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公开(公告)号：US20240392968A1
公开(公告)日：2024-11-28
申请号：US18652193
申请日：2024-05-01
Applicant: ROLLS-ROYCE PLC
Inventor： Stephen C. HARDING
Abstract: An integral guide vane combustor assembly for a gas turbine engine comprises an annular array of radially extending guide vane combustors. The gas turbine engine comprises, in axial flow sequence, a compressor assembly, the integral guide vane combustor assembly, a turbine assembly, and an exhaust assembly. Each of the guide vane combustors comprises, in axial flow sequence, a guide vane portion, and a combustor body portion. The guide vane portion is formed integrally with the combustor body portion, and the guide vane portion is configured to direct a gas flow exiting the compressor assembly into the combustor body portion.
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公开(公告)号：US20240353599A1
公开(公告)日：2024-10-24
申请号：US18631432
申请日：2024-04-10
Applicant: Rolls-Royce plc
Inventor： Stephen C. HARDING , James G. BREWSTER
IPC: G02B5/08
CPC classification number: G02B5/0808
Abstract: A component for a hot section of an engine comprises a substrate and an infrared-reflective layer configured to reflect infrared radiation away from the substrate and in some cases the infrared-reflective layer has: a spectral reflectance R_λ of no less than about 0.5 when measured by spectrophotometry, according to ISO 15368:2021, using incident electromagnetic radiation having a wavelength λ no less than about 500 nm and no greater than about 1 mm; and a spectral emissivity ε_λ of less than about 0.4, for example no greater than about 0.3, when measured using incident electromagnetic radiation having a wavelength λ no less than about 500 nm and no greater than about 1 mm.
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公开(公告)号：US20200277868A1
公开(公告)日：2020-09-03
申请号：US16786037
申请日：2020-02-10
Applicant: ROLLS-ROYCE plc
Inventor： Paul A. HUCKER , Stephen C. HARDING , Quentin BORLON
Abstract: A combustion liner for a gas turbine engine. The combustion liner defines a bypass direction which extends between an upstream portion and a downstream portion of the combustion liner in use, the combustion liner. The combustion liner comprises a liner wall for defining at least a portion of a combustion chamber, the liner wall having an outer surface and an inner surface and a depth between the outer and inner surfaces of the combustion liner in use. The combustion liner comprises a chute formed through the liner wall for conveying fluid from the outer surface through the liner wall and ejecting fluid from an exhaust hole of the chute on the inner surface, the exhaust hole having a length L along the bypass direction. The combustion liner also comprises a fluid-guiding surface at an upstream side of the chute which defines an arc terminating at the exhaust hole, the fluid guiding surface configured to guide fluid from a direction generally parallel to the outer surface into the chute to be ejected from the chute exhaust hole at a direction generally perpendicular to the inner surface.
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公开(公告)号：US20190293294A1
公开(公告)日：2019-09-26
申请号：US16355111
申请日：2019-03-15
Applicant: ROLLS-ROYCE plc
Inventor： Paul A. HUCKER , Stephen C. HARDING , Iain MORGAN
Abstract: An igniter seal arrangement for a combustion chamber. The combustion chamber has a wall having first surface and second surfaces. A boss projects from the first surface, and has a platform on its remote end. The platform has an inner surface spaced from the first surface of the wall to define a chamber between the first surface of the wall and the inner surface of the platform. The platform has an outer surface facing away from the first surface of the wall and an aperture extends through the wall from the outer surface of the platform of the boss to the second surface. First and second L-shape rails extend from the platform and a sealing member has a first edge and a second edge locatable between the outer surface of the platform and the first and second L-shape rails and the sealing member has an aperture to receive an igniter.
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公开(公告)号：US20160123156A1
公开(公告)日：2016-05-05
申请号：US14872511
申请日：2015-10-01
Applicant: ROLLS-ROYCE PLC
Inventor： Paul A. HUCKER , Stephen C. HARDING , Alan P. GEARY
CPC classification number: F01D5/186 , F01D5/188 , F01D9/065 , F05B2260/202 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R3/005 , F23R2900/00018 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043
Abstract: A cooled gas turbine engine component comprises a wall having first and second surfaces. The second surface has a plurality of recesses and each recess has a planar upstream end surface arranged so that it hangs over the upstream end of the recess. Each recess has a depth equal to the required depth plus the thickness of the thermal barrier coating to be deposited. The wall has a plurality of angled effusion cooling apertures extending from the first surface towards the second surface. Each effusion cooling aperture has an inlet in the first surface and an outlet in the end surface of a corresponding one of the recesses in the second surface. Each recess has smoothly curved transitions from the end surface and side surfaces to the second surface. Blocking of the effusion cooling apertures by thermal barrier coating is reduced.
Abstract translation: 冷却的燃气涡轮发动机部件包括具有第一和第二表面的壁。 第二表面具有多个凹部，并且每个凹部具有布置成使其悬挂在凹部的上游端上的平坦的上游端面。 每个凹槽的深度等于所要求的深度加上待沉积的热障涂层的厚度。 壁具有从第一表面朝向第二表面延伸的多个倾斜的积水冷却孔。 每个排出冷却孔在第一表面中具有入口，在第二表面中的相应的一个凹部的端面中具有出口。 每个凹部具有从端表面和侧表面到第二表面的平滑弯曲过渡。 通过热障涂层阻挡积液冷却孔。
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Patent Agency Ranking
公开(公告)号：US20250052425A1
公开(公告)日：2025-02-13
申请号：US18772375
申请日：2024-07-15
Applicant: ROLLS-ROYCE plc
Inventor： Stephen C. HARDING , Paul A. HUCKER , Iain MORGAN
IPC: F23R3/00
Abstract: The present disclosure relates to a combustor assembly for a gas turbine engine. The combustor assembly comprises a combustor liner, a combustor head, a cowl and a fastener. The combustor liner and the cowl define a cavity. The combustor liner has an integral lug that extends into the cavity from a wall of the combustor liner. The fastener extends into the combustor liner lug to fasten the combustor head to the combustor liner.
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公开(公告)号：US20240392970A1
公开(公告)日：2024-11-28
申请号：US18652125
申请日：2024-05-01
Applicant: ROLLS-ROYCE plc
Inventor： Stephen C. HARDING
Abstract: A combustor assembly for a gas turbine engine comprises a combustor casing. The combustor casing has a diametral height D and an axial length L. An Aspect Ratio parameter S is defined as: S = D L and the S parameter lies in the range of 0.30 to 1.00.
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公开(公告)号：US20240117967A1
公开(公告)日：2024-04-11
申请号：US18359346
申请日：2023-07-26
Applicant: ROLLS-ROYCE plc
Inventor： Stephen C. HARDING
Abstract: There is described a fuel injector for a gas turbine engine. The fuel injector comprises an air passageway having an inlet region and an outlet region in fluid communication with the inlet region at an air passageway interface, the inlet region being configured to receive a flow of air from a compressor of the gas turbine engine at an air inlet, the outlet region being configured to receive the flow of air from the inlet region via the air passageway interface and discharge the flow of air to a combustor head of the gas turbine engine. The fuel injector also comprises a fuel passageway having a fuel outlet configured to discharge a flow of fuel into the combustor head. A width of the inlet region in a direction perpendicular to a centreline of the air passageway decreases continuously from the air inlet to the air passageway interface.
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公开(公告)号：US20190195497A1
公开(公告)日：2019-06-27
申请号：US16288535
申请日：2019-02-28
Applicant: ROLLS-ROYCE plc
Inventor： Jonathan F. CARROTTE , Stephen C. HARDING , Ashley G. BARKER
CPC classification number: F23R3/20 , F02C7/222 , F23D11/107 , F23D2206/10 , F23D2900/11401 , F23R3/343 , F23R2900/00014
Abstract: A fuel injection system for a gas turbine engine comprises; a pilot fuel injector section and a main airblast fuel injector section, the main airblast fuel injector section having an aft end facing a combustion chamber. A surface of the injection system exposed to air flow through an injection system is non-axisymmetric or non-planar in a reference circumferential plane and/or is configured to generate controlled and varying acoustic impedance at or adjacent the aft end where, in use, the air flow collides with an oncoming acoustic wave.
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公开(公告)号：US20180031238A1
公开(公告)日：2018-02-01
申请号：US15658863
申请日：2017-07-25
Applicant: ROLLS-ROYCE plc
Inventor： Stephen C. HARDING
Abstract: A combustion chamber assembly comprises a combustion chamber and a plurality of nozzle guide vanes. Each nozzle guide vane comprises an inner platform, an outer platform and an aerofoil. The combustion chamber comprises an annular wall which includes at least one box like structure. An outer wall of each box has a plurality of apertures for the supply of coolant into the box and the interior of the box is divided into at least two regions. The upstream end of each box has apertures to supply coolant from a first region of its interior onto an inner surface of the inner wall to form a film of coolant. The downstream end of each box has apertures to supply coolant from a second region of its interior onto a surface of the inner or outer platform of the nozzle guide vanes to form a film of coolant.
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