公开(公告)号：US12129815B2

公开(公告)日：2024-10-29

申请号：US17816556

申请日：2022-08-01

申请人： IHI Corporation

发明人： Yasuhiro Ishikawa ,  Shinji Ishihara ,  Hatsuo Mori

IPC分类号： F02K9/52 ,  F02K9/97

CPC分类号： F02K9/972 ,  F02K9/52 ,  F05D2240/35 ,  F05D2260/2214 ,  F05D2260/232 ,  F05D2260/96

摘要： The combustor for a rocket engine includes a combustion room configured to cause a combustion reaction between a fuel and an oxidant, an injector configured to inject the fuel and the oxidant into the combustion room, and a nozzle skirt configured to inject combustion gas generated by the combustion reaction to an outside, and an inertance increasing portion configured to increase an equivalent inertance in a vibration equivalent circuit of the combustor for the rocket engine.

公开(公告)号：US12123319B2

公开(公告)日：2024-10-22

申请号：US17137536

申请日：2020-12-30

申请人： General Electric Company

发明人： Brian Stephen Gray ,  Michael Anthony Wondrasek ,  Jan Emeric Agudo

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F05D2240/81 ,  F05D2260/2214 ,  F05D2260/232 ,  F05D2260/606

摘要： A turbomachine component includes a platform, a shank, and an airfoil. The platform includes a pressure side slash face and a suction side slash face. The shank extends radially inward from the platform. The airfoil extends radially outward from the platform. The airfoil includes a leading edge and a trailing edge. A cooling circuit is defined within the shank and the airfoil. The cooling circuit further includes a plurality of exit channels disposed along the trailing edge of the airfoil. The cooling circuit further includes at least one bypass conduit that extends from an inlet disposed in the cooling circuit to an outlet positioned on the pressure side slash face. The at least one bypass conduit being positioned radially inward of the plurality of exit channels.

公开(公告)号：US20240060449A1

公开(公告)日：2024-02-22

申请号：US18498410

申请日：2023-10-31

申请人： General Electric Company

发明人： Eyitayo James Owoeye

IPC分类号： F02C7/14 ,  F02C7/32

CPC分类号： F02C7/14 ,  F02C7/32 ,  F05D2200/13 ,  F05D2200/14 ,  F05D2260/213 ,  F05D2260/2214

摘要： A turbofan engine is provided. The turbofan engine includes a low pressure spool; a fan mechanically coupled with the low pressure spool; a high pressure spool; an accessory gearbox mechanically coupled with the high pressure spool; a hydraulic pump mechanically coupled with the accessory gearbox; and one or more heat exchangers tied to the accessory gearbox, the one or more heat exchangers having a heat exchanger capacity defined by a product raised to a half power, the product being determined by multiplying an average heat exchanger effectiveness of the one or more heat exchangers by a heat conductance factor that relates an accessory gearbox heat load, a hydraulic pump power of the hydraulic pump, a fan diameter of the fan, an engine length of the turbofan engine, and an overall pressure ratio of the turbofan engine.

公开(公告)号：US11713715B2

公开(公告)日：2023-08-01

申请号：US17363155

申请日：2021-06-30

申请人： Unison Industries, LLC

发明人： Gurudatta Srinivasa Murthy Sirigere ,  Gordon Tajiri ,  Dattu Guru Venkata Jonnalagadda ,  Rajapriyan Rajendran ,  Udaya Bhaskar Pamidimarri

IPC分类号： F02C7/10 ,  B23P15/26

CPC分类号： F02C7/10 ,  B23P15/26 ,  F05D2220/62 ,  F05D2240/24 ,  F05D2260/2214

摘要： An electroformed heat exchanger suitable for use between rotating blades and seals in a stationary casing of a turbine engine. The heat exchanger comprising a non-electroformed carrier plate having a radial outer surface and a radial outer surface, an electroformed duct provided along the radial outer surface, an electroformed rail provided on the radial inner surface, and an electroformed stiffener formed by a portion of the electroformed duct and the electroformed rail.

公开(公告)号：US20180328224A1

公开(公告)日：2018-11-15

申请号：US15590512

申请日：2017-05-09

申请人： GENERAL ELECTRIC COMPANY

发明人： Sandip DUTTA ,  Joseph Anthony WEBER ,  Benjamin Paul LACY

IPC分类号： F01D25/12 ,  F01D9/04

CPC分类号： F01D5/189 ,  F05D2250/21 ,  F05D2260/201 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141

摘要： An airfoil including a leading edge, a trailing edge, a pressure side, a suction side, and an internal impingement cavity. An impingement insert is located within the impingement cavity. The impingement insert includes at least one impingement cooling hole spaced along a first face of the impingement insert and at least one impingement fin, having a base and a tip opposite the base, spaced along the first face of the impingement insert. The at least one impingement fin is spaced apart from the at least one impingement cooling hole.

公开(公告)号：US09995147B2

公开(公告)日：2018-06-12

申请号：US14619343

申请日：2015-02-11

申请人： United Technologies Corporation

发明人： Dominic J. Mongillo, Jr. ,  Jeffrey R. Levine ,  Kyle C. Lana ,  Sasha M. Moore

IPC分类号： F01D5/18 ,  F01D5/20

CPC分类号： F01D5/186 ,  F01D5/187 ,  F01D5/20 ,  F05D2240/307 ,  F05D2260/2214 ,  F05D2260/22141 ,  Y02T50/673 ,  Y02T50/676

摘要： A turbine blade according to an example of the present disclosure includes, among other things, a platform, an airfoil tip, and an airfoil section between the platform and the airfoil tip. The airfoil section has a cavity spaced radially from the airfoil tip and a plurality of cooling passages radially between the cavity and the airfoil tip. Each of the plurality of cooling passages defines an exit port adjacent the airfoil tip. An internal feature within each of the plurality of cooling passages is configured to meter flow to the exit port.

公开(公告)号：US20180119570A1

公开(公告)日：2018-05-03

申请号：US15342185

申请日：2016-11-03

申请人： General Electric Company

发明人： Benjamin Paul Lacy ,  Christopher Donald Porter ,  David Edward Schick ,  Lyndsay Marie Kibler

IPC分类号： F01D25/12 ,  F02C3/04 ,  F01D11/08 ,  F01D5/18

CPC分类号： F01D25/12 ,  F01D5/187 ,  F01D11/08 ,  F02C3/04 ,  F05D2230/22 ,  F05D2230/50 ,  F05D2240/11 ,  F05D2240/128 ,  F05D2240/30 ,  F05D2240/81 ,  F05D2250/71 ,  F05D2260/204 ,  F05D2260/2214

摘要： A cooled structure of a gas turbine engine has a main body with a leading edge, a trailing edge, a first side portion, a second side portion, and a cavity. A first set of cooling air micro-channels extends from the cavity and is arranged along the first side portion. A second set of cooling air micro-channels extends from the cavity and is arranged along the second side portion. The first and second set of cooling air micro-channels have turning portions positioned adjacent each other and interwoven exhaust ends originating from each opposing side micro-channel. Each interwoven exhaust end extends around the opposing turning portion and is configured to exhaust cooling air from a plurality of exhaust ports positioned generally radially outward from the turning portions.

公开(公告)号：US09945252B2

公开(公告)日：2018-04-17

申请号：US13541935

申请日：2012-07-05

申请人： Nathan Snape ,  Gabriel L. Suciu ,  Simon Pickford

发明人： Nathan Snape ,  Gabriel L. Suciu ,  Simon Pickford

IPC分类号： F01D25/18 ,  F01D25/12 ,  F02C7/06 ,  F02C7/14 ,  F02C7/32 ,  B64D33/00 ,  B64D29/08 ,  F01M5/00 ,  F16N19/00

CPC分类号： F01D25/18 ,  B64D29/08 ,  B64D33/00 ,  F01D25/12 ,  F01M5/002 ,  F02C7/06 ,  F02C7/14 ,  F02C7/32 ,  F05D2260/2214 ,  F16N19/00 ,  Y02T50/675

摘要： A gas turbine engine includes a fan case radially outwardly of a core compartment. A compressor section is located within an engine core compartment and includes a front mount flange and an aft mount flange. An oil tank is mounted to at least one of the fan case or the front and aft mount flanges. The oil tank has a cooling structure integrated into an outer surface such that the oil tank is subjected to cooling air flow from a plurality of air sources.

公开(公告)号：US20170268358A1

公开(公告)日：2017-09-21

申请号：US15505170

申请日：2014-09-04

申请人： Siemens Aktiengesellschaft

发明人： Ching-Pang Lee ,  Jae Y. Um ,  Gerald L. Hillier ,  Wayne J. McDonald ,  Mohamed Abdullah ,  Eric Schroeder ,  Ralph W. Matthews ,  Zhengxiang Pu

IPC分类号： F01D9/06 ,  F01D5/18

CPC分类号： F01D9/065 ,  B22C9/10 ,  F01D5/186 ,  F01D5/187 ,  F01D5/188 ,  F01D5/189 ,  F05D2220/32 ,  F05D2240/122 ,  F05D2240/127 ,  F05D2250/183 ,  F05D2260/20 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/2214

摘要： An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities (16) having an insert (18) contained therein that forms nearwall cooling channels (20) having enhanced flow patterns is disclosed. The flow of cooling fluids in the nearwall cooling channels (20) may be controlled via a plurality of cooling fluid flow controllers (22) extending from the outer wall (24) forming the generally hollow elongated airfoil (26). The cooling fluid flow controllers (22) may be collected into spanwise extending rows (28), and the internal cooling system (14) may include one or more bypass flow reducers (30) extending from the insert (18) toward the outer wall (24) to direct the cooling fluids through the channels (20) created by the cooling fluid flow controllers (22), thereby increasing the effectiveness of the internal cooling system (14).

公开(公告)号：US20170248021A1

公开(公告)日：2017-08-31

申请号：US15053682

申请日：2016-02-25

申请人： United Technologies Corporation

发明人： James Tilsley Auxier ,  Bret M. Teller

IPC分类号： F01D5/18 ,  F01D11/08 ,  F01D25/12 ,  F01D9/04

CPC分类号： F01D5/187 ,  B22C9/101 ,  F01D9/041 ,  F01D11/08 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/20 ,  F05D2230/211 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2240/55 ,  F05D2260/2214 ,  F05D2260/22141 ,  Y02T50/676

摘要： An airfoil of a gas turbine engine includes an airfoil body having a leading edge and a trailing edge extending in a radial direction, a trailing edge cavity formed within the airfoil and proximate to the trailing edge of the airfoil, the trailing edge cavity extending from the trailing edge in a forward direction toward the leading edge, at least one set of blocking pedestals located within the trailing edge cavity, a set of circular pedestals located aftward from the at least one blocking set of pedestals, and a set of spear pedestals located aftward from the set of circular pedestals and closest to the trailing edge of the airfoil body.