公开(公告)号：US20250067434A1

公开(公告)日：2025-02-27

申请号：US18804670

申请日：2024-08-14

Applicant: ROLLS-ROYCE PLC

Inventor： Marcin Damian DUTKA

IPC: F23R3/00 ,  F02C7/12

Abstract: A tile for a gas turbine engine combustor. The tile has a base that has a hot-side surface, a cold-side surface, a first circumferential extremity, a second circumferential extremity and a local radial axis. The tile also has a plurality of cooling channels that have inlets on the cold-side surface and outlets on the hot-side surface, and one or more rail structure attached to the cold-side surface of the base.

公开(公告)号：US12234988B1

公开(公告)日：2025-02-25

申请号：US18626821

申请日：2024-04-04

Applicant: RTX Corporation

Inventor： Zhongtao Dai ,  Justin M. Locke

IPC: F23R3/14 ,  F23R3/36 ,  F23R3/00 ,  F23R3/28

Abstract: A fuel nozzle for a gas turbine engine combustor includes a fuel nozzle assembly including an inflow tube disposed along and a nozzle axis, the inflow tube defining an inner air passage and a liquid swirler concentrically disposed about the inflow tube, the liquid swirler including a liquid swirler inner wall having a liquid swirler inner wall end portion angled radially outward from the nozzle axis, a liquid swirler outer wall having a liquid swirler outer wall end portion angled radially outward from the nozzle axis, and an annular liquid passage defined therebetween. The fuel nozzle assembly further includes a radial air swirler (RAS) concentrically disposed about the liquid swirler outer wall, the RAS including an RAS inner wall having an RAS inner wall end portion angled radially inward toward the nozzle axis, an RAS outer wall having an end cap at a downstream-most position, and an annular gas passage defined therebetween. The end cap includes a radiused inner surface and a contoured outer surface, and the radiused inner surface is parallel to the RAS inner wall end portion.

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.

公开(公告)号：US12222104B2

公开(公告)日：2025-02-11

申请号：US17740443

申请日：2022-05-10

Applicant: General Electric Company

Inventor： Manampathy G. Giridharan ,  Michael T. Bucaro ,  Pradeep Naik ,  Clayton S. Cooper ,  Michael A. Benjamin ,  Steven C. Vise ,  Ajoy Patra ,  Perumallu Vukanti ,  R Narasimha Chiranthan

IPC: F23R3/00 ,  F23R3/16 ,  F23R3/26

Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustor liner at least partially defining a combustion chamber. The combustor liner can include at least one aperture fluidly coupled to the combustion chamber.

公开(公告)号：US12215867B2

公开(公告)日：2025-02-04

申请号：US18401588

申请日：2023-12-31

Applicant: GE Infrastructure Technology LLC

Inventor： Jonathan Dwight Berry ,  Sven Bethke ,  Bailey Basso

IPC: F23R3/28 ,  F02C7/04 ,  F02C7/12 ,  F02C7/22 ,  F23D14/48 ,  F23R3/00 ,  F23R3/16 ,  F23R3/34

Abstract: A gas turbine engine combustor includes: a head end section containing a fuel nozzle assembly and defining a head end air plenum; and a liner extending downstream from the head end section toward an aft frame and defining a combustion chamber therein. First injectors are disposed at a first axial location spaced apart from the head end section to direct a first fuel/air mixture through the liner. A dynamics mitigation system includes cold-side resonators disposed wholly within the head end air plenum, each resonator of the plurality of cold-side resonators having a resonator body with a closed end and an open neck extending from the resonator body opposite the closed end. Each resonator body defines a respective volume, and the open neck is in fluid communication with the head end air plenum. In some embodiments, quarter-wave tube dampers are installed within the fuel nozzle assembly of the head end section.

公开(公告)号：US12173898B1

公开(公告)日：2024-12-24

申请号：US18486368

申请日：2023-10-13

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Pradeep Naik ,  Joseph Zelina ,  Sripathi Mohan ,  Perumallu Vukanti ,  Clayton S. Cooper ,  Michael A. Benjamin ,  Steven C. Vise ,  Karthikeyan Sampath

IPC: F23R3/00 ,  F23R3/42

Abstract: A turbine engine with a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. A combustion section for the turbine engine, having a primary combustor liner including an inner liner and an outer liner annular about an engine centerline. A dome wall extending between the inner liner and the outer liner. A set of primary dome inlets located in the dome wall and circumferentially arranged about the engine centerline. A set of secondary combustors fluidly coupled to a primary combustion chamber, the set of secondary combustors including a first mini combustor and a second mini combustor.

公开(公告)号：US20240418370A1

公开(公告)日：2024-12-19

申请号：US18419006

申请日：2024-01-22

Applicant: Gameto, Inc.

Inventor： Christian KRAMME ,  Dina Radenkovic ,  Martin Varsavsky ,  Klaus E. Wiemer

IPC: F23R3/10 ,  C07K16/28 ,  F01D9/04 ,  F04D29/54 ,  F23R3/00

Abstract: An apparatus and method for oocyte rescue in vitro post stimulation, the apparatus including a computing device, wherein the computing device includes at least a processor; and a memory communicatively connected to the at least processor, the memory containing instructions configuring the at least processor to: receive biological sample data from a biological sample relating to a user, including at least an oocyte; determine a maturity level of the at least an oocyte; assign the at least an oocyte to a culture protocol as a function of the maturity level; receive culture data relating to the at least an oocyte as a function of the culture protocol; and calculate a scoring metric as a function of the culture data.

公开(公告)号：US20240410656A1

公开(公告)日：2024-12-12

申请号：US18207527

申请日：2023-06-08

Applicant: Raytheon Technologies Corporation

Inventor： Michael G. McCaffrey

IPC: F28D15/02 ,  F23R3/00

Abstract: An assembly is provided for an engine. This engine assembly includes a heat exchange apparatus, and the heat exchange apparatus includes a core, a shell and an inner flowpath. The core includes a core sidewall and a plurality of internal passages. The core sidewall extends axially along and circumferentially around an axis. The core sidewall extends radially from a core inner side to a core outer side. The core inner side forms an outer peripheral boundary of the inner flowpath. The internal passages are arranged circumferentially about the axis. Each of the internal passages extends axially in the core sidewall. The shell extends axially along and circumscribes the core. The shell is abutted radially against the core outer side.

公开(公告)号：US20240410581A1

公开(公告)日：2024-12-12

申请号：US18669683

申请日：2024-05-21

Applicant: ROLLS-ROYCE plc

Inventor： Edward A. WALTERS

IPC: F23R3/00

Abstract: A combustor assembly for a gas turbine engine includes a combustor shell extending along a shell axis. The combustor shell includes a shell wall extending around the shell axis and a meter panel connected to an upstream end of the shell wall. The shell wall and the meter panel together define a combustion space therebetween. The combustor assembly further includes: a tile disposed within the combustor shell and including a tile flange portion extending radially with respect to the shell axis; a heatshield connected to the meter panel and extending at least radially towards the tile; a fastener connecting the tile flange portion to the meter panel; and a compartment thermally shielded from the combustion space. Either the heatshield and the tile together form the compartment or the tile alone forms the compartment. The fastener is spaced apart from the combustion space and at least partially disposed within the compartment.

公开(公告)号：US12129812B2

公开(公告)日：2024-10-29

申请号：US17603151

申请日：2020-05-20

Applicant: HYLIION HOLDINGS CORP

Inventor： 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: 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 classification number: 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

Abstract: 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.