EP3404331B1 - Gas turbine engine combustor with a fuel air mixer assembly - Google Patents
Gas turbine engine combustor with a fuel air mixer assembly Download PDFInfo
- Publication number
- EP3404331B1 EP3404331B1 EP18173047.4A EP18173047A EP3404331B1 EP 3404331 B1 EP3404331 B1 EP 3404331B1 EP 18173047 A EP18173047 A EP 18173047A EP 3404331 B1 EP3404331 B1 EP 3404331B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustor
- fuel
- round
- swirler
- fuel air
- 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.)
- Active
Links
- 239000000446 fuel Substances 0.000 title claims description 99
- 230000000712 assembly Effects 0.000 claims description 48
- 238000000429 assembly Methods 0.000 claims description 48
- 239000007921 spray Substances 0.000 claims description 23
- 239000000203 mixture Substances 0.000 claims description 15
- 238000002485 combustion reaction Methods 0.000 description 16
- 239000007789 gas Substances 0.000 description 8
- 238000001816 cooling Methods 0.000 description 4
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000006641 stabilisation Effects 0.000 description 2
- 238000011105 stabilization Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 239000004215 Carbon black (E152) Substances 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 239000003607 modifier Substances 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000003954 pattern orientation Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 230000002028 premature Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
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
- F23R3/286—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
- F23R3/002—Wall structures
-
- 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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
Description
- The present disclosure relates to a gas turbine engine and, more particularly, to a fuel air mixer assembly for a combustor section therefor.
- Gas turbine engines, such as those which power modern commercial and military aircraft, include a compressor for pressurizing a supply of air, a combustor for burning a hydrocarbon fuel in the presence of the pressurized air, and a turbine for extracting energy from the resultant combustion gases. The combustor generally includes radially spaced apart inner and outer wall assemblies that define an annular combustion chamber therebetween.
- Gas turbine combustors typically utilize a fuel nozzle integrated with air introduction that effectively mixes the fuel spray with air to generate a fine spray for ignition and continuous combustion. The fuel air mixer assembly in most modern combustors includes a swirler where one or more air passages interact with one or more fuel passages from a fuel nozzle.
- The fuel air mixer assembly includes slots or holes radially outboard of the fuel nozzle to interact as a system to provide an atomized fuel-air mixture that is conical in shape. These axisymmetric conical fuel air mixtures provide flame patterns which form uniform periodic horseshoe shaped impact, or "touchdown regions," on the combustor wall surfaces which may ultimately form hot spots that may result in premature failure.
-
US 2014/165578 A1 discloses a combustor having an ovate shaped swirler arranged around a fuel injector. A further prior art fuel air mixer assembly is disclosed inUS 5,937,653 A . - A combustor according to one aspect of the present invention is provided as recited in
claim 1. - An aspect of the present disclosure includes, wherein the non-round fuel nozzle includes a multiple of fuel jets, a first of the multiple of fuel jets of a size different than a second of the multiple of fuel jets.
- A further aspect of the present disclosure includes, wherein the non-round fuel nozzle is elliptical in cross-section.
- A further aspect of the present disclosure includes, wherein the non-round fuel nozzle is rectilinear in cross-section.
- A further aspect of the present disclosure includes, wherein the non-round swirler of each of the respective multiple of fuel air mixer assemblies is arranged such that a major axis of the cross-section thereof is clocked relative to the major axis of an adjacent one of the multiple of mixer assemblies.
- A further aspect of the present disclosure includes, wherein the swirler of each of the respective multiple of fuel air mixer assemblies is arranged such that a major axis of the cross-section thereof is clocked to define a circular distribution around an engine central longitudinal axis.
- A further aspect of the present disclosure includes, wherein the fuel-air mixture pattern from each of the respective multiple of fuel air mixer assemblies at least partially overlaps an adjacent one of the respective multiple of mixer assemblies.
- A further aspect of the present disclosure includes, wherein the swirler of each of the respective multiple of fuel air mixer assemblies is arranged such that a major axis of the cross-section thereof is oriented to be generally parallel with respect to an inner and outer combustor liner assembly.
- A further aspect of the present disclosure includes, wherein the swirler of each of the respective multiple of fuel air mixer assemblies is arranged such that a major axis of the cross-section thereof is clocked with respect to an inner and outer combustor liner assembly.
- A further aspect of the present disclosure includes, wherein the swirler of each of the respective multiple of fuel air mixer assemblies is arranged such that a major axis of the cross-section thereof is clocked to form a circular arrangement around an engine axis.
- A further aspect of the present disclosure includes, wherein the swirler of at least one of the multiple of fuel air mixer assemblies is arranged such that a major axis of a cross-section thereof is clocked relative to at least one other of the multiple of mixer assemblies.
- A further aspect of the present disclosure includes, wherein the fuel nozzle of at least one of the multiple of fuel air mixer assemblies is arranged such that a major axis of a cross-section thereof is clocked relative to at least one other of the multiple of mixer assemblies.
- "Clocked" as defined herein refers to the rotational position of the non-round swirler around the swirler axis.
- The foregoing features and elements may be combined in various combinations without exclusivity, unless expressly indicated otherwise. These features and elements as well as the operation thereof will become more apparent in light of the following description and the accompanying drawings. It should be appreciated, however, that the following description and drawings are intended to be exemplary in nature and non-limiting.
- Various features will become apparent to those skilled in the art from the following detailed description of the disclosed non-limiting embodiment. The drawings that accompany the detailed description can be briefly described as follows:
-
FIG. 1 is a schematic cross-section of an example of gas turbine engine architecture. -
FIG. 2 is an expanded longitudinal schematic sectional view of a combustor section. -
FIG. 3 is a perspective partial longitudinal sectional view of the combustor section. -
FIG. 4 is a sectional view of a fuel air mixer assembly. -
FIG. 5 is a face view of a bulkhead assembly with a multiple of fuel air mixer assemblies indicating a spray pattern orientation according to one disclosed non-limiting embodiment. -
FIG. 6 is a schematic view of a fuel air mixer assembly according to another disclosed non-limiting embodiment. -
FIG. 7 is a schematic view of a fuel air mixer assembly according to another disclosed non-limiting embodiment. -
FIG. 8 is a schematic view of a fuel nozzle according to a configuration which is not part of the present invention. -
FIG. 1 schematically illustrates agas turbine engine 20. Thegas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates afan section 22, acompressor section 24, acombustor section 26 and aturbine section 28. Thefan section 22 drives air along a bypass flowpath while thecompressor section 24 drives air along a core flowpath for compression and communication into thecombustor section 26 then expansion through theturbine section 28. Although depicted as a turbofan in the disclosed non-limiting embodiment, it should be appreciated that the concepts described herein are not limited to use with turbofans as the teachings may be applied to other types of turbine engines such as a turbojets, turboshafts, and three-spool (plus fan) turbofans. - The
engine 20 generally includes alow spool 30 and ahigh spool 32 mounted for rotation about an engine central longitudinal axis A relative to an enginestatic structure 36 viaseveral bearing structures 38. Thelow spool 30 generally includes aninner shaft 40 that interconnects afan 42, a low pressure compressor ("LPC") 44 and a low pressure turbine ("LPT") 46. Theinner shaft 40 drives thefan 42 directly or through a gearedarchitecture 48 to drive thefan 42 at a lower speed than thelow spool 30. An exemplary reduction transmission is an epicyclic transmission, namely a planetary or star gear system. - The
high spool 32 includes anouter shaft 50 that interconnects a high pressure compressor ("HPC") 52 and high pressure turbine ("HPT") 54. Acombustor 56 is arranged between thehigh pressure compressor 52 and thehigh pressure turbine 54. Theinner shaft 40 and theouter shaft 50 are concentric and rotate about the engine central longitudinal axis A which is collinear with their longitudinal axes. - Core airflow is compressed by the
LPC 44, then the HPC 52, mixed with the fuel and burned in thecombustor 56, then expanded over the HPT 54 and theLPT 46. The HPT 54 andLPT 46 rotationally drive the respectivelow spool 30 andhigh spool 32 in response to the expansion. - With reference to
FIG. 2 , thecombustor section 26 generally includes acombustor 56 with an outercombustor wall assembly 60, an innercombustor wall assembly 62 and adiffuser case module 64. The outercombustor wall assembly 60 and the innercombustor wall assembly 62 are spaced apart such that acombustion chamber 66 is defined therebetween. Thecombustion chamber 66 is generally annular in shape. - The outer
combustor wall assembly 60 is spaced radially inward from anouter diffuser case 64A of thediffuser case module 64 to define an outerannular plenum 76. The innercombustor wall assembly 62 is spaced radially outward from aninner diffuser case 64B of thediffuser case module 64 to define an innerannular plenum 78. It should be appreciated that although a particular combustor is illustrated, other combustor types with various combustor liner arrangements will also benefit herefrom. It should be further appreciated that the disclosed cooling flow paths are but an illustrated embodiment and should not be limited only thereto. - In this example, the combustor wall assemblies 60, 62 contain the combustion products for direction toward the
turbine section 28. Eachcombustor wall assembly respective support shell respective support shell combustor wall assemblies - Each of the liner panels 72, 74 may be generally rectilinear and manufactured of, for example, a nickel based super alloy, ceramic or other temperature resistant material and are arranged to form a liner array. The liner array includes a multiple of
forward liner panels aft liner panels forward liner panels aft liner panels FIG. 3 ). - The
combustor 56 further includes aforward assembly 80 immediately downstream of thecompressor section 24 to receive compressed airflow therefrom. Theforward assembly 80 generally includes anannular hood 82, abulkhead assembly 84, a multiple offuel injectors 86 and a multiple ofswirlers fuel injectors 86 and the multiple ofswirlers FIG. 4 ) for a Rich-Quench-Lean (RQL) combustor that directs the fuel-air mixture into the combustor chamber generally along an axis F, also referred to as a swirler axis F. It should be appreciated that although a RQL combustor is disclosed in the illustrated embodiment, other combustor technologies such as a Lean Premixed (LP) combustor will also benefit herefrom. - The
bulkhead assembly 84 includes abulkhead support shell 96 secured to thecombustor wall assemblies bulkhead liner panels 98 secured to the bulkhead support shell 96 (FIG. 2 ). Theannular hood 82 extends radially between, and is secured to, the forwardmost ends of thecombustor wall assemblies annular hood 82 includes a multiple of circumferentially distributedhood ports 94 that accommodate therespective fuel injectors 86 and direct air into the forward end of thecombustion chamber 66 through therespective swirler - The
forward assembly 80 introduces primary combustion air into the forward section of thecombustion chamber 66 while the remainder enters the outerannular plenum 76 and the innerannular plenum 78. The multiple of fuelair mixer assemblies 102 and adjacent structure generate a blended fuel-air mixture that supports stable combustion in thecombustion chamber 66. - Opposite the
forward assembly 80, the outer andinner support shells HPT 54 to define a combustor exit. TheNGVs 54A are static engine components which direct combustion gases onto a first turbine rotor in theturbine section 28 to facilitate the conversion of pressure energy into kinetic energy. - With reference to
FIG. 4 , each of the multiple of fuelair mixer assemblies 102 includes afuel nozzle 100 of thefuel injector 86 that is at least partially received within thenon-round swirler mixture spray pattern 104. Thefuel nozzle 100 is non-round. Eachfuel nozzle 100 is located within therespective non-round swirler combustion chamber 66. As defined herein, a "swirler" may generate, for example, a counterrotating swirl, a specific swirl which provides a resultant swirl or a residual net swirl which may be further directed at an angle. It should be appreciated that various combinations thereof may alternatively be utilized. Thenon-round swirler - The
non-round swirler FIG. 5 ). The adjective "elliptical" is used herein as an example swirler or swirler component having a major diameter extending in a radial direction greater than a minor diameter extending in a circumferential direction about the axis F. - The
non-round swirler inner shroud 108 positioned around thefuel nozzle 100 to form afuel air exit 109 and anouter shroud 110 positioned radially outward from theinner shroud 108 to define an air exit 113 (FIG. 6 ). Afuel nozzle guide 111 may house thefuel nozzle 100 to form a rear housing in relation to theswirler body fuel nozzle 100 therein and to accommodate thermal excursions. A plurality ofswirler vanes shrouds 108 andfuel nozzle guide 111 such that combustion air may enter into the combustion chamber through a plurality of air passages between theswirler vanes first swirler 114 is positioned around thenozzle 100 as described above and asecond swirler 116 is positioned radially outward from thefirst swirler 114. In such an arrangement, theinner shroud 108 and theouter shroud 110 of thesecond swirler 116 may be joined by a second plurality ofvanes 118. - The elliptical fuel-
air mixture pattern 104 and resultant elliptical flame pattern may be beneficial compared to a fully conical axis-symmetric spray in that the elliptical fuel-air mixture pattern 104 orientation can be tailored to the combustion chamber (FIG. 5 ). For annular combustors, thecombustor wall assemblies HPT 54. The elliptical flame pattern of each fuelair mixer assembly 102 is appropriately clocked to minimize impact on thecombustor wall assemblies 60, 62 (FIG. 6 ). - The volume of the combustor is related to combustion efficiency, emissions, and ultimately, the exit temperature profile. The
combustor wall assemblies combustor wall assemblies non-round swirler combustor wall assemblies - With reference to
FIG. 5 , thenon-round swirlers elliptical spray patterns 104 are generally oriented such that amajor axis 103 thereof is clocked around the engine axis A. Each of theelliptical spray patterns 104 is clocked to define a circular distribution in which the Z-axis thereof is collinear with the engine central longitudinal axis A in an X-Y-Z coordinate system. In other words, the engine central longitudinal axis A represents the Z-axis in the X-Y-Z coordinate system of thenon-round swirler elliptical spray pattern 104. In this distribution, each of the adjacentelliptical spray patterns 104 provides anoverlap area 105 which facilitates a contiguous annular flame pattern while limiting the flame spread in the radialminor axis 107 direction to minimize a "touchdown region" on the surfaces of the inner and outercombustor wall assemblies - The spray pattern of the fuel air mixture exiting the
swirlers combustor wall assemblies combustor wall assemblies combustor wall assemblies - The shape of the fuel spray and resulting flame can be tailored in shape by the swirler shape and/or air passages thereof as well as the fuel nozzle spray pattern. That is, the
major axis 103 of thenon-round swirler non-round fuel nozzle 100. Furthermore, thenon-round fuel nozzle 100 can also be tailored or clocked with respect to the shape of thenon-round swirler - With reference to
FIG. 6 , in another embodiment, thenon-round fuel nozzle 100A is of an elliptical shape to correspond with the generallynon-round swirler - With reference to
FIG. 7 , in another embodiment, thenon-round fuel nozzle 100B is of a rectilinear or flat shape that is oriented with the generallynon-round swirler - With reference to
FIG. 8 , which shows a configuration outside the wording of the claims, thefuel nozzle 100C may alternatively include a multiple of fuel jets 200 that includefuel jets fuel nozzle body 202 is round, in a configuration outside the wording of the claims. In an embodiment, thefuel nozzle body 202 is non-round but the fuel jets 200 are tailored in size to provide various fuel spray patterns to interact with thenon-round swirler - The
non-round swirler elliptical spray pattern 104 such that the flame has minimal impact on thecombustor wall assemblies non-round swirler swirlers 114, 116 (FIG. 5 ) can also be optimized to improve exit temperature quality, which results in a hot gas profile that exits thecombustor 66 in a more uniform manner. This, for example, translates to improved turbine vane and airfoil durability that may be a significant driver for engine maintenance costs. - The use of the terms "a" and "an" and "the" and similar references in the context of description (especially in the context of the following claims) are to be construed to cover both the singular and the plural, unless otherwise indicated herein or specifically contradicted by context. The modifier "about" used in connection with a quantity is inclusive of the stated value and has the meaning dictated by the context (e.g., it includes the degree of error associated with measurement of the particular quantity). All ranges disclosed herein are inclusive of the endpoints, and the endpoints are independently combinable with each other. It should be appreciated that relative positional terms such as "forward," "aft," "upper," "lower," "above," "below," and the like are with reference to the normal operational attitude of the vehicle and should not be considered otherwise limiting.
- It should be appreciated that like reference numerals identify corresponding or similar elements throughout the several drawings. It should also be appreciated that although a particular component arrangement is disclosed in the illustrated embodiment, other arrangements will benefit herefrom.
Claims (13)
- A combustor (56) for a gas turbine engine (20), comprising:a multiple of fuel air mixer assemblies (102) defined around an engine central longitudinal axis (A), wherein each of the fuel air mixer assemblies (102) comprises a non-round swirler (114, 116) arranged along a swirler axis (F), and a fuel nozzle (100) received at least partially within the non-round swirler (114, 116) and arranged along the swirler axis (F), the non-round swirler (114, 116) is elliptical in cross-section, and each of the fuel air mixer assemblies (102) is operable to provide a non-round fuel air mixture spray pattern,characterized in that the fuel nozzle (100) of each of the fuel air mixer assemblies (102) is non-round in cross-section and is arranged such that a major axis of its cross-section is clocked around the engine axis (A).
- The combustor as recited in claim 1, wherein a major axis (103) of the cross-section of the non-round swirler (114, 116) coincides with the major axis of the cross-section of the fuel nozzle (100).
- The combustor as recited in claim 1 or 2, wherein the fuel nozzle (100) includes a multiple of fuel jets (200A, 200B), and a first of the fuel jets (200A, 200B) is of a different size to a second of the fuel jets (200A, 200B).
- The combustor as recited in claim 1, 2 or 3, wherein the fuel nozzle (100) is elliptical (100A) or rectilinear (100B) in cross-section.
- The combustor as recited in any preceding claim, wherein each non-round fuel air mixture spray pattern at least partially overlaps an adjacent non-round fuel air mixture spray pattern.
- The combustor as recited in any preceding claim, wherein each of the fuel air mixer assemblies (102) is clocked in relation to the circumferential position within the combustor (56).
- The combustor as recited in any preceding claim, wherein the non-round swirler (114, 116) of each of the fuel air mixer assemblies (102) is arranged such that a major axis (103) of the cross-section thereof is clocked relative to the maj or axis (103) of the cross-section of an adjacent one of the fuel air mixer assemblies (102).
- The combustor as recited in any preceding claim, wherein the non-round swirler (114, 116) of each of the fuel air mixer assemblies (102) is arranged such that a major axis (103) of the cross-section thereof is clocked to define a circular distribution around an engine axis.
- The combustor as recited in any preceding claim, wherein the non-round fuel air mixture spray pattern from each of the fuel air mixer assemblies (102) at least partially overlaps an adjacent one of the fuel air mixer assemblies (102).
- The combustor as recited in any preceding claim, wherein the non-round swirler (114, 116) of each of the fuel air mixer assemblies (102) is arranged such that a major axis (103) of the cross-section thereof is oriented to be generally parallel with respect to an inner and outer combustor wall assembly (60, 62).
- The combustor as recited in any of claims 1 to 9, wherein the non-round swirler (114, 116) of each of the fuel air mixer assemblies (102) is arranged such that a major axis (103) of the cross-section thereof is clocked with respect to an inner and outer combustor wall assembly (60, 62).
- The combustor as recited in any preceding claim, wherein the non-round swirler (114, 116) of at least one of the fuel air mixer assemblies (102) is arranged such that a major axis (103) of the cross-section thereof is clocked relative to at least one other of the fuel air mixer assemblies (102).
- The combustor as recited in any preceding claim, wherein the fuel nozzle (100) of at least one of the fuel air mixer assemblies (102) is arranged such that a major axis of the cross-section thereof is clocked relative to at least one other of the fuel air mixer assemblies (102).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US15/599,252 US20180335214A1 (en) | 2017-05-18 | 2017-05-18 | Fuel air mixer assembly for a gas turbine engine combustor |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3404331A1 EP3404331A1 (en) | 2018-11-21 |
EP3404331B1 true EP3404331B1 (en) | 2022-07-06 |
Family
ID=62200331
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP18173047.4A Active EP3404331B1 (en) | 2017-05-18 | 2018-05-17 | Gas turbine engine combustor with a fuel air mixer assembly |
Country Status (2)
Country | Link |
---|---|
US (1) | US20180335214A1 (en) |
EP (1) | EP3404331B1 (en) |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10591163B2 (en) * | 2017-07-21 | 2020-03-17 | United Technologies Corporation | Swirler for combustor of gas turbine engine |
GB201806631D0 (en) * | 2018-04-24 | 2018-06-06 | Rolls Royce Plc | A combustion chamber arrangement and a gas turbine engine comprising a combustion chamber arrangement |
CN110345513B (en) * | 2019-07-12 | 2021-04-16 | 中国航发沈阳发动机研究所 | Cyclone atomization device for staged combustion |
JP7446077B2 (en) | 2019-10-04 | 2024-03-08 | 三菱重工業株式会社 | Gas turbine combustor, gas turbine and oil fuel combustion method |
US11378275B2 (en) * | 2019-12-06 | 2022-07-05 | Raytheon Technologies Corporation | High shear swirler with recessed fuel filmer for a gas turbine engine |
CN112240568B (en) * | 2020-09-11 | 2022-10-28 | 北京动力机械研究所 | Water-cooling cylindrical rectifier for stable combustion of heater |
US11725824B2 (en) | 2021-04-08 | 2023-08-15 | Raytheon Technologies Corporation | Turbulence generator mixer for rotating detonation engine |
US20230204215A1 (en) * | 2021-12-29 | 2023-06-29 | General Electric Company | Fuel nozzle and swirler |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9303875B2 (en) * | 2012-02-08 | 2016-04-05 | Rolls-Royce Deutschland Ltd & Co Kg | Gas-turbine combustion chamber having non-symmetrical fuel nozzles |
Family Cites Families (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1445208A (en) * | 1920-12-30 | 1923-02-13 | Chauncey B Forward | Oil burner |
US2012139A (en) * | 1933-07-24 | 1935-08-20 | Peabody Engineering Corp | Atomizer |
SE352139B (en) * | 1968-07-09 | 1972-12-18 | Lucas Ltd Joseph | |
US3521824A (en) * | 1968-10-11 | 1970-07-28 | Delavan Manufacturing Co | Air-liquid flat spray nozzle |
US3763650A (en) * | 1971-07-26 | 1973-10-09 | Westinghouse Electric Corp | Gas turbine temperature profiling structure |
US4218020A (en) * | 1979-02-23 | 1980-08-19 | General Motors Corporation | Elliptical airblast nozzle |
US4991398A (en) * | 1989-01-12 | 1991-02-12 | United Technologies Corporation | Combustor fuel nozzle arrangement |
US5373694A (en) * | 1992-11-17 | 1994-12-20 | United Technologies Corporation | Combustor seal and support |
FR2751054B1 (en) * | 1996-07-11 | 1998-09-18 | Snecma | ANNULAR TYPE FUEL INJECTION ANTI-NOX COMBUSTION CHAMBER |
US6119459A (en) * | 1998-08-18 | 2000-09-19 | Alliedsignal Inc. | Elliptical axial combustor swirler |
DE10348604A1 (en) * | 2003-10-20 | 2005-07-28 | Rolls-Royce Deutschland Ltd & Co Kg | Fuel injector with filmy fuel placement |
DE102006032429A1 (en) * | 2006-07-13 | 2008-02-21 | Rolls-Royce Deutschland Ltd & Co Kg | Fuel injection device for an aircraft gas turbine |
ATE528589T1 (en) * | 2008-08-04 | 2011-10-15 | Siemens Ag | SWIRLERS |
US8474265B2 (en) * | 2009-07-29 | 2013-07-02 | General Electric Company | Fuel nozzle for a turbine combustor, and methods of forming same |
US9366440B2 (en) * | 2012-01-04 | 2016-06-14 | General Electric Company | Fuel nozzles with mixing tubes surrounding a liquid fuel cartridge for injecting fuel in a gas turbine combustor |
US9322336B2 (en) * | 2012-12-06 | 2016-04-26 | General Electric Company | Fuel nozzle for gas turbine |
GB201222304D0 (en) * | 2012-12-12 | 2013-01-23 | Rolls Royce Plc | A fuel injector and a gas turbine engine combustion chamber |
US9404656B2 (en) * | 2012-12-17 | 2016-08-02 | United Technologies Corporation | Oblong swirler assembly for combustors |
US9376985B2 (en) * | 2012-12-17 | 2016-06-28 | United Technologies Corporation | Ovate swirler assembly for combustors |
US9791153B2 (en) * | 2015-02-27 | 2017-10-17 | United Technologies Corporation | Line replaceable fuel nozzle apparatus, system and method |
US20170003023A1 (en) * | 2015-07-01 | 2017-01-05 | Profire Energy, Inc | Dual trim valve cartridge and system |
GB201516977D0 (en) * | 2015-09-25 | 2015-11-11 | Rolls Royce Plc | A Fuel Injector For A Gas Turbine Engine Combustion Chamber |
-
2017
- 2017-05-18 US US15/599,252 patent/US20180335214A1/en not_active Abandoned
-
2018
- 2018-05-17 EP EP18173047.4A patent/EP3404331B1/en active Active
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9303875B2 (en) * | 2012-02-08 | 2016-04-05 | Rolls-Royce Deutschland Ltd & Co Kg | Gas-turbine combustion chamber having non-symmetrical fuel nozzles |
Also Published As
Publication number | Publication date |
---|---|
EP3404331A1 (en) | 2018-11-21 |
US20180335214A1 (en) | 2018-11-22 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP3404331B1 (en) | Gas turbine engine combustor with a fuel air mixer assembly | |
US11156359B2 (en) | Combustor liner panel end rail with diffused interface passage for a gas turbine engine combustor | |
EP3008391B1 (en) | Combustor with axial staging for a gas turbine engine | |
US10436449B2 (en) | Light weight swirler for gas turbine engine combustor and a method for lightening a swirler for a gas turbine engine | |
US10738704B2 (en) | Pilot/main fuel shifting in an axial staged combustor for a gas turbine engine | |
EP3087266B1 (en) | Multi-streamed dilution hole configuration for a gas turbine engine and relating method of operation | |
EP3301372B1 (en) | Circumferential fuel shifting and biasing in an axial staged combustor for a gas turbine engine | |
US10830448B2 (en) | Combustor liner panel with a multiple of heat transfer augmentors for a gas turbine engine combustor | |
US11365884B2 (en) | Radial fuel shifting and biasing in an axial staged combustor for a gas turbine engine | |
US11226102B2 (en) | Fuel nozzle for a gas turbine engine | |
EP3333486B1 (en) | Main mixer for a gas turbine engine combustor | |
US10830433B2 (en) | Axial non-linear interface for combustor liner panels in a gas turbine combustor | |
EP3321585B1 (en) | Non-planar combustor liner panel for a gas turbine engine combustor |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
AX | Request for extension of the european patent |
Extension state: BA ME |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE |
|
17P | Request for examination filed |
Effective date: 20190521 |
|
RBV | Designated contracting states (corrected) |
Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: EXAMINATION IS IN PROGRESS |
|
17Q | First examination report despatched |
Effective date: 20200619 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: EXAMINATION IS IN PROGRESS |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: RAYTHEON TECHNOLOGIES CORPORATION |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: GRANT OF PATENT IS INTENDED |
|
INTG | Intention to grant announced |
Effective date: 20210624 |
|
GRAJ | Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted |
Free format text: ORIGINAL CODE: EPIDOSDIGR1 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: EXAMINATION IS IN PROGRESS |
|
INTC | Intention to grant announced (deleted) | ||
GRAJ | Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted |
Free format text: ORIGINAL CODE: EPIDOSDIGR1 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: GRANT OF PATENT IS INTENDED |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
INTG | Intention to grant announced |
Effective date: 20220114 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE PATENT HAS BEEN GRANTED |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: REF Ref document number: 1503103 Country of ref document: AT Kind code of ref document: T Effective date: 20220715 Ref country code: CH Ref legal event code: EP |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 602018037490 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D |
|
REG | Reference to a national code |
Ref country code: LT Ref legal event code: MG9D |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: MP Effective date: 20220706 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 Ref country code: RS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 Ref country code: PT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20221107 Ref country code: NO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20221006 Ref country code: NL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 Ref country code: LV Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 Ref country code: LT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 Ref country code: FI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 Ref country code: ES Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MK05 Ref document number: 1503103 Country of ref document: AT Kind code of ref document: T Effective date: 20220706 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: PL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 Ref country code: IS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20221106 Ref country code: HR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 Ref country code: GR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20221007 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 602018037490 Country of ref document: DE |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SM Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 Ref country code: RO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 Ref country code: DK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 Ref country code: CZ Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 Ref country code: AT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 Ref country code: EE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 |
|
26N | No opposition filed |
Effective date: 20230411 |
|
P01 | Opt-out of the competence of the unified patent court (upc) registered |
Effective date: 20230521 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: AL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20230420 Year of fee payment: 6 Ref country code: DE Payment date: 20230419 Year of fee payment: 6 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20230420 Year of fee payment: 6 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MC Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 |
|
REG | Reference to a national code |
Ref country code: BE Ref legal event code: MM Effective date: 20230531 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MC Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 Ref country code: LU Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20230517 Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20230531 Ref country code: IT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20230531 |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: MM4A |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20230517 |