公开(公告)号：US12129812B2

公开(公告)日：2024-10-29

申请号：US17603151

申请日：2020-05-20

申请人： HYLIION HOLDINGS CORP

发明人： Kevin Michael VandeVoorde ,  Joshua Tyler Mook ,  Aigbedion Akwara ,  Jason Joseph Bellardi ,  Mohammed El Hacin Sennoun ,  Mary Kathryn Thompson ,  Scott Douglas Waun ,  Michael Thomas Gansler ,  Michael Robert Notarnicola

IPC分类号： F02G1/044 ,  B33Y80/00 ,  F02G1/04 ,  F02G1/043 ,  F02G1/047 ,  F02G1/05 ,  F02G1/053 ,  F02G1/055 ,  F02G1/057 ,  F02G3/00 ,  F23R3/00 ,  F28D9/04 ,  F28D21/00 ,  F28F7/02 ,  F28F13/00 ,  F28F13/14

CPC分类号： F02G1/044 ,  B33Y80/00 ,  F02G1/04 ,  F02G1/043 ,  F02G1/047 ,  F02G1/05 ,  F02G1/053 ,  F02G1/055 ,  F02G1/057 ,  F02G3/00 ,  F23R3/005 ,  F28D9/04 ,  F28F7/02 ,  F28F13/003 ,  F28F13/14 ,  F02G1/0435 ,  F02G2243/00 ,  F02G2244/00 ,  F02G2244/08 ,  F02G2244/50 ,  F02G2244/52 ,  F02G2244/54 ,  F02G2250/00 ,  F02G2254/10 ,  F02G2254/18 ,  F02G2257/00 ,  F02G2258/10 ,  F02G2270/40 ,  F02G2270/45 ,  F02G2270/80 ,  F02G2280/10 ,  F28D2021/0026 ,  F28F2210/10 ,  F28F2250/04

摘要： A system for energy conversion, the system including a closed cycle engine containing a volume of working fluid, the engine comprising a first chamber defining an expansion chamber and a second chamber defining a compression chamber each separated by a piston attached to a connection member of a piston assembly, and wherein the engine comprises a heater body in thermal communication with the first chamber, and further wherein the engine comprises a cold side heat exchanger in thermal communication with the second chamber, and wherein a third chamber is defined within the piston, wherein the third chamber is in selective flow communication with the first chamber, the second chamber, or both.

公开(公告)号：US20240353105A1

公开(公告)日：2024-10-24

申请号：US18639359

申请日：2024-04-18

申请人： RTX Corporation

发明人： Thomas E. Clark ,  Andrew E. Breault ,  William K. Ackermann

IPC分类号： F23R3/60 ,  F23R3/00 ,  F23R3/50

CPC分类号： F23R3/60 ,  F23R3/002 ,  F23R3/50 ,  F23R2900/00017

摘要： A gas turbine engine is provided having an axial centerline, a compressor section, a turbine section, and a combustor section. The turbine section has a turbine first vane assembly that includes an annular first vane inner radial support. The combustor section has an outer casing, an annular combustor, and a unitary inner diffuser structure. The annular combustor has an inner radial flange. The unitary inner diffuser structure includes a compressor discharge, an inner diffuser case, and a tangential onboard injector (TOBI) inseparably attached to one another. The unitary inner diffuser structure further includes an outer radial flange and a TOBI connection flange. The annular FV inner radial support, the combustor inner radial flange, and the TOBI connection flange are secured to one another.

公开(公告)号：US20240310047A1

公开(公告)日：2024-09-19

申请号：US18121286

申请日：2023-03-14

申请人： RTX Corporation

发明人： Dibesh D. Joshi

IPC分类号： F23R3/00 ,  F02C7/24 ,  F02C7/30

CPC分类号： F23R3/002 ,  F02C7/24 ,  F02C7/30 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/231 ,  F05D2260/95

摘要： A combustor for a gas turbine engine, including: a heat shield panel attached to a combustor liner, the combustor liner having a plurality of primary apertures extending through the combustor liner and the heat shield panel having a plurality of apertures extending therethrough; an intermediary layer located between the combustor liner and the heat shield panel, the intermediary layer being spaced from the combustor liner and the intermediary layer being spaced from the heat shield panel, the intermediary layer including a plurality of secondary apertures extending through the intermediary layer, the plurality of apertures, the plurality of primary apertures and the plurality of secondary apertures each being in fluid communication with each other; and a plurality of pins extending upwardly and away from a surface of the intermediary layer towards a surface of the combustor liner.

公开(公告)号：US12078077B2

公开(公告)日：2024-09-03

申请号：US18236053

申请日：2023-08-21

申请人： RTX Corporation

发明人： Lawrence A. Binek ,  Sean R. Jackson

IPC分类号： F01D9/02 ,  F01D25/24 ,  F02C7/22 ,  F23R3/00

CPC分类号： F01D25/24 ,  F01D9/02 ,  F02C7/222 ,  F23R3/002 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2240/128 ,  F05D2240/14 ,  F05D2240/35

摘要： An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a stationary engine structure. The stationary engine structure includes a diffuser, a combustor, an engine case and a plenum. The combustor is disposed within the plenum. The engine case forms a peripheral boundary of the plenum. A gas path extends sequentially through the diffuser, the plenum and the combustor. A first section of the stationary engine structure is formed as a first monolithic body. The first section includes the diffuser and the combustor. A second section of the stationary structure is formed as a second monolithic body. The second section is configured as or otherwise includes the engine case.

公开(公告)号：US20240271785A1

公开(公告)日：2024-08-15

申请号：US18110230

申请日：2023-02-15

申请人： Raytheon Technologies Corporation

发明人： Dibesh D. Joshi

IPC分类号： F23R3/00

CPC分类号： F23R3/002 ,  F23R2900/03044

摘要： A combustor wall includes a panel, a boss, a wall aperture and multiple cooling apertures. The panel extends axially along and circumferentially about an axial centerline. The panel extends radially between a first panel surface and a second panel surface. The first panel surface forms a peripheral boundary of a combustion chamber. The boss projects out from the second panel surface. The boss extends circumferentially around and forms an outer peripheral boundary of the wall aperture. The wall aperture extends along a wall aperture centerline through the combustor wall to the first panel surface. The cooling apertures are arranged circumferentially about the wall aperture. Each of the cooling apertures extends along a cooling aperture centerline through the panel and/or the boss to the wall aperture. The cooling aperture centerline of a first of the cooling apertures is angularly offset from the wall aperture centerline by a first acute angle.

公开(公告)号：US12053821B2

公开(公告)日：2024-08-06

申请号：US18122207

申请日：2023-03-16

申请人： RAYTHEON TECHNOLOGIES CORPORATION

发明人： Lawrence Binek ,  Jesse R. Boyer ,  Dmytro Mykolayovych Voytovych

IPC分类号： F23R3/16 ,  B22F10/25 ,  F23R3/00 ,  F23R3/26

CPC分类号： B22F10/25 ,  F23R3/002 ,  F23R3/16 ,  F23R3/26

摘要： A core engine article includes a combustor liner defining a combustion chamber therein and a turbine nozzle. The combustor liner includes a plurality of injector ports, and the plurality of injector ports have a shape that tapers to a corner on a forward side of the injector ports. The turbine nozzle includes a plurality of airfoils. The combustor liner and turbine nozzle are integral with one another. A method of making a core engine article is also disclosed.

公开(公告)号：US20240230095A1

公开(公告)日：2024-07-11

申请号：US18401568

申请日：2023-12-31

申请人： GE Infrastructure Technology LLC

发明人： Michael John Hughes ,  Jonathan Dwight Berry ,  Homayoon Feiz ,  Sven Bethke

IPC分类号： F23R3/28 ,  F02C7/22 ,  F23R3/00

CPC分类号： F23R3/286 ,  F02C7/22 ,  F23R3/002 ,  F05D2240/35

摘要： A combustor for a gas turbine engine comprises: a head end section defining a head end plenum and containing a fuel nozzle assembly; and a liner extending downstream from the head end section to an aft frame and defining a combustion chamber therein. First injectors, disposed at a first axial location, direct a first fuel/air mixture through the liner. Second injectors, disposed at a different, second axial location, direct a second fuel/air mixture through the liner. Each of the head end section, the first injectors, and the second injectors receives a respective air supply from a compressor discharge plenum that at least partially surrounds the combustor. The respective air supplies are directed to only one of the fuel nozzle assembly, the first injectors, and the second injectors. The first injectors and the second injectors receive more than 50% of the air supply from the compressor discharge plenum.

公开(公告)号：US20240219027A1

公开(公告)日：2024-07-04

申请号：US18515033

申请日：2023-11-20

申请人： Relativity Space, Inc.

发明人： Bishop Wright, JR. ,  Erik Daniel Stengline ,  Thomas Vaughn ,  Fritz C. Gruber ,  Vladislav Mogilevskiy ,  Nazareth Ekmekjian ,  Rocco DiVerdi ,  Alyssa Ishigo ,  Benjamin Stephen Waxman ,  Jacob Shearman ,  Allan Huang ,  Samuel James Tonneslan ,  Aaron Goldfogel ,  John Charles Fuller ,  Andrew Neil Osborn ,  Chandler Aulick

IPC分类号： F23R3/00 ,  B33Y10/00 ,  B33Y70/00 ,  B33Y80/00

CPC分类号： F23R3/002 ,  B33Y10/00 ,  B33Y80/00 ,  B33Y70/00 ,  F23R2900/00018 ,  F23R2900/03043

摘要： Additively manufactured thrust chambers and thrust chambers with integral fluid manifolds, and hybrid additive manufacturing methods for their production, are provided. Hybrid additive manufacturing techniques may combine a variety of processes including, WAAM, PBF, cold spray and DED, for example, to produce objects with variant dimensional requirements, i.e., large overall size and small features. Hybrid additive manufacturing may be defined as provide various process layers within any manufactured object. These process layers in turn allow for the introduction of variable feature and size distribution throughout the manufactured object. Hybrid process layers according to aspects may also allow the use of a variety of materials or may use a single material across the various process layers.

公开(公告)号：US12024474B2

公开(公告)日：2024-07-02

申请号：US17850430

申请日：2022-06-27

申请人： RTX CORPORATION

发明人： David C. Jarmon

IPC分类号： C04B35/80 ,  B28B1/00 ,  B28B11/12 ,  C04B35/01 ,  C04B35/565 ,  C04B35/571 ,  C04B35/573 ,  C04B35/622 ,  C04B35/634 ,  C04B35/638 ,  C04B35/64 ,  C04B35/76 ,  C04B35/83 ,  C04B37/00 ,  D03D25/00 ,  F01D5/00 ,  F01D9/00 ,  F01D11/00 ,  F01D25/00 ,  F01D25/24 ,  F01D25/28 ,  F01D25/30 ,  F02C7/28 ,  F02K1/82 ,  F23R3/00 ,  F23R3/28 ,  F23R3/60

CPC分类号： C04B35/80 ,  B28B1/001 ,  B28B1/002 ,  B28B11/12 ,  C04B35/01 ,  C04B35/565 ,  C04B35/571 ,  C04B35/573 ,  C04B35/62227 ,  C04B35/634 ,  C04B35/638 ,  C04B35/64 ,  C04B35/76 ,  C04B35/83 ,  C04B37/001 ,  D03D25/005 ,  F01D5/00 ,  F01D9/00 ,  F01D11/00 ,  F01D25/00 ,  F01D25/005 ,  F01D25/243 ,  F01D25/246 ,  F01D25/28 ,  F01D25/30 ,  F02C7/28 ,  F02K1/822 ,  F23R3/002 ,  F23R3/007 ,  F23R3/283 ,  F23R3/60 ,  C04B2235/48 ,  C04B2235/5208 ,  C04B2235/5244 ,  C04B2235/5248 ,  C04B2235/5252 ,  C04B2235/5256 ,  C04B2235/612 ,  C04B2235/614 ,  C04B2235/616 ,  C04B2237/38 ,  C04B2237/385 ,  C04B2237/60 ,  C04B2237/61 ,  C04B2237/80 ,  C04B2237/84 ,  F05D2220/323 ,  F05D2230/10 ,  F05D2230/314 ,  F05D2240/91 ,  F05D2260/30 ,  F05D2260/31 ,  F05D2300/6033 ,  F23M2900/05004 ,  Y02T50/60

摘要： A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.

公开(公告)号：US11994296B2

公开(公告)日：2024-05-28

申请号：US18034119

申请日：2021-09-13

申请人： MITIS S.A. ,  UNIVERSITE LIBRE DE BRUXELLES

发明人： Michel Delanaye ,  Alessandro Parente

IPC分类号： F23R3/00 ,  F02C3/14 ,  F23R3/16 ,  F23R3/54

CPC分类号： F23R3/16 ,  F02C3/14 ,  F23R3/54 ,  F05D2250/82

摘要： A combustion device for an electricity production or energy cogeneration apparatus, the apparatus comprising a gas turbine supplied by the device, the device being suitable for a combustion regime of a “flameless” type, the device including: an outer tube; and a combustion tube forming a combustion zone for flameless combustion of a mixture of oxidizing air and fuel, the combustion tube being concentric with the outer tube, in communication with fuel-injection means, and with air-injection means arranged at a first end of the combustion tube, referred to as a front end, and which is closed by an end wall at a second end of the combustion tube, referred to as a rear end, the end wall being secured to the combustion tube and fluidtight, the fuel-injection means including at least a first orifice, referred to as a fuel-injection orifice, the air-injection means including at least a second orifice.