Fuel nozzle guide plate mistake proofing

Abstract

A fuel nozzle guide plate has mirror symmetry about a first plane perpendicular to the fuel nozzle guide plate and mirror symmetry about a second plane parallel to the fuel nozzle guide plate. The fuel nozzle guide plate is attached to an air swirler, which is mounted in an opening of a bulkhead for mixing air and fuel at an upstream side of a combustor.

Claims

1 . A fuel nozzle mounting assembly for a combustor, the mounting assembly comprising: a bulkhead defining an upstream side of the combustor; at least one opening in the bulkhead for accommodating injection of fuel and air; an air swirler mounted in the at least one opening; a fuel nozzle guide plate attached to the air swirler, the fuel nozzle guide plate having mirror symmetry about a first plane perpendicular to the fuel nozzle guide plate and mirror symmetry about a second plane parallel to the fuel nozzle guide plate. 2 . The mounting assembly of claim 1 , further comprising: a fuel nozzle received by a central aperture of the fuel nozzle guide plate. 3 . The mounting assembly of claim 2 , further comprising: a retainer plate attached to the air swirler to form an annular track for attachment of the fuel nozzle guide plate. 4 . The mounting assembly of claim 3 , wherein the fuel nozzle guide plate includes a substantially circular flange surrounding the central aperture, the flange received by the annular track such that axial movement is substantially restrained, but radial movement is permitted. 5 . The mounting assembly of claim 4 , wherein the annular track includes a cut out window. 6 . The mounting assembly of claim 5 , wherein a tab extends from the flange and is received by the window to prevent rotation of the fuel nozzle guide plate with respect to the annular track. 7 . The mounting assembly of claim 6 , wherein the fuel nozzle guide plate includes a collar extending inwardly from the flange and surrounding the central aperture, the collar configured for non-binding engagement of the fuel nozzle. 8 . The mounting assembly of claim 7 , wherein the collar includes an upstream chamfer, a downstream chamfer, and a convex surface located between the upstream chamfer and the downstream chamfer. 9 . The mounting assembly of claim 8 , wherein the collar has mirror symmetry about the second plane parallel to the fuel nozzle guide plate. 10 . A fuel nozzle mounting assembly for a combustor, the mounting assembly comprising: an air swirler mounted in an opening located on an upstream side of the combustor; a fuel nozzle guide plate attached to an upstream side of the air swirler, the fuel nozzle guide plate comprising: a collar defining a central aperture for non-binding engagement of the fuel nozzle, the collar having mirror symmetry about a first plane perpendicular to the collar and mirror symmetry about a second plane parallel to the collar; and a substantially circular flange surrounding the collar for attaching the fuel nozzle guide plate to the swirler; and a retainer plate attached to the upstream end of the air swirler to form an annular track for trapping the substantially circular flange of the fuel nozzle guide plate such that the fuel nozzle guide plate is capable of relative radial and circumferential movement, but not relative axial movement. 11 . The mounting assembly of claim 10 , wherein the mirror symmetry about the first plane perpendicular to the collar is side to side symmetry and the mirror symmetry about the second plane perpendicular to the collar is front to back symmetry. 12 . The mounting assembly of claim 11 , wherein the collar includes an upstream chamfer, a downstream chamfer, and a convex surface located between the upstream chamfer and the downstream chamfer. 13 . The mounting assembly of claim 12 , wherein a cross-sectional view of the collar is mushroom shaped. 14 . The mounting assembly of claim 13 , wherein the collar has a small, predetermined internal diameter at an approximate center of the convex surface for non-binding engagement of a fuel nozzle. 15 . The mounting assembly of claim 14 , further comprising: a fuel nozzle extending through the central aperture and contacting the collar at the small, predetermined diameter. 16 . A method of mounting a fuel nozzle in a combustor, the method comprising: mounting an air swirler in an opening located at an upstream side of the combustor; contacting an upstream side of the air swirler with a fuel nozzle guide plate having a mirror symmetry about a first plane perpendicular to the fuel nozzle guide plate and mirror symmetry about a second plane parallel to the fuel nozzle guide plate; trapping the guide plate against the air swirler with a retainer plate; and securing the retainer plate to the air swirler thereby forming a floating connection between the air swirler and the fuel nozzle guide plate. 17 . The method of claim 16 , further comprising: inserting a fuel nozzle into an upstream side of the fuel nozzle guide plate past a first chamfer and toward a second chamfer located on an opposite, downstream side. 18 . The method of claim 17 , further comprising: aligning a tab extending from the fuel nozzle guide plate with a window located between the air swirler and the retainer plate. 19 . The method of claim 18 , wherein trapping the fuel nozzle guide plate against the air swirler includes forming an annular track for receiving the fuel nozzle guide plate therein. 20 . The method of claim 19 , wherein securing the retainer plate to the swirler includes welding or bolting the retainer plate to the air swirler.
BACKGROUND [0001] The present disclosure relates generally to gas turbine engines and, more particularly, to a fuel nozzle guide plate for use in a combustor section of a gas turbine engine. [0002] A gas turbine engine includes one or more upstream compressors which provide pressurized air to a combustor. The combustor mixes the pressurized air with fuel and ignites the mixture to create combustion gases that flow downstream into one or more turbines. The turbines extract energy from the combustion gases to power the compressor, as well as power an aircraft, train, ship, or generator. [0003] Fuel nozzles atomize and inject fuel into the combustion section of the gas turbine engine. Surrounding the fuel nozzles are air swirler assemblies, which impart a swirling motion to compressed air for mixing with the fuel. In annular type combustors, each swirler assembly includes a guide plate for centrally receiving the fuel nozzle. U.S. Pat. No. 5,577,379 to United Technologies Corporation and U.S. Pat. No. 7,140,189 to Pratt & Whitney Canada Corp. describe guide plates for receiving fuel nozzles in the upstream portion of a combustor. SUMMARY [0004] An embodiment of the present disclosure is a fuel nozzle mounting assembly for a combustor. A bulkhead defines an upstream side of the combustor. There is at least one opening in the bulkhead for accommodating injection of fuel and air. An air swirler is mounted in the at least one opening. A fuel nozzle guide plate is attached to the air swirler. The fuel nozzle guide plate has mirror symmetry about a first plane perpendicular to the fuel nozzle guide plate and mirror symmetry about a second plane parallel to the fuel nozzle guide plate. [0005] Another embodiment of the present disclosure is a fuel nozzle mounting assembly for a combustor. An air swirler is mounted in an opening located on an upstream side of the combustor. A fuel nozzle guide plate is attached to an upstream side of the air swirler. The fuel nozzle guide plate includes a collar defining a central aperture for non-binding engagement of the fuel nozzle, and a substantially circular flange surrounding the collar for attaching the fuel nozzle guide plate to the air swirler. The collar has mirror symmetry about a first plane perpendicular to the collar and mirror symmetry about a second plane parallel to the collar. A retainer plate is attached to the upstream end of the air swirler to form an annular track for trapping the substantially circular flange of the fuel nozzle guide plate such that the fuel nozzle guide plate is capable of relative radial (up and down) and circumferential (left to right) movement, but not relative axial movement. [0006] An additional embodiment of the present disclosure is a method of mounting a fuel nozzle in a combustor. The method includes mounting an air swirler in an opening located at an upstream side of the combustor and contacting an upstream side of the air swirler with a fuel nozzle guide plate having a mirror symmetry about a first plane perpendicular to the fuel nozzle guide plate and mirror symmetry about a second plane parallel to the fuel nozzle guide plate. The method also includes trapping the fuel nozzle guide plate against the air swirler with a retainer plate and securing the retainer plate to the air swirler thereby forming a floating connection between the air swirler and the fuel nozzle guide plate. BRIEF DESCRIPTION OF THE DRAWINGS [0007] FIG. 1 is a cross-sectional view of a gas turbine engine. [0008] FIG. 2 is an enlarged cross-sectional view of a combustor section of the gas turbine engine from FIG. 1 . [0009] FIG. 3 is an enlarged cross-sectional view of an air swirler in accordance with the present disclosure. [0010] FIG. 4A is a front view and FIG. 4B is a cross-sectional view of the fuel nozzle guide plate from FIG. 3 . [0011] FIG. 5A is a front view and FIG. 5B is a cross-sectional view of an alternative fuel nozzle guide plate. DETAILED DESCRIPTION [0012] FIG. 1 is a cross sectional view of gas turbine engine 10 , which includes four main sections connected to one another in the following order: inlet fan 12 , compressor section 14 , combustor section 16 , and turbine section 18 . Air enters gas turbine engine 10 through inlet fan 12 and a portion of the air is directed to the attached compressor section 14 . The air is then compressed by a series of rotating blades and static vanes located in compressor section 14 . The compressed air is mixed with fuel and ignited in the attached combustor section 16 . The resulting combustion exhaust is then directed toward turbine section 18 , which also includes blades and vanes. The blades within turbine section 18 extract kinetic energy from the exhaust to turn a shaft (or shafts) thereby providing power to drive inlet fan 12 and compressor section 14 . Thrust is provided by inlet fan 12 and the exhaust from turbine section 18 . [0013] FIG. 2 is an enlarged cross-sectional view of combustor section 16 of gas turbine engine 10 from FIG. 1 . Depicted in FIG. 2 are components of combustor section 16 : bulkhead 20 , liner 22 , studs 24 , cowl 26 , bulkhead opening 28 , heat shield 30 , air swirler 32 , fuel nozzle guide plate 34 , fuel nozzle tip 36 , and fuel nozzle 38 . Fuel nozzle guide plate 34 holds fuel nozzle tip 36 in place at an upstream side of combustor section 16 . [0014] Bulkhead 20 defines the upstream side of combustion section 16 . Attached to and extending in a downstream direction from bulkhead 20 is liner 22 . Spaced along and extending into liner 22 are studs 24 . Attached to and enclosing an upstream side of bulkhead 20 is semi-circular cowl 26 . Bulkhead opening 28 is located in an approximate center of bulkhead 20 , opposite an approximate center of circular cowl 26 . Heat shield 30 extends downwardly from bulkhead 20 at a location near bulkhead opening 28 toward liner 20 . Air swirler 32 extends upstream from bulkhead 20 at a location near bulkhead opening 28 toward cowl 26 . Attached to an upstream side of air swirler 32 is fuel nozzle guide plate 34 . Fuel nozzle guide plate 34 extends centrally into bulkhead opening 28 to contact fuel nozzle tip 36 around its perimeter. Fuel nozzle 38 extends upwardly from fuel nozzle tip 36 out of cowl 26 to connect with a fuel reservoir where fuel to be supplied to combustion section 16 is stored. [0015] Liner 22 and heat shield 30 are pieces of metal configured to withstand the immense heat characteristic of combustion. Liner 22 and heat shield 30 can include holes to allow secondary cooling air to enter combustion section 16 . Studs 24 are located at intervals along liner 22 to fasten liner 22 to a combustor shelf. Bulkhead opening 28 is configured to house fuel and air injection components, such as heat shield 30 , air swirler 32 , fuel nozzle guide plate 34 , and fuel nozzle tip 36 . Heat shield 30 is aptly named as it is constructed to shield bulkhead 20 from heat. Air swirler 32 introduces primary air into combustion section 16 and swirls the incoming air to encourage mixing between air and fuel and help combustion. Fuel nozzle guide plate 34 secures fuel nozzle tip 36 within bulkhead opening 28 while allowing for a non-binding attachment between fuel nozzle tip 36 and air swirler 32 . Fuel nozzle 38 supplies fuel to fuel nozzle tip 36 for spraying or atomizing fuel introduced into combustion section 16 . The fuel nozzle tip 36 mounting assembly, including fuel nozzle guide plate 34 and air swirler 32 , is considered in more detail below. [0016] FIG. 3 is an enlarged cross-sectional view of air swirler 32 and bulkhead opening 28 in accordance with the present disclosure. In FIG. 3 , fuel nozzle tip 36 is removed to better show the attachment between air swirler 32 , fuel nozzle guide plate 34 , and retainer plate 42 , which collectively form mounting assembly 40 . Together retainer plate 42 and air swirler 32 from track 44 having window 52 located therein. For descriptive purposes, fuel nozzle guide plate 34 can be further divided into subcomponents: flange 46 , collar 48 , tab 50 , upstream side 54 , downstream side 56 , center surface 58 , and center aperture 60 . Fuel nozzle guide plate 34 is configured to mistake or fool proof construction of mounting assembly 40 . [0017] Fuel nozzle guide plate 34 is located between air swirler 32 and retainer plate 42 . Air swirler 32 has upstream lip 33 for connecting to fuel nozzle guide plate 34 . Air swirler 32 tapers as it extends downstream from lip 33 toward bulkhead opening 28 . A downstream side of fuel nozzle guide plate 34 is in contact with upstream lip 33 of air swirler 32 , and an upstream side of fuel nozzle guide plate 34 is in contact with, or in close proximity to, retainer plate 42 , such that fuel nozzle guide plate 34 is trapped between air swirler 32 and retainer plate 42 . Annular track 44 is formed between retainer plate 42 and air swirler 32 during construction of mounting assembly 40 . First, circular flange 46 of fuel nozzle guide plate 34 is brought into position relative to upstream lip 33 of air swirler 32 . Second, retainer plate 42 is brought into position relative to the upstream side of fuel nozzle guide plate 34 so that fuel nozzle guide plate is located between air swirler 32 and retainer plate 42 . Air swirler 32 has upstream lip 33 that attaches to the downstream side of retainer plate 42 thereby forming U-shaped track 44 . Track 44 surrounds and traps circular flange 46 of fuel nozzle guide plate 34 between air swirler 32 and retainer plate 42 , which can be bolted, welded, or otherwise retained together. [0018] Fuel nozzle guide plate 34 has circular flange 46 with collar 48 extending centrally or inwardly from flange 46 . When viewed in cross-section, collar 48 resembles a mushroom head with flange 46 being a stem. Extending outwardly from a top of flange 46 is rectangular tab 50 . When viewed in cross section, tab 50 appears to be an extension of the stem (flange 46 ) of top mushroom (collar 48 ). Tab 50 extends upwardly into window 52 , which is an opening in a top of track 44 . Collar 48 can be further divided into upstream edge 54 , downstream edge 56 , and center surface 58 located there between. Both upstream edge 54 and downstream edge 56 are chamfered and center surface 58 is toroidal or alternatively, surface 58 is cylindrical. Located centrally inside of both flange 46 and collar 48 , and defined by an inside diameter of center surface 58 , is circular central aperture 60 . Since both upstream edge 54 and downstream edge 56 are equally chamfered, either edge 54 or edge 56 can face upstream and act as an upstream edge for fuel nozzle guide plate 34 . [0019] Air swirler 32 introduces and swirls air entering combustion section 16 of gas turbine engine. Fuel nozzle guide plate 34 holds fuel nozzle tip 36 (removed) centrally within mounting assembly 40 so that fuel injected by fuel nozzle tip 36 mixes with the swirling air. Air swirler 32 and retainer plate 42 form track 44 , which allows for a floating or sliding attachment between fuel nozzle guide plate 34 and air swirler 32 . Flange 46 of fuel nozzle guide plate 34 is trapped within track 44 , but can float about 0.125 inches (0.318 centimeters) radially to accommodate manufacturing tolerances and/or thermal mismatches. While track 44 allows for radial (up and down) and circumferential (left to right) movement, it restrains axial movement of flange 46 . When attaching retainer plate 42 to air swirler 32 thereby forming track 44 around fuel nozzle guide plate 34 , care is taken to ensure that tab 50 is located within window 52 . Containing tab 50 within window 52 prevents rotation of fuel nozzle guide plate 34 relative to track 44 . In an alternative embodiment, the tab 50 —window 52 relationship is repeated one or more times around the circumference of flange 46 . Chamfers located on upstream edge 54 and downstream edge 56 aide in insertion of fuel nozzle tip 36 into center aperture 60 . Center surface 58 is toroidal to accommodate non-binding angular misalignment during insertion of fuel nozzle tip 36 and during engine 10 operation. Since upstream edge 54 and downstream edge 56 are equally chamfered and center surface is toroidal, collar 48 has bilateral symmetry rendering fuel nozzle guide plate 34 incapable of being installed into mounting assembly 40 backwards. [0020] FIG. 4A is a front view and FIG. 4B is a cross-sectional view of fuel nozzle guide plate 34 from FIG. 3 . Depicted in FIGS. 4A and 4B are components of fuel nozzle guide plate 34 : flange 46 , collar 48 , tab 50 , upstream edge 54 , downstream edge 56 , center surface 58 , and aperture 60 . Fuel nozzle guide plate 34 is designed for fool-proof installation into mounting assembly 40 . In other words, either upstream edge 54 or downstream edge 56 can face downstream and act as a downstream edge 56 . [0021] Fuel nozzle guide plate 34 can be formed from any metal or metal alloy, such as but not limited to, Nickel Alloy or Cobalt Alloy. Flange 46 is substantially circular and surrounds central aperture 60 . Collar 48 extends inwardly from flange 46 into central aperture 60 and resembles a mushroom when viewed in cross-section. In an alternative embodiment, collar 48 and flange 46 have similar widths, and a cross-sectional view of this embodiment resembles a crayon. Tab 50 is rectangular and projects outwardly from a top of collar 48 away from central aperture 60 or in direction opposite to collar 48 . Upstream edge 54 and downstream edge 56 of collar 48 are both chamfered at about 50 degrees. Center surface 58 is convex and defines an inner diameter of about 0.47 inches (1.194 centimeters) that closely matches an outer diameter of fuel nozzle tip 36 . Unlike previous unidirectional fuel nozzle guide plates, fuel nozzle guide plate 34 has planar symmetry about two planes, A and B, rendering fuel nozzle guide plate 34 incapable of being installed incorrectly. [0022] Running vertically through center aperture 60 is first plane A. First plane A is perpendicular to fuel nozzle guide plate 34 , which is particularly evident where first plane A bisects tab 50 . First plane A divides fuel nozzle guide plate 34 into two equal and symmetrical halves such that fuel nozzle guide plate 34 has mirror symmetry about first plane A. The mirror symmetry about plane A is sometimes known as bilateral symmetry or side-to-side symmetry. Running vertically through center surface 58 is second plane B. Second plane B is parallel to fuel nozzle guide plate 34 , which is particularly evident where second plane B bisects collar 48 . Second plane B divides fuel nozzle guide plate 34 into two equal and symmetrical halves such that fuel nozzle guide plate 34 has mirror symmetry about second plane B. The mirror symmetry about plane B is sometimes known as front-to-back symmetry. While in the above description collar 48 is explained as having upstream edge 56 and downstream edge 58 , these edges can be reversed without causing any ill effect within mounting assembly 40 . By incorporating two planes of mirror symmetry into fuel nozzle guide plate 34 , construction of mounting assembly 40 is mistake proofed. [0023] FIG. 5A is a front view and FIG. 5B is a cross-sectional view of an alternative fuel nozzle guide plate 34 ′. Depicted in FIGS. 5A and 5B are components of fuel nozzle guide plate 34 ′: flange 46 ′, collar 48 ′, upstream edge 54 ′, downstream edge 56 ′, center surface 58 ′, aperture 60 ′, and slot 62 . Also shown is pin 64 , which is a component of either air swirler 32 ′ or retainer plate 42 ′. [0024] Fuel nozzle guide plate 34 ′ is substantially similar to fuel nozzle guide plate 34 described above. Fuel nozzle guide plate 34 ′ has planar symmetry about two planes, A and B, rendering fuel nozzle guide plate 34 ′ incapable of being installed incorrectly. Fuel nozzle guide plate 34 ′ differs from fuel nozzle guide plate 34 in that the tab 50 —window 52 relationship is replaced by a slot 62 —pin 64 relationship. Like the tab 50 —window 52 relationship, the slot 62 —pin 64 relationship serves as an anti-rotation feature. Pin 64 protrudes from either air swirler 32 ′ or retainer plate 42 ′ and engages slot 62 of fuel nozzle guide plate 34 ′ to prevent inadvertent rotation therebetween. While one slot 62 and one pin 64 are depicted in FIGS. 5A and 5B , additional anti-rotation features can be incorporated around the circumference of flange 34 ′. [0025] Vertical, horizontal, top, bottom, inward, outward, upstream, and downstream have been used through the specification to help define relative directions. Although the present invention has been described with reference to preferred embodiments, workers skilled in the art will recognize that changes may be made in form and detail without departing from the spirit and scope of the invention.

Description

Topics

Download Full PDF Version (Non-Commercial Use)

Patent Citations (52)

    Publication numberPublication dateAssigneeTitle
    US-6314739-B1November 13, 2001General Electric CompanyBrazeless combustor dome assembly
    US-3563470-AFebruary 16, 1971Director Of National AerospaceAir swirling vanes for burner
    US-4763482-AAugust 16, 1988General Electric CompanySwirler arrangement for combustor of gas turbine engine
    US-5996335-ADecember 07, 1999Bmw Rolls-Royce GmbhHead part of an annular combustion chamber of a gas turbine having a holding part to secure a burner collar in a bayonet-catch type manner
    US-4454711-AJune 19, 1984Avco CorporationSelf-aligning fuel nozzle assembly
    US-7591136-B2September 22, 2009SnecmaAntirotation injection system for turbojet
    US-5577379-ANovember 26, 1996United Technologies CorporationFuel nozzle guide retainer assembly
    US-2007137208-A1June 21, 2007Pratt & Whitney Canada Corp.Combustor swirler and method of manufacturing same
    US-3796134-AMarch 12, 1974Midland Ross CorpHydraulic booster brake mechanism
    US-5916142-AJune 29, 1999General Electric CompanySelf-aligning swirler with ball joint
    US-6880341-B2April 19, 2005Pratt & Whitney Canada Corp.Low cost combustor floating collar with improved sealing and damping
    US-7104066-B2September 12, 2006General Electric CompanyCombuster swirler assembly
    US-4693074-ASeptember 15, 1987Rolls-Royce PlcCombustion apparatus for a gas turbine engine
    US-4582329-AApril 15, 1986Combustion Engineering, Inc.Sealing bearing arrangement with convex bushing ring
    US-7617689-B2November 17, 2009Honeywell International Inc.Combustor dome assembly including retaining ring
    US-7415826-B2August 26, 2008General Electric CompanyFree floating mixer assembly for combustor of a gas turbine engine
    US-6412272-B1July 02, 2002United Technologies CorporationFuel nozzle guide for gas turbine engine and method of assembly/disassembly
    US-5197290-AMarch 30, 1993Fuel Systems Textron Inc.Variable area combustor air swirler
    US-7478534-B2January 20, 2009SnecmaArrangement with a twist-lock coupling for a turbomachine combustion chamber
    US-2006207258-A1September 21, 2006Tanner Keith M, Kirsopp Philip JFuel injector bearing plate assembly and swirler assembly
    US-7140189-B2November 28, 2006Pratt & Whitney Canada Corp.Gas turbine floating collar
    US-4686823-AAugust 18, 1987United Technologies CorporationSliding joint for an annular combustor
    US-6427435-B1August 06, 2002General Electric CompanyRetainer segment for swirler assembly
    US-4148190-AApril 10, 1979Tokico Ltd.Master cylinder
    US-5353599-AOctober 11, 1994United Technologies CorporationFuel nozzle swirler for combustors
    US-4271675-AJune 09, 1981Rolls-Royce LimitedCombustion apparatus for gas turbine engines
    US-7543383-B2June 09, 2009Pratt & Whitney Canada Corp.Method for manufacturing of fuel nozzle floating collar
    US-6497105-B1December 24, 2002Pratt & Whitney Canada Corp.Low cost combustor burner collar
    US-5463864-ANovember 07, 1995United Technologies CorporationFuel nozzle guide for a gas turbine engine combustor
    US-7131273-B2November 07, 2006General Electric CompanyGas turbine engine carburetor with flat retainer connecting primary and secondary swirlers
    US-6032457-AMarch 07, 2000United Technologies CorporationFuel nozzle guide
    US-7062920-B2June 20, 2006General Electric CompanyCombustor dome assembly of a gas turbine engine having a free floating swirler
    US-5924288-AJuly 20, 1999General Electric CompanyOne-piece combustor cowl
    US-7134286-B2November 14, 2006Pratt & Whitney Canada Corp.Gas turbine floating collar arrangement
    US-5373693-ADecember 20, 1994Mtu Motoren- Und Turbinen-Union Munchen GmbhBurner for gas turbine engines with axially adjustable swirler
    US-6036191-AMarch 14, 2000Adwest Engineering LimitedRotary valve seal assembly
    US-4244278-AJanuary 13, 1981Itt Industries, Inc.Arrangement for a hydraulic brake booster
    US-2008282703-A1November 20, 2008Oleg Morenko, Kenneth Parkman, Stephen PhillipsInterface between a combustor and fuel nozzle
    US-5419115-AMay 30, 1995United Technologies CorporationBulkhead and fuel nozzle guide assembly for an annular combustion chamber
    US-5581999-ADecember 10, 1996United Technologies CorporationBulkhead liner with raised lip
    US-3667229-AJune 06, 1972Ferruccio ManziniDevice for supplying fluid under pressure
    US-5664412-ASeptember 09, 1997Rolls-Royce PlcVariable geometry air-fuel injector
    US-4525996-AJuly 02, 1985Rolls-Royce LimitedMounting combustion chambers
    US-8015706-B2September 13, 2011Lorin Markarian, Bhawan Bhai PatelGas turbine floating collar
    US-2009025224-A1January 29, 2009Patel Bhawan B, Lorin Markarian, Melissa DespresMethod for manufacturing of fuel nozzle floating collar
    US-7874164-B2January 25, 2011Pratt & Whitney Canada Corp.Fuel nozzle flange with reduced heat transfer
    US-2010058765-A1March 11, 2010SnecmaTurbomachine combustion chamber
    US-7721436-B2May 25, 2010Pratt & Whitney Canada Corp.Method of manufacturing a metal injection moulded combustor swirler
    US-7628019-B2December 08, 2009United Technologies CorporationFuel injector bearing plate assembly and swirler assembly
    US-7926280-B2April 19, 2011Pratt & Whitney Canada Corp.Interface between a combustor and fuel nozzle
    US-6896491-B2May 24, 2005Caterpillar IncBearing mounting flange having flexibility pocket
    US-3589127-AJune 29, 1971Gen ElectricCombustion apparatus

NO-Patent Citations (0)

    Title

Cited By (11)

    Publication numberPublication dateAssigneeTitle
    FR-3015641-A1June 26, 2015SnecmaDispositif d'injection dans une turbomachine
    US-2013199194-A1August 08, 2013Rolls-Royce PlcCombustor head arrangement
    US-2014144148-A1May 29, 2014United Technologies CorporationCooled Combustor Seal
    US-2016033130-A1February 04, 2016United Technologies CorporationFuel nozzle for a gas turbine engine
    US-9243561-B2January 26, 2016Rolls-Royce PlcCombustor head arrangement
    US-9310072-B2April 12, 2016Hamilton Sundstrand CorporationNon-symmetric arrangement of fuel nozzles in a combustor
    US-9347378-B2May 24, 2016Solar Turbines IncorporatedOuter premix barrel vent air sweep
    US-9366190-B2June 14, 2016Solar Turbines IncorporatedTapered gas turbine engine liquid gallery
    US-9587831-B2March 07, 2017United Technologies CorporationCooled combustor seal
    US-9592480-B2March 14, 2017Solar Turbines IncorporatedInner premix tube air wipe
    WO-2015053818-A3June 18, 2015United Technologies CorporationInterface de montage de coupelle de turbulence pour chambre de combustion de moteur à turbine à gaz