canada Corp. | Simple low cost fuel nozzle support |
US6463739B1 (en) * | 2001-02-05 | 2002-10-15 | General Electric Company | Afterburner heat shield |
EP1278014B1 (en) * | 2001-07-18 | 2007-01-24 | Rolls-Royce PLC | Fuel delivery system |
US7028484B2 (en) * | 2002-08-30 | 2006-04-18 | Pratt & Whitney Canada Corp. | Nested channel ducts for nozzle construction and the like |
-
2002
- 2002-08-30 US US10/231,334 patent/US7028484B2/en not_active Expired - Lifetime
-
2003
- 2003-08-22 DE DE60326611T patent/DE60326611D1/en not_active Expired - Lifetime
- 2003-08-22 JP JP2004531321A patent/JP2005536679A/en not_active Ceased
- 2003-08-22 EP EP03790583A patent/EP1546527B1/en not_active Expired - Lifetime
- 2003-08-22 WO PCT/CA2003/001251 patent/WO2004020805A1/en active Application Filing
- 2003-08-22 CA CA2494950A patent/CA2494950C/en not_active Expired - Lifetime
-
2006
- 2006-01-25 US US11/338,827 patent/US20060260317A1/en not_active Abandoned
-
2008
- 2008-05-21 US US12/124,593 patent/US8074452B2/en active Active
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20050188699A1 (en) * | 2004-02-27 | 2005-09-01 | Pratt & Whitney Canada Corp. | Apparatus for fuel transport and the like |
US7654088B2 (en) * | 2004-02-27 | 2010-02-02 | Pratt & Whitney Canada Corp. | Dual conduit fuel manifold for gas turbine engine |
US20060218926A1 (en) * | 2005-04-01 | 2006-10-05 | Pratt & Whitney Canada Corp. | Fuel conveying member with heat pipe |
US7530231B2 (en) * | 2005-04-01 | 2009-05-12 | Pratt & Whitney Canada Corp. | Fuel conveying member with heat pipe |
US20090320483A1 (en) * | 2008-06-26 | 2009-12-31 | General Electric Company | Variable Orifice Plug for Turbine Fuel Nozzle |
US20120047900A1 (en) * | 2009-03-17 | 2012-03-01 | Boettcher Andreas | Burner Assembly |
US9157370B2 (en) * | 2009-03-17 | 2015-10-13 | Siemens Aktiengesellschaft | Burner assembly |
US20120151928A1 (en) * | 2010-12-17 | 2012-06-21 | Nayan Vinodbhai Patel | Cooling flowpath dirt deflector in fuel nozzle |
US10317081B2 (en) | 2011-01-26 | 2019-06-11 | United Technologies Corporation | Fuel injector assembly |
CN106051824A (en) * | 2015-04-14 | 2016-10-26 | 通用电气公司 | Thermally-coupled fuel manifold |
US20160319780A1 (en) * | 2015-04-29 | 2016-11-03 | Mudassir Ahmed | Novel design of an effervescent atomizer with gas injection at reduced pressures |
US9897310B2 (en) * | 2015-04-29 | 2018-02-20 | Mudassir Ahmed | Effervescent atomizer with gas injection at reduced pressures |
Also Published As
Publication number | Publication date |
---|---|
US20090320479A1 (en) | 2009-12-31 |
CA2494950C (en) | 2011-03-15 |
US8074452B2 (en) | 2011-12-13 |
EP1546527B1 (en) | 2009-03-11 |
DE60326611D1 (en) | 2009-04-23 |
US20040040306A1 (en) | 2004-03-04 |
JP2005536679A (en) | 2005-12-02 |
WO2004020805A1 (en) | 2004-03-11 |
CA2494950A1 (en) | 2004-03-11 |
US7028484B2 (en) | 2006-04-18 |
EP1546527A1 (en) | 2005-06-29 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US8074452B2 (en) | Nested channel ducts for nozzle construction and the like | |
EP1725755B1 (en) | Internal fuel manifold for gas turbine engine or gas turbine fuel nozzle assembly | |
EP1830036B1 (en) | Method of manufacturing of an internal fuel manifold with turned channel having a variable cross-sectional area | |
EP1908940B1 (en) | Multi-conduit fuel manifold and method of manufacture | |
US6141968A (en) | Fuel nozzle for gas turbine engine with slotted fuel conduits and cover | |
US6622488B2 (en) | Pure airblast nozzle | |
US7506510B2 (en) | System and method for cooling a staged airblast fuel injector | |
EP0074196B1 (en) | Gas turbine prechamber and fuel manifold structure | |
US6915638B2 (en) | Nozzle with fluted tube | |
US5423178A (en) | Multiple passage cooling circuit method and device for gas turbine engine fuel nozzle | |
CA2580327C (en) | Fuel conveying member with side-brazed sealing members | |
US20130199191A1 (en) | Fuel injector with increased feed area |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |