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公开(公告)号：US12116898B2
公开(公告)日：2024-10-15
申请号：US18160117
申请日：2023-01-26
Applicant: Pratt & Whitney Canada Corp.
Inventor： Venkata Sai Prahasith Mahankali
CPC classification number: F01D11/24 , F01D11/18 , F05D2220/323 , F05D2240/11 , F05D2240/55 , F05D2260/201
Abstract: Turboprop engines include a housing, a propeller arranged at a forward end of the housing, and a rotor assembly arranged within the housing, the rotor assembly comprising at least one rotor having a plurality of rotor blades. A blade shroud is arranged radially outward from the rotor assembly and positioned relative to the rotor blades such that a tip clearance is defined between tips of the rotor blades and an inner diameter surface of the blade shroud. A shroud cooling duct is defined radially outward from the blade shroud and radially inward from the housing and an air scoop is configured to direct a shroud cooling flow into the shroud cooling duct to pick up heat from the blade shroud and provide cooling thereto.
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公开(公告)号：US20240337190A1
公开(公告)日：2024-10-10
申请号：US18295388
申请日：2023-04-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Susan Emily Schulz , Zachary Daniel Webster , Daniel Endecott Osgood , Jorge Rodrigo Quintero Badillo , Catherine Marie Rucki , Ricardo Caraballo , David Lawrence Holzschuh
CPC classification number: F01D5/188 , F01D5/147 , F05D2240/81 , F05D2260/201
Abstract: A turbine blade assembly for a turbine engine that generates a hot fluid flow and provides a cooling fluid flow. The turbine blade assembly having a platform with an upper wall radially spaced from a lower wall, and a platform wall connecting the upper wall to the lower wall to bound an interior of the platform. An airfoil extending from the upper wall and having an airfoil wall at least partially bounding an interior of the airfoil and defining a heated surface in contact with the hot fluid flow. At least one cooling supply conduit extending into the interior of the airfoil and multiple cores provided in the interior of the platform.
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公开(公告)号：US20240254890A1
公开(公告)日：2024-08-01
申请号：US18160117
申请日：2023-01-26
Applicant: Pratt & Whitney Canada Corp.
Inventor： Venkata Sai Prahasith Mahankali
CPC classification number: F01D11/24 , F01D11/18 , F05D2220/323 , F05D2240/11 , F05D2240/55 , F05D2260/201
Abstract: Turboprop engines include a housing, a propeller arranged at a forward end of the housing, and a rotor assembly arranged within the housing, the rotor assembly comprising at least one rotor having a plurality of rotor blades. A blade shroud is arranged radially outward from the rotor assembly and positioned relative to the rotor blades such that a tip clearance is defined between tips of the rotor blades and an inner diameter surface of the blade shroud. A shroud cooling duct is defined radially outward from the blade shroud and radially inward from the housing and an air scoop is configured to direct a shroud cooling flow into the shroud cooling duct to pick up heat from the blade shroud and provide cooling thereto.
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公开(公告)号：US12044411B2
公开(公告)日：2024-07-23
申请号：US17350529
申请日：2021-06-17
Applicant: General Electric Company
Inventor： Lucas John Stoia , Terese Marinita Martinez , Ronnie Ray Pentecost , Elizabeth Leigh Exley
CPC classification number: F23R3/346 , F02C7/222 , F23R3/46 , F05D2240/35 , F05D2260/201 , F23R2900/03044
Abstract: A combustor includes an end cover and at least one fuel nozzle extending from the end cover and at least partially surrounded by a combustion liner. The combustor further includes an outer sleeve spaced apart from and surrounding the combustion liner such that an annulus is defined therebetween. The combustor further includes a fuel injection assembly. The fuel injection assembly includes a fuel injector that extends through the outer sleeve, the annulus, and the combustion liner to the secondary combustion zone. A fuel supply conduit positioned outside of the outer sleeve. The fuel supply conduit extending to the fuel injector. A shielding assembly coupled to the outer sleeve and at least partially surrounding the fuel supply conduit. The at least one fuel sweep opening is defined in the outer sleeve and disposed within the shielding assembly.
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公开(公告)号：US20240229663A9
公开(公告)日：2024-07-11
申请号：US17971270
申请日：2022-10-21
Applicant: Raytheon Technologies Corporation
Inventor： Parag H. Mathuria , Lajos H. Horvath , Joshua R. Seyler , Malvin B. Cedeno-Jimenez , James Masloski , Jason P. Meert
CPC classification number: F01D25/12 , F01D9/065 , F01D11/08 , F05D2240/11 , F05D2260/201
Abstract: An apparatus is provided for a gas turbine engine. This engine apparatus includes a shroud, and the shroud includes a wall and a bleed passage. The wall includes an interior surface and an exterior surface. The wall extends circumferentially about an axis. The wall extends depthwise between the interior surface and the exterior surface. The interior surface forms a peripheral boundary of a flowpath that extends along the shroud. The bleed passage includes an inlet orifice and an outlet orifice. The bleed passage extends through the shroud between the inlet orifice and the outlet orifice. The inlet orifice is disposed in the interior surface and fluidly couples the flowpath to the bleed passage. At least a downstream section of the bleed passage circumferentially tapers as the downstream section of the bleed passage extends within the wall towards the outlet orifice.
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Patent Agency Ranking
公开(公告)号：US12025019B2
公开(公告)日：2024-07-02
申请号：US17609375
申请日：2020-05-20
Applicant: Siemens Energy Global GmbH & Co. KG
Inventor： Ksenia Denisova , Alexander Fakeev , Ilya Fedorov , Omid Lorestani
CPC classification number: F01D25/246 , F01D11/24 , F01D25/14 , F05D2240/15 , F05D2260/201 , F05D2260/30
Abstract: A heatshield for a gas turbine engine, includes a main body having a leading edge, a trailing edge, lateral edges, a first surface and a second surface. The first surface being exposed to a hot working gas in use passing through the gas turbine engine. The heatshield having a leading hook and a trailing hook each extending between the lateral edges, the leading hook and the trailing hook extending from the second surface. A stiffening structure extends from the leading hook to the trailing hook and free from direct contact or attachment to the second surface.
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公开(公告)号：US12018588B2
公开(公告)日：2024-06-25
申请号：US17796383
申请日：2020-11-20
Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
Inventor： Saki Matsuo , Yusuke Izumi , Satoshi Hada , Takuya Okamoto
CPC classification number: F01D5/187 , F01D9/041 , F01D25/24 , F05D2240/126 , F05D2240/81 , F05D2260/201
Abstract: This stator vane is at least provided with a blade body disposed in a combustion gas flow channel through which a combustion gas flows, a shroud that defines a part of the combustion gas flow channel, and an impingement plate attached to the shroud. A partition rib extends from a blade body end to an inner wall surface of a peripheral wall, and a shelf is provided at a rib-less part of the inner wall surface of the peripheral wall excluding at least a part in which the partition rib extends to the inner wall surface of the peripheral wall.
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公开(公告)号：US20240159158A1
公开(公告)日：2024-05-16
申请号：US17988518
申请日：2022-11-16
Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
Inventor： Satoshi Mizukami , David Allen Flodman , Satoshi Hada , Yasumasa Kunisada , Saki Matsuo , Ryo Tanaka , Takuro Kameda , Yusuke Akada
IPC: F01D9/06
CPC classification number: F01D9/065 , F05D2240/11 , F05D2260/201
Abstract: A shroud of a vane of a turbine is provided. The shroud includes a shroud main body comprising a first wall having a gas-passage face facing a hot gas passage of the turbine and a cooling face facing opposite to the hot gas passage, a shroud edge disposed on a circumference of the shroud main body to surround the shroud main body, the shroud edge comprising a shroud edge passage therein, and an impingement box disposed to face the cooling face of the first wall so as to be spaced apart from the cooling face of the first wall. The impingement box comprises a cooling air inlet to introduce a cooling air from the shroud edge passage into an inside of the impingement box, and an impingement air hole configured to jet the introduced cooling air to the cooling face of the first wall to cool the cooling face of the first wall.
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公开(公告)号：US11952910B2
公开(公告)日：2024-04-09
申请号：US18200220
申请日：2023-05-22
Applicant: Hamilton Sundstrand Corporation
Inventor： Zhongtao Dai , Ram Ranjan , Robert H. Dold
CPC classification number: F01D5/046 , F01D5/048 , B33Y80/00 , F05D2240/24 , F05D2260/201
Abstract: A turbine rotor includes a base and a plurality of blades. A central nose is radially inward of the blades and defines an axis of rotation. A plurality of cooling manifolds is disposed within the turbine rotor and includes impingement cooling jets extending through a rear surface of the turbine rotor. An internal cooling manifold extends radially inward of the impingement cooling jets and extends between the base and the rear surface of the turbine rotor. A central nose cooling manifold extends into the central nose and is fluidically connected to the internal cooling manifold. A base cooling manifold is fluidically connected to the central nose manifold and extends radially outward from the central nose cooling manifold. A blade cooling manifold is fluidically connected to the base cooling manifold and extends within the blade. Trailing edge jets extend from the blade cooling manifold and through the trailing edge of blades.
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公开(公告)号：US11905849B2
公开(公告)日：2024-02-20
申请号：US17967252
申请日：2022-10-17
Applicant: RTX Corporation
Inventor： Brandon W. Spangler , David R. Pack
CPC classification number: F01D5/187 , F01D5/147 , F05D2240/303 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2250/11 , F05D2260/201 , F05D2260/22141
Abstract: Airfoils and core assemblies for such airfoils are described. The airfoils include a leading edge cavity defined, in part, by a leading edge interior rib and a trailing edge cavity defined, in part, by a trailing edge interior rib. A plurality of pressure side cavities are defined by pressure side skin cavity walls with at least one pressure side skin cavity wall not extending to the suction side wall. A plurality of suction side cavities are defined by suction side skin cavity walls with at least one suction side skin cavity wall not extending to the pressure side wall. A main body cavity extends between the leading edge interior rib and the trailing edge interior rib and the plurality of side cavities are arranged in a staggered pattern to define the bounds of the main body cavity.
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