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公开(公告)号：US11519604B2
公开(公告)日：2022-12-06
申请号：US17305202
申请日：2021-07-01
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Nagaraja S. Rudrapatna , Atul Verma , David Chou , Christopher Zollars
IPC: F23R3/04
Abstract: A combustor for a gas turbine engine includes a liner having a first surface, a second surface opposite the first surface, and defining a plurality of effusion cooling holes. At least one of the effusion cooling holes includes an inlet section and a converging section downstream of the inlet section. The at least one of the effusion cooling holes includes a metering section downstream of the converging section. The at least one of the effusion cooling holes includes an outlet section downstream of the metering section. The outlet section is proximate to the second surface. The inlet section, the converging section, the metering section and the outlet section extend along a longitudinal axis, with the inlet section asymmetrical relative to the longitudinal axis and the metering section symmetrical relative to the longitudinal axis.
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公开(公告)号：US11306659B2
公开(公告)日：2022-04-19
申请号：US16423579
申请日：2019-05-28
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Nagaraja Rudrapatna
Abstract: An effusion cooling hole for a component associated with a gas turbine engine extends along a longitudinal axis. The effusion cooling hole includes an inlet section spaced apart from a first surface of the component. The inlet section includes a face orientated transverse to the first surface and defines an inlet through the face that has a first diameter. The effusion cooling hole includes an outlet at a second surface of the component and downstream from the inlet section. The effusion cooling hole includes a diverging section downstream from the inlet section and upstream from the outlet. The diverging section is defined substantially external to a thickness of the component, and the effusion cooling hole transitions from the first diameter to a second diameter at the diverging section. The effusion cooling hole includes an intermediate section that fluidly connects the diverging section to the outlet.
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公开(公告)号：US10816211B2
公开(公告)日：2020-10-27
申请号：US15686533
申请日：2017-08-25
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Sunil James
Abstract: A combustion system and a method of combustion for a gas turbine engine includes a combustor liner defining a combustion chamber. A plurality of fuel nozzle sets extend into, and supply fuel flow to, the combustion chamber. A pilot fuel nozzle injects a first fuel spray in a tangential direction relative to the combustion liner and toward the upstream end of the combustion chamber. A main fuel nozzle injects a second fuel spray toward the exit end of the combustion chamber. At ignition conditions, a majority of the fuel flow is injected through the pilot fuel nozzles, and at high power conditions a majority of the fuel flow is injected through the main fuel nozzles. At high power conditions, a fuel rich mixture is supplied to the combustion chamber, and a row of quench jets are configured to supply air to the combustion chamber, providing rich-quench-lean combustion.
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公开(公告)号：US10101030B2
公开(公告)日：2018-10-16
申请号：US14475106
申请日：2014-09-02
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Eric Blumer
Abstract: A combustor for a turbine engine is provided. A first liner has a first surface and a second surface. A second liner forms a combustion chamber with the second side of the first liner, and the combustion chamber configured to receive an air-fuel mixture for combustion therein. The first liner defines a plurality of effusion cooling holes configured to form a film of cooling air on the second surface of the first liner. The plurality of effusion cooling holes includes a first effusion cooling hole extending from the first surface to the second surface and including an inlet portion extending from the first surface, a metering portion fluidly coupled to the inlet portion, and an outlet portion fluidly coupled to the metering portion and extending to the second surface. The inlet portion is larger than the metering portion.
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公开(公告)号：US09400110B2
公开(公告)日：2016-07-26
申请号：US13656219
申请日：2012-10-19
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Terrel Kuhn , Vinayender Kuchana , Veeraraghava Raju Hasti , Raymond Gage , Sunil James
CPC classification number: F23R3/002 , F23R3/06 , F23R3/16 , F23R3/54 , F23R2900/00015 , F23R2900/03041 , Y02T50/675
Abstract: A combustor for a gas turbine engine is provided. The combustor includes an annular inner liner; an annular outer liner circumscribing the annular inner liner; and a combustor dome having a first edge coupled to the annular inner liner and a second edge coupled to the annular outer liner, the combustor dome forming a combustion chamber with the annular inner liner and the annular outer liner. The combustion chamber accommodates fluid flow through the annular inner and annular outer liners. The combustion chamber converges in the direction of the air flow to reduce a diameter of the combustion chamber. The combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the annular inner liner and a second stream directed to the annular outer liner.
Abstract translation: 提供了一种用于燃气涡轮发动机的燃烧器。 燃烧器包括环形内衬; 围绕所述环形内衬的环形外衬套; 以及燃烧器穹顶，其具有联接到所述环形内衬的第一边缘和连接到所述环形外衬垫的第二边缘，所述燃烧器圆顶形成具有所述环形内衬和所述环形外衬套的燃烧室。 燃烧室容纳通过环形内环和外环的外衬的流体流。 燃烧室在空气流的方向上会聚，以减小燃烧室的直径。 燃烧器穹顶构造成将燃烧器穹顶处的空气流分叉成指向环形内衬的第一流和指向环形外衬套的第二流。
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Patent Agency Ranking
公开(公告)号：US20240110520A1
公开(公告)日：2024-04-04
申请号：US18054177
申请日：2022-11-10
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout
CPC classification number: F02C7/232 , F23R3/28 , F05D2220/323 , F05D2240/35
Abstract: A gaseous fuel nozzle includes a main body, a plurality of inner air injection passages having inlet and outlet ports, a plurality of outer air injection passages having inlet and outlet ports, and a plurality of gaseous fuel injection passages having inlet and outlet ports. At least the gaseous fuel injection outlet ports are disposed concentrically about an axis of symmetry and between the plurality of inner air injection nozzle outlet ports and the plurality of outer air injection nozzle outlet ports.
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公开(公告)号：US20190063754A1
公开(公告)日：2019-02-28
申请号：US15686533
申请日：2017-08-25
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Sunil James
Abstract: A combustion system and a method of combustion for a gas turbine engine includes a combustor liner defining a combustion chamber. A plurality of fuel nozzle sets extend into, and supply fuel flow to, the combustion chamber. A pilot fuel nozzle injects a first fuel spray in a tangential direction relative to the combustion liner and toward the upstream end of the combustion chamber. A main fuel nozzle injects a second fuel spray toward the exit end of the combustion chamber. At ignition conditions, a majority of the fuel flow is injected through the pilot fuel nozzles, and at high power conditions a majority of the fuel flow is injected through the main fuel nozzles. At high power conditions, a fuel rich mixture is supplied to the combustion chamber, and a row of quench jets are configured to supply air to the combustion chamber, providing rich-quench-lean combustion.
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公开(公告)号：US20140109581A1
公开(公告)日：2014-04-24
申请号：US13656219
申请日：2012-10-19
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Terrel Kuhn , Vinayender Kuchana , Veeraraghava Raju Hasti , Raymond Gage , Sunil James
CPC classification number: F23R3/002 , F23R3/06 , F23R3/16 , F23R3/54 , F23R2900/00015 , F23R2900/03041 , Y02T50/675
Abstract: A combustor for a gas turbine engine is provided. The combustor includes an annular inner liner; an annular outer liner circumscribing the annular inner liner; and a combustor dome having a first edge coupled to the annular inner liner and a second edge coupled to the annular outer liner, the combustor dome forming a combustion chamber with the annular inner liner and the annular outer liner. The combustion chamber accommodates fluid flow through the annular inner and annular outer liners. The combustion chamber converges in the direction of the air flow to reduce a diameter of the combustion chamber. The combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the annular inner liner and a second stream directed to the annular outer liner.
Abstract translation: 提供了一种用于燃气涡轮发动机的燃烧器。 燃烧器包括环形内衬; 围绕所述环形内衬的环形外衬套; 以及燃烧器穹顶，其具有联接到所述环形内衬的第一边缘和联接到所述环形外衬垫的第二边缘，所述燃烧器圆顶形成具有所述环形内衬和所述环形外衬套的燃烧室。 燃烧室容纳通过环形内环和外环的外衬的流体流。 燃烧室在空气流的方向上会聚，以减小燃烧室的直径。 燃烧器穹顶构造成将燃烧器穹顶处的空气流分叉成指向环形内衬的第一流和指向环形外衬套的第二流。
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公开(公告)号：US11674686B2
公开(公告)日：2023-06-13
申请号：US17317589
申请日：2021-05-11
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Nagaraja Rudrapatna , Rodolphe Dudebout
CPC classification number: F23R3/002 , F02C7/18 , F23R2900/03041 , F23R2900/03042
Abstract: A coating occlusion resistant effusion cooling hole to form a film of a cooling fluid on a surface of a wall. The cooling hole extends along a longitudinal axis. The cooling hole includes an inlet section defined so as to be spaced apart from the surface. The inlet section is to receive the cooling fluid. The cooling hole includes a metering section fluidly coupled downstream of the inlet section. The cooling hole includes an outlet section fluidly coupled downstream of the metering section. The outlet section includes an overhang portion, a recessed portion, a first sidewall and a second sidewall. The first sidewall and the second sidewall interconnect the overhang portion with the recessed portion along a portion of the outlet section, and the first sidewall and the second sidewall converge and diverge in a plane transverse to the longitudinal axis.
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20.发明公开公开(公告)号：US20230175696A1
公开(公告)日：2023-06-08
申请号：US17457441
申请日：2021-12-03
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Duane Peterson , Girish Kanakagiri , Jaydeep Basani , Nagaraja Rudrapatna , Paul Yankowich , Richard R. Bohman , Rodolphe Dudebout , Venkatesha Prasad
CPC classification number: F23R3/283 , F02C7/22 , F02C9/26 , F23D11/383 , F23R3/54
Abstract: An injector module includes an injector stem that extends along an injector longitudinal axis between an inlet end and an outlet end of the injector module. The injector module also includes a first fuel line of a first fuel circuit at least partly extending through the injector stem. The first fuel line has a first outlet disposed at the outlet end of the injector stem. The injector module further includes a second fuel line of a second fuel circuit at least partly extending through the injector stem. The second fuel line has a second outlet disposed at the outlet end of the injector stem. The first outlet and the second outlet are spaced apart and have different orientations relative to the injector longitudinal axis. The first fuel line is thermally coupled to the second fuel line.
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