专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US12071856B2 Assembly for a turbomachine turbine 有权
公开(公告)号：US12071856B2
公开(公告)日：2024-08-27
申请号：US17634159
申请日：2020-08-04
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Simon Nicolas Morliere , Stéphane Pierre Guillaume Blanchard , Nicolas Jean-Marc Marcel Beauquin , Alain Dominique Gendraud , Olivier Renon
IPC分类号： F01D25/14 , F01D25/12
CPC分类号： F01D25/14 , F01D25/12 , F05D2220/30 , F05D2240/14 , F05D2260/213
摘要： The invention relates to an assembly (25) for a turbomachine turbine comprising a casing (18) including an annular wall (26) extending about an axis, and means of cooling the casing (18), the said means of cooling comprising a collector housing (22) and at least one tube (23) extending circumferentially around the annular wall (26) of the casing (18) and connected to the housing (22), with the tube (23) comprising cooling-air ejection orifices.

2. 发明授权

US12044149B2 Cooling system for power cables in a gas turbine engine 有权
公开(公告)号：US12044149B2
公开(公告)日：2024-07-23
申请号：US18333443
申请日：2023-06-12
申请人： RAYTHEON TECHNOLOGIES CORPORATION
发明人： Marc J. Muldoon
IPC分类号： F01D9/06 , F01D25/12 , F02C7/18 , F01D15/10 , F04D25/06
CPC分类号： F01D9/065 , F01D25/12 , F02C7/18 , F01D15/10 , F04D25/06
摘要： A cooling system for a plurality of conductive cables in a gas turbine engine includes a cooling source and an electric motor disposed in a tail cone. The cooling source may comprise an electric fan or an oil pump. The cooling source may be configured for active cooling of the plurality of conductive cables. The electric fan may be in fluid communication with ambient air during operation of the gas turbine engine.

3. 发明公开

US20240240571A1 AIRFOILS FOR TURBOFAN ENGINES 审中-公开
公开(公告)号：US20240240571A1
公开(公告)日：2024-07-18
申请号：US18155118
申请日：2023-01-17
申请人： General Electric Company
发明人： Trevor Howard Wood , Kishore Ramakrishnan , William Dwight Gerstler , Changjie Sun , Lana Maria Osusky
IPC分类号： F01D25/12 , F01D9/04 , F01D25/04
CPC分类号： F01D25/12 , F01D9/041 , F01D25/04 , F05D2220/32 , F05D2240/12 , F05D2260/202 , F05D2260/96
摘要： Airfoil include a body extending along a spanwise direction between a root end and a tip end, the body comprising a plurality of acoustic cavities each having an inlet on the airfoil; and at least one cooling channel having an inlet section an outlet section and a middle section within the airfoil extending between the inlet section and the outlet section; and at least one porous face sheet positioned on at least one inlet of the plurality of acoustic cavities.

4. 发明授权

US12031484B2 Gas turbine engine cooling system control 有权
公开(公告)号：US12031484B2
公开(公告)日：2024-07-09
申请号：US17160742
申请日：2021-01-28
申请人： General Electric Company
发明人： Michael Robert Millhaem , Christopher R. Bosco , Gerardo Perez , Hejie Li , Francisco Ernesto de la Pena , Alejandro Federico Medrano Perez , Andrew Campbell
IPC分类号： F02C7/18 , F01D25/12 , F01D21/12 , F02C9/18
CPC分类号： F02C7/18 , F01D25/12 , F01D21/12 , F02C9/18 , F05D2220/323 , F05D2220/50 , F05D2240/35 , F05D2260/20 , F05D2270/303 , F05D2270/3032 , F05D2270/304
摘要： A method is provided for operating a gas turbine engine. The method includes: determining data indicative of an operation of a cooling system of the gas turbine engine during a shutdown of the gas turbine engine, following the shutdown of the gas turbine engine, or both; and modifying a startup schedule of the gas turbine engine in response to the determined data indicative of the operation of the cooling system of the gas turbine engine.

5. 发明公开

US20240175373A1 GAS TURBINE ENGINE COMPONENT HAVING AN AIRFOIL WITH INTERNAL CROSS-RIBS 审中-公开
公开(公告)号：US20240175373A1
公开(公告)日：2024-05-30
申请号：US18071121
申请日：2022-11-29
申请人： Raytheon Technologies Corporation
发明人： James T. Roach , Jonas Banhos , Russell Kim
IPC分类号： F01D25/12 , F01D5/18 , F01D9/02
CPC分类号： F01D25/12 , F01D5/18 , F01D9/02 , F05D2220/323 , F05D2240/126 , F05D2240/30 , F05D2260/20
摘要： A gas turbine engine component includes an airfoil body extending between a leading edge and a trailing edge and having a suction wall and a pressure wall. An outer surface of the airfoil body is formed by an outer coat defining around the pressure and suction sides, a leading edge and a trailing edge. An internal cross-rib is formed within a cavity in the airfoil body. The internal cross-rib extends to be secured to the outer coat adjacent the leading edge and the trailing edge, and extending across the internal cavity to form a junction such that the cross-rib is x-shaped. The outer coat and the cross-rib are formed of ceramic matrix composites. A gas turbine engine is also disclosed.

6. 发明授权

US11994037B2 Compact turbine-compressor assembly 有权
公开(公告)号：US11994037B2
公开(公告)日：2024-05-28
申请号：US17800843
申请日：2021-02-19
申请人： Nathan Geoffrey Andrews
发明人： Nathan Geoffrey Andrews
IPC分类号： F01D25/12 , F02B39/08
CPC分类号： F01D25/12 , F02B39/08 , F05D2220/40 , F05D2260/213
摘要： There is provided a compact turbine-compressor assembly 25. The turbine-compressor assembly 25 includes a turbine wheel 39 with one or more turbine blades 41 and a compressor wheel 47 that includes one or more compressor blades 49. The compressor wheel 47 is concentric with the turbine wheel 39. Furthermore, the compressor wheel 47 and the turbine wheel 39 are not located at opposite ends of a common axle with a medial portion of the axle distancing them apart, as is the case with prior art turbine-compressor assemblies that are known. In contrast, the turbine wheel 39 and the compressor wheel 47 are located adjacent to each other and in one embodiment they axially overlap each other so that one nests within the other to thereby provide a compact arrangement. The turbine-compressor assembly 25 includes a first fluid path 67 which is configured to convey fluid, which will typically be air, through the turbine blades 41. The turbine-compressor assembly 25 also includes a second fluid path 77 which is configured to convey fluid, which will typically be air, through the compressor blades. The turbine-compressor assembly 25 is arranged so that the first fluid path 67 is distinct from the second fluid path 77 and vice-versa.

7. 发明授权

US11976562B2 System for controlling blade clearances within a gas turbine engine 有权
公开(公告)号：US11976562B2
公开(公告)日：2024-05-07
申请号：US18297835
申请日：2023-04-10
申请人： General Electric Company
发明人： Steven Douglas Johnson , Julius John Montgomery , Brandon Wayne Miller , Robert Proctor , Bradley W. Fintel , Jeffrey Douglas Rambo
IPC分类号： F01D11/24 , F01D5/03 , F01D11/18 , F02C6/08 , F02C7/18 , F01D25/12 , F01D25/14
CPC分类号： F01D11/24 , F01D5/03 , F01D11/18 , F02C6/08 , F02C7/185 , F01D25/12 , F01D25/14 , F05D2220/323 , F05D2240/11 , F05D2240/55 , F05D2260/20 , F05D2260/30
摘要： A system for controlling blade clearances within a gas turbine engine includes a rotor disk and a rotor blade coupled to the rotor disk. Additionally, the system includes an outer turbine component positioned outward of the rotor blade such that a clearance is defined between the rotor blade and the outer turbine component. Furthermore, the system includes a heat exchanger configured to receive a flow of cooling air bled from the gas turbine engine and transfer heat from the received flow of the cooling air to a flow of coolant to generate cooled cooling air. Moreover, the system includes a valve configured to control the flow of the coolant to the heat exchanger. In this respect, the cooled cooling air is supplied to at least one of the rotor disk or the rotor blade to adjust the clearance between the rotor blade and the outer turbine component.

8. 发明公开

US20240125248A1 GAS TURBINE ENGINE VANE AND SPAR COMBINATION WITH VARIABLE AIR FLOW PATH 审中-公开
公开(公告)号：US20240125248A1
公开(公告)日：2024-04-18
申请号：US18545092
申请日：2023-12-19
申请人： RTX Corporation
发明人： Jonas Banhos , James T. Roach
IPC分类号： F01D25/12 , F01D5/18 , F01D9/04
CPC分类号： F01D25/12 , F01D5/186 , F01D5/187 , F01D5/188 , F01D5/189 , F01D9/041 , F05D2220/32 , F05D2240/12 , F05D2260/20
摘要： A gas turbine engine stator vane combination includes a stator vane body having an airfoil with a leading edge, a trailing edge, a suction side and a pressure side, and having at least one internal cooling channel. The stator vane body is formed of ceramic matrix composite materials. A spar is received within the at least one cooling air channel and formed of a metal. The spar has an outer peripheral surface spaced from an inner peripheral surface of the cooling air channel to define a cooling air path, with the cooling air path having a varying cross-sectional area through the cooling air channel. A gas turbine engine is also disclosed.

9. 发明公开

US20240125243A1 COOLING FEATURES FOR A COMPONENT OF A GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20240125243A1
公开(公告)日：2024-04-18
申请号：US17965311
申请日：2022-10-13
申请人： Raytheon Technologies Corporation
发明人： Billie R. Maldonado , Jeremy T. Drake , Terence Tyler , Dmitriy A. Romanov
IPC分类号： F01D11/24 , F01D25/12
CPC分类号： F01D11/24 , F01D25/12 , F05D2220/32 , F05D2240/55 , F05D2260/202
摘要： A component for a gas turbine engine, including: at least one internal channel extending through a first portion of the component, the at least one internal channel having at least one inlet opening and at least one outlet opening each being in fluid communication with the at least one internal channel; a plurality of cooling features extending from a surface of the at least one internal channel; and at least one internal channel extending through a second portion of the component, the at least one internal channel extending through the second portion of the component is in fluid communication with the at least one internal channel extending through the first portion of the component, the second portion being located on top of the first portion, the at least one internal channel extending through the second portion of the component having a plurality of openings extending from the least one internal channel extending through the second portion of the component through the plurality of cooling features to an outer surface of the component.

10. 发明公开

US20240093642A1 GAS TURBINE ENGINES WITH HEAT RECOVERY SYSTEMS 审中-公开
公开(公告)号：US20240093642A1
公开(公告)日：2024-03-21
申请号：US18524874
申请日：2023-11-30
申请人： General Electric Company , General Electric Deutschland Holding GmbH
发明人： Paul Hadley Vitt , Michael Simonetti , Ashish Sharma
IPC分类号： F02C7/141 , F01D25/12 , F02C7/16
CPC分类号： F02C7/141 , F01D25/12 , F02C7/16 , F05D2220/32 , F05D2230/60 , F05D2260/205 , F05D2260/232
摘要： A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An outlet guide vane assembly includes multiple outlet guide vanes located in an exhaust airflow path downstream of the turbine section. The multiple outlet guide vanes being spaced-apart circumferentially from each other over an angular range of about 360 degrees, and each multiple outlet guide vane defining a radial extent. At least one of the multiple outlet guide vanes includes a cold fluid passageway and another of the multiple guide vanes includes a heated fluid passageway.

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式