US20190107285A1 - Segmented fuel distributor - Google Patents

Segmented fuel distributor Download PDF

Info

Publication number
US20190107285A1
US20190107285A1 US15/726,447 US201715726447A US2019107285A1 US 20190107285 A1 US20190107285 A1 US 20190107285A1 US 201715726447 A US201715726447 A US 201715726447A US 2019107285 A1 US2019107285 A1 US 2019107285A1
Authority
US
United States
Prior art keywords
fuel
segments
segmented
secondary conduits
distributor
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
Application number
US15/726,447
Other languages
English (en)
Inventor
Oleg Morenko
Aleksandar Kojovic
Gavin Rohiteshwar KISUN
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Pratt and Whitney Canada Corp
Original Assignee
Pratt and Whitney Canada Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Pratt and Whitney Canada Corp filed Critical Pratt and Whitney Canada Corp
Priority to US15/726,447 priority Critical patent/US20190107285A1/en
Assigned to PRATT & WHITNEY CANADA CORP. reassignment PRATT & WHITNEY CANADA CORP. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: KOJOVIC, ALEKSANDAR, MORENKO, OLEG, KISUN, GAVIN ROHITESHWAR
Priority to CA3016780A priority patent/CA3016780A1/fr
Publication of US20190107285A1 publication Critical patent/US20190107285A1/en
Abandoned legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/40—Use of a multiplicity of similar components
    • 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
    • F23R3/002—Wall structures

Definitions

  • the application relates generally to gas turbine engines and, more particularly, to systems and methods for injecting fuel in combustors of such engines.
  • Existing fuel manifolds for gas turbine engines include internal fuel manifolds and external fuel manifolds. While internal fuel manifolds are advantageous in a number of respects (e.g. weight, cost, etc.), they are not as easily removed and/or accessible for maintenance purposes as their more traditionally-used external counterparts. For example, a gas turbine engine with an internal fuel manifold must be split apart in order to access the fuel manifold for service and/or replacement. Consequently, such operations cannot be done in the field and involve more time, cost and engine downtime.
  • a segmented fuel distributor for injecting fuel into a combustion chamber of a gas turbine engine, the segmented fuel distributor comprising a plurality of segments serially interconnected in fuel flow communication to provide an annular structure, the segmented fuel distributor configured for mounting to an external casing of the gas turbine engine, the segments including a main conduit defining a first axis along which a main fuel flow path extends, the segments having two or more secondary conduits extending from the main conduit and being in fluid flow communication therewith, and fuel injectors fluidly connected to the secondary conduits at remote ends thereof.
  • a combustor for a gas turbine engine comprising a casing and a segmented fuel distributor affixed to the casing and configured for injecting fuel into a combustion chamber of the combustor, the segmented fuel distributor comprising a plurality of segments serially interconnected in fuel flow communication, the segments including a main conduit defining a first axis along which a main fuel flow path extends, the segments having two or more secondary conduits extending from the main conduit and being in fluid flow communication therewith, and fuel injectors fluidly connected to the secondary conduits at remote ends thereof.
  • a method of assembling a combustor of a gas turbine engine comprising: disposing fuel distribution segments circumferentially around a central axis of the combustor, the fuel distribution segments having two or more fuel injectors; fluidly connecting the fuel distribution segments with two respectively adjacent ones of the fuel distribution segments to form a segmented fuel distributor; and securing the segmented fuel distributor to a casing of the combustor.
  • FIG. 1 is a schematic cross-sectional view of a gas turbine engine
  • FIG. 2 is a schematic tridimensional view of a segmented fuel distributor in accordance with one embodiment
  • FIG. 3 is a schematic front view of a fuel carrying segment of the segmented fuel distributor of FIG. 2 ;
  • FIG. 3 a is a schematic top view of a segmented fuel distributor comprising fuel carrying segments in accordance with another embodiment
  • FIG. 4 is a schematic cross-sectional view of a portion of the segmented fuel distributor of FIG. 2 ;
  • FIG. 5 is a schematic tridimensional cross-sectional view of a portion of the segmented fuel distributor of FIG. 2 ;
  • FIG. 6 is a schematic tridimensional view of the segmented fuel distributor of FIG. 3 a ;
  • FIG. 7 is a schematic top cross-sectional view of the segmented fuel distributor of FIG. 6 .
  • FIG. 1 illustrates a gas turbine engine 10 of a type preferably provided for use in subsonic flight, generally comprising in serial flow communication a fan 12 through which ambient air is propelled, a compressor section 14 for pressurizing the air, a combustor 16 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section 18 for extracting energy from the combustion gases.
  • the compressor section 14 , the fan 12 , and the turbine section 18 rotate about a central axis 11 of the gas turbine engine 10 .
  • the combustor 16 is surrounded by a casing 20 disposed around the central axis 11 .
  • the segmented fuel distributor 22 comprises individual fuel carrying segments 24 serially interconnected in fuel flow communication to form an annular structure 26 .
  • the individual fuel carrying segments 24 are interconnected with each other with transfer tube assemblies 28 .
  • the transfer tube assemblies 28 are configured to allow a flexibility of the segmented fuel distributor 22 .
  • a combustion chamber 30 is located radially inward to the casing 20 relative to the central axis 11 . Using such transfer tube assemblies 28 might offer certain advantages.
  • each of the fuel carrying segments 24 acts as a single fuel nozzle having several fuel injection points 32 .
  • the fuel carrying segments 24 are made of AMS 5401/INCONEL 625 or other suitable metal.
  • the fuel carrying segment 24 includes a main conduit 34 extending along a longitudinal axis L along which a primary fuel flow path 36 extends.
  • the fuel carrying segment 24 further includes two or more secondary conduits 38 , which may also be referred to as stems, extending away from the main conduit 34 and which each define a secondary fuel flow path.
  • the fuel carrying segment 24 includes three secondary conduits 38 , however it is to be understood that in alternate embodiments there may be only two secondary conduits 38 or there may be more than three secondary conduits 38 .
  • the main conduit 34 and the secondary conduits 38 are integrally formed with each other to define a monolithic component.
  • the secondary conduits 38 are disposed at respective angles ⁇ relative to the main conduit 34 along respective longitudinal axes L′.
  • Secondary fuel flow paths 40 extend through the secondary conduits 38 and are fluidly connected with the main flow path 36 of the main conduit 34 .
  • the fuel carrying segment 24 may comprise from two to five, or more, secondary conduits 38 .
  • the segmented fuel distributor 22 may comprise simultaneously individual fuel carrying segments 24 having different numbers of secondary conduits 38 .
  • the angles between the longitudinal axes L and L′ may range from 15° to 90°.
  • the secondary conduits 38 extend away from each other from the longitudinal axis toward remote ends 38 a of the secondary conduits 38 relative to a radial distance from the longitudinal axis L. In other words, an axial distance between two of the secondary conduits 38 relative to the longitudinal axis L increases with a radial distance from said longitudinal axis L.
  • the main conduit 34 defines two opposed ends 42 and 44 spaced apart from each other along the longitudinal axis L.
  • the two opposed ends 42 and 44 circumscribe openings 46 for receiving a fuel flow to be injected into the combustion chamber 30 .
  • the two opposed ends 42 , 44 of the main conduit 34 are configured to be fluidly connected with circumferentially adjacent ones of the individual fuel carrying segments 24 via the transfer tube assemblies 28 .
  • the fuel carrying segment 24 defines coupling portions 34 a adjacent the opposed ends 42 , 44 and formed integrally with the main conduit 34 .
  • the coupling portions 34 a are configured for being sealingly connected to the transfer tube assemblies 28 .
  • a diameter of the coupling portions 34 a is greater than a diameter of the main conduit 34 .
  • Each of the coupling portions 34 a defines a first annular groove 34 b .
  • One of the coupling portions 34 a defines a second annular groove 34 c of a depth less than that of the other annular grooves 34 b and disposed beyond the first annular groove 34 b relative to a distance from end 42 .
  • the second annular groove 34 c is configured for receiving external snap ring or circlip 45 ( FIG. 3 a ) to limit movement of an outer sleeve 68 ( FIG. 5 ).
  • the first annular grooves 34 b are configured for receiving O-rings (not shown) for creating a sealing engagement between the coupling portions 34 a and the outer sleeve 68 .
  • the outer sleeve 68 may then be able to contain a fuel leak.
  • the leaked fuel may be able to drain through drain passages 34 e ( FIG. 5 ) defined in the fuel carrying segments 24 .
  • the fuel carrying segment 24 further includes fuel injector receiving members 50 disposed at the remote, or distal ends 38 a of the secondary conduits 38 .
  • the fuel carrying segment 24 further includes fuel injectors 52 ( FIGS. 4-5 ) configured for being received by the fuel injector receiving members 50 .
  • the assembly of the fuel injectors 52 within the fuel injector receiving members 50 is described herein below.
  • the main conduit 34 , the secondary conduits 38 , and the fuel injector receiving members 50 are integrally formed by suitable manufacturing processes.
  • the fuel carrying segment 24 is integrally formed and fuel passages are formed by manufacturing along the longitudinal axes L and L′ of the main and secondary conduits 34 and 38 .
  • Manufactured holes 54 are shown for illustration purposes. It is understood that the manufactured holes 54 are suitably clogged to preclude fluid flow communication between the main and secondary flow paths 36 and 40 and an environment E ( FIG. 2 ) of the segmented fuel distributor 22 .
  • the fuel carrying segments 24 may be manufactured using metal injection molding (MIM) or additive manufacturing (AM), or other technologies to create complex shapes which might be optimized for weight.
  • MIM metal injection molding
  • AM additive manufacturing
  • the MIM/AM manufacturing is unable to create the fuel passages within the conduits. Said passages may then be manufactured and plug welded at any location where they interface with the environment E. As discussed below, the shape of the fuel carrying segments 24 might improve cooling with ambient air.
  • FIG. 3A another embodiment of a fuel carrying segment 24 ′ is illustrated.
  • the secondary conduits 38 ′ of the fuel carrying segment 24 ′ have an L-shape and extend from the main conduit 34 ′.
  • An angle ⁇ between the main conduit 34 ′ and the secondary conduits 38 ′ may, in one particular embodiment, range from about 5 degrees to about 175 degrees.
  • the secondary conduits 38 ′ each define an angle ⁇ such that the secondary conduits 38 ′ curve radially inwardly to reach the fuel injector receiving members 50 .
  • the angle ⁇ may range from about 60 degrees to about 130 degrees, and an angle between said members 50 and the secondary conduits 38 ′ may be about 90 degrees.
  • angle ⁇ and angle ⁇ can also be used, and will depend upon the specific configuration required, engine architecture, design requirements and parameters, etc.
  • each of the fuel injector receiving members 50 has a cylindrical shape extending perpendicularly to a respective one of the secondary conduits 38 .
  • each of the fuel injector receiving members 50 defines two cavities 50 a and 50 b separated by a wall 50 c .
  • the two cavities 50 a and 50 b overlap each other along a given length relative to a central axis L′′ of the fuel injector receiving member 50 .
  • the two cavities 50 a and 50 b decrease in height, or diameter, toward a center of the fuel injector receiving member 50 relative to its central axis L′′.
  • One of the two cavities 50 b is shaped for slidingly and sealingly receiving one of the fuel injectors 52 therein.
  • the other of the two cavities 50 a faces away from the casing 20 and is also referred to as a first cooling cavity 50 a configured for receiving air from the environment E of the segmented fuel distributor 22 .
  • the air circulating in the first cooling cavity 50 a might reduce a temperature of the fuel carrying segment 24 .
  • the fuel injector receiving member 50 further defines a second cooling cavity 50 d configured for receiving a flow of air from the environment E and is fluidly connected with the first cooling cavity 50 a.
  • the secondary flow paths 40 extend through the fuel injector receiving members 50 such that the fuel injectors 52 are in fluid flow communication with the one of the two cavities 50 b .
  • Fuel cavities 56 are defined between the fuel injectors 52 and cylindrical walls of the fuel injector receiving members 50 .
  • the fuel cavities 56 are fluidly connected with the one of the two cavities 50 b and with the main conduit 34 via the secondary conduits 38 . Stated otherwise, the fuel cavities 56 are fluidly connected with the main flow path 36 via the secondary flow paths 40 .
  • the fuel injectors 52 define outlets 58 fluidly connected to the main conduit 34 via the secondary conduits 38 , along the main and secondary flow paths 36 and 40 , and via the fuel cavities 56 , for injecting fuel in the combustion chamber 30 .
  • Any suitable fuel injector may be used.
  • the fuel injectors 52 may be integrally formed with the fuel carrying segments 24 or separated as shown.
  • apertures 20 a are defined through the casing 20 for allowing the fuel injectors 52 to extend therethrough.
  • Each of the apertures 20 a is surrounded by a respective one of cylindrical protrusions 20 b , also referred to as slotted bosses, that are hollow for slidingly receiving the fuel injector receiving members 50 therein.
  • a diameter of the apertures 20 a is less than that of an inner diameter of the cylindrical protrusions 20 b to define annular tabs 20 c .
  • the fuel injector receiving members 50 once disposed within the cylindrical protrusions 20 b may abut against the annular tab 20 c.
  • the cylindrical protrusions 20 b are hollow and are each shaped for receiving therein a respective one of the fuel injector receiving members 50 of the fuel carrying segments 24 .
  • Each of the cylindrical protrusions 50 defines a slot 20 d for allowing the secondary conduits 38 to extend through the cylindrical protrusions 20 b .
  • inner surfaces of the cylindrical protrusions 20 b are threaded for receiving nuts 64 to be screwed therein to limit movements of the fuel injector receiving members 50 when they are received within the cylindrical protrusions 20 b .
  • the nuts 64 are hollow for allowing fluid flow communication between the first cooling cavity 50 a and the environment E.
  • gaskets 62 are disposed between the fuel injector receiving members 50 and the cylindrical protrusions 20 b for providing a sealing engagement therebetween.
  • the gaskets 62 are annular and disposed adjacent to the annular tabs 20 c to be sandwiched between said tabs 20 c and the fuel injector receiving members 50 . More specifically, air that has been compressed through its passage in the compressor section 14 is injected in the combustor chamber 30 for being mixed with fuel.
  • the gaskets 62 are configured to preclude the compressed air to escape the combustion chamber 30 via an intersection between the cylindrical protrusions 20 b and the fuel injector receiving members 50 .
  • the transfer tube assemblies 28 each include two transfer tubes 66 that are disposed within an outer sleeve 68 configured for maintaining a position of the transfer tubes 66 therein.
  • the main conduits 34 define two inlets 34 d each receiving a respective one of the transfer tubes 66 . It is understood that the transfer tube assemblies 28 may comprise less, or more, than two of the transfer tubes 66 . Similarly, the main conduits 34 may comprise less, or more, than two of the inlets 34 d .
  • the transfer tubes 66 are made of AMS 5648/SS 316 stainless steel or other suitable metal.
  • the secondary conduits 38 define each two fuel passages (not shown) each fluidly connected to a respective one of the two transfer tubes 66 . Therefore, the main flow path 36 defines two main sub-flow paths 36 a and 36 b and each of the secondary conduits 38 defines two secondary sub-flow paths 40 a and 40 b .
  • the two main sub-flow paths 36 a and 36 b are in fluid flow communication with a respective one of the two secondary sub-flow paths 40 a and 40 b .
  • the fuel injectors 52 have each two of the fuel outlets 58 each fluidly connected to a respective one of the two secondary sub-flow paths 40 a and 40 b.
  • connection C between the transfer tube assemblies 28 and the segments 24 offers a flexibility that allows some displacement of the segments 24 relative to the assemblies 28 . Such displacement might be the result of thermal expansion during use. More specifically, the flexibility is provided by the interaction between the transfer tubes 66 and the inlets 34 d of the main conduit 34 . In the embodiment shown, the connection C is flexible and allows variations of about ⁇ 3 degrees between a longitudinal axis of each of the transfer tubes 66 and the main conduit 34 of the segments 24 .
  • the outer sleeve 68 has a cylindrical shape and defines two ends 68 a and 68 b that have a diameter greater than that of a central section 68 c disposed between the two ends 68 a , 68 b .
  • two ends 68 a , 68 b are each configured for receiving therein the coupling portions 34 a ′ of the segments 24 ′.
  • O-rings may be disposed within the annular grooves 34 b ′ to create a sealing engagement between the coupling portions 34 a and the outer sleeve ends 68 a , 68 b.
  • the outer sleeve 68 further includes two tabs 68 d each defining an aperture.
  • the two tabs are diametrically opposed relative to a longitudinal axis of the outer sleeve 68 .
  • the tabs 68 d are configured for manipulating the outer sleeve 68 , and thus any transfer tube assemblies 28 mounted thereto, in order to position and move the transfer tube assemblies 28 and/or the outer sleeve 68 into or out of a desired position.
  • the tabs 68 d can be used to push or pull and simultaneously engage or disengage the transfer tubes and the outer sleeve with a corresponding fuel carrying segment 24 or fuel nozzle.
  • the outer sleeve 68 encloses a support member 68 e defining two apertures for receiving therein, and for supporting, the transfer tubes 66 .
  • the support member 68 e limits radial and/or axial movements of the tubes 66 relative to the outer sleeve 68 .
  • each of the two transfer tubes 66 have two sections 66 a , 66 b that are jointed together at a location of the support member 68 e .
  • Each of the two sections 66 a , 66 b defines abutment portions 66 c configured for abutting against the support member 68 e .
  • the abutment portions 66 c are configured to limit axial movement of each of the two sections 66 a , 66 b toward each other.
  • the fuel distribution segments 24 are first circumferentially distributed around the central axis of the combustor 11 . Then, the fuel distribution segments 24 are each fluidly connected with two respectively adjacent ones of the fuel distribution segments 24 with the transfer tubes 66 of the transfer tube assemblies 28 to form the segmented fuel distributor 22 . Then, the segmented fuel distributor 22 is secured to the casing 20 .
  • the fuel injector receiving members 50 are each secured to the casing 20 , within a respective one of the cylindrical protrusions 20 b , with the nuts 64 screwed in the cylindrical protrusions 20 b.
  • the two transfer tubes 66 are coupled with the inlets 34 d defined by the main conduits 34 of the fuel carrying segments 24 . Therefore, the fuel injectors 52 are each fluidly connected to both of the transfer tubes 66 via the connections C.
  • the fuel injector receiving members 50 are pushed in a sealing engagement against the gaskets 62 that abut against the annular tabs 20 c defined by the casing 20 .
  • the nut 64 may be used for that purpose.
  • the fuel injector receiving members 50 which are disposed at the remote ends 38 a ( FIG. 3 ) of the secondary conduits 38 are disposed in the cylindrical protrusions 20 b extending from the casing 20 .
  • the fuel injectors 52 are fluidly connected to the fuel injector receiving members 50 of the fuel distribution segments 24 during the assembly.
  • the transfer tube assemblies 28 are each slid and locked into position. More specifically, the outer sleeve ends 68 a are slid over first coupling portions 34 a of the main conduit 34 . Then, the transfer tube assemblies 28 are each slid toward second coupling portions 34 a of an adjacent one of the segments 24 . Then, the circlips 45 ( FIG. 3 a ) are each disposed within the second annular grooves 34 c ( FIG. 3 ) of the first coupling portions 34 a to limit a sliding movement between the outer sleeves 68 and the coupling portions 34 a.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
US15/726,447 2017-10-06 2017-10-06 Segmented fuel distributor Abandoned US20190107285A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US15/726,447 US20190107285A1 (en) 2017-10-06 2017-10-06 Segmented fuel distributor
CA3016780A CA3016780A1 (fr) 2017-10-06 2018-09-06 Repartiteur de carburant segmente

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US15/726,447 US20190107285A1 (en) 2017-10-06 2017-10-06 Segmented fuel distributor

Publications (1)

Publication Number Publication Date
US20190107285A1 true US20190107285A1 (en) 2019-04-11

Family

ID=65992247

Family Applications (1)

Application Number Title Priority Date Filing Date
US15/726,447 Abandoned US20190107285A1 (en) 2017-10-06 2017-10-06 Segmented fuel distributor

Country Status (2)

Country Link
US (1) US20190107285A1 (fr)
CA (1) CA3016780A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20220065167A1 (en) * 2019-07-22 2022-03-03 Delavan Inc. Sectional fuel manifolds
CN114877376A (zh) * 2022-06-02 2022-08-09 清航空天(北京)科技有限公司 一种双通道爆震燃烧室
US20240003298A1 (en) * 2022-07-04 2024-01-04 Pratt & Whitney Canada Corp. Adaptor for a fuel system of an aircraft engine
US12613035B1 (en) * 2024-09-16 2026-04-28 General Electric Company Combustion section for a turbine engine

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9140453B2 (en) * 2011-12-20 2015-09-22 Pratt & Whitney Canada Corp. Fuel manifold with jumper tubes
US9567910B2 (en) * 2013-07-22 2017-02-14 Rolls-Royce Plc Fuel manifold and fuel injector arrangement for a combustion chamber
US9732960B2 (en) * 2014-02-19 2017-08-15 United Technologies Corporation Fuel manifold for a gas turbine engine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9140453B2 (en) * 2011-12-20 2015-09-22 Pratt & Whitney Canada Corp. Fuel manifold with jumper tubes
US9567910B2 (en) * 2013-07-22 2017-02-14 Rolls-Royce Plc Fuel manifold and fuel injector arrangement for a combustion chamber
US9732960B2 (en) * 2014-02-19 2017-08-15 United Technologies Corporation Fuel manifold for a gas turbine engine

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20220065167A1 (en) * 2019-07-22 2022-03-03 Delavan Inc. Sectional fuel manifolds
US11713717B2 (en) * 2019-07-22 2023-08-01 Collins Engine Nozzles, Inc. Sectional fuel manifolds
US12196135B2 (en) 2019-07-22 2025-01-14 Delavan Inc. Sectional fuel manifolds
CN114877376A (zh) * 2022-06-02 2022-08-09 清航空天(北京)科技有限公司 一种双通道爆震燃烧室
US20240003298A1 (en) * 2022-07-04 2024-01-04 Pratt & Whitney Canada Corp. Adaptor for a fuel system of an aircraft engine
US12241416B2 (en) * 2022-07-04 2025-03-04 Pratt & Whitney Canada Corp. Adaptor for a fuel system of an aircraft engine
US12613035B1 (en) * 2024-09-16 2026-04-28 General Electric Company Combustion section for a turbine engine

Also Published As

Publication number Publication date
CA3016780A1 (fr) 2019-04-06

Similar Documents

Publication Publication Date Title
US11131458B2 (en) Fuel injectors for turbomachines
US9932903B2 (en) Fuel manifold and fuel injector arrangement
US8991192B2 (en) Fuel nozzle assembly for use as structural support for a duct structure in a combustor of a gas turbine engine
CA2597592C (fr) Montage de chambre de combustion et de collecteur de carburant de turbine a gaz
US10605171B2 (en) Fuel nozzle manifold systems for turbomachines
EP2829707B1 (fr) Collecteur de carburant et dispositif d'injection de carburant pour une chambre de combustion
US9523504B2 (en) Fuel manifold and fuel injector arrangement
US20190107285A1 (en) Segmented fuel distributor
US9790862B2 (en) Fuel manifold and fuel injector arrangement for a combustion chamber
US20180149364A1 (en) Combustor with axially staged fuel injection
US8033113B2 (en) Fuel injection system for a gas turbine engine
US10294865B2 (en) Internal manifold with fuel inlet
US9803555B2 (en) Fuel delivery system with moveably attached fuel tube
US11156362B2 (en) Combustor with axially staged fuel injection
EP3339609A1 (fr) Ensemble de montage pour conduit de fluide de moteur à turbine à gaz
US20180363907A1 (en) Liquid fuel cartridge unit for gas turbine combustor and method of assembly
US20200132303A1 (en) Combustor dome tiles
EP1734307B1 (fr) Collecteur de combustible interne avec goupilles de support
EP3633163B1 (fr) Ensemble collecteur de carburant
US20180363899A1 (en) Dual-fuel fuel nozzle with air shield
US11306660B2 (en) Transfer tube manifold with integrated plugs

Legal Events

Date Code Title Description
STPP Information on status: patent application and granting procedure in general

Free format text: DOCKETED NEW CASE - READY FOR EXAMINATION

AS Assignment

Owner name: PRATT & WHITNEY CANADA CORP., CANADA

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:MORENKO, OLEG;KOJOVIC, ALEKSANDAR;KISUN, GAVIN ROHITESHWAR;SIGNING DATES FROM 20170918 TO 20170921;REEL/FRAME:044838/0955

STPP Information on status: patent application and granting procedure in general

Free format text: NON FINAL ACTION MAILED

STPP Information on status: patent application and granting procedure in general

Free format text: NON FINAL ACTION MAILED

STPP Information on status: patent application and granting procedure in general

Free format text: FINAL REJECTION MAILED

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION