公开(公告)号：US20250043723A1

公开(公告)日：2025-02-06

申请号：US18228255

申请日：2023-07-31

Applicant: Rolls-Royce North American Technologies Inc.

Inventor： Kerry J. Lighty ,  Douglas J. Snyder

IPC: F02C7/12 ,  F02C9/18

Abstract: A gas turbine engine includes a bypass duct including an outer wall, a flow wall arranged within the bypass duct so as to bifurcate a flow path of the bypass duct into radially outer and inner flow paths, and a heat exchanger. The outer wall includes a segmented wall portion that is removable from the outer wall. The heat exchanger is arranged within the radially outer flow path and is coupled to the segmented wall portion such that the heat exchanger is configured to be removed from the bypass duct via removal of the segmented wall portion from the outer wall.

公开(公告)号：US20250027430A1

公开(公告)日：2025-01-23

申请号：US18356650

申请日：2023-07-21

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： JEFFREY J. LIENAU ,  COURTNEY LANA PRUETTE ,  KEVIN M. BROWN ,  RICHARD YU ,  PAUL K. SANCHEZ

IPC: F02C7/12 ,  F01D25/24 ,  F02C3/04

Abstract: A gas turbine engine is provided. The gas turbine engine includes a case having a wall that provides a manifold cavity, the wall including an aperture and a bore; a tube assembly with a flange that provides a fluid passage aligned with the aperture; a mixing feature arranged in the manifold cavity and including a plate with a hole; and an insert having a body and a head, the body received in the hole and sealed in the bore, the head capturing the plate against the wall. The mixing feature is configured to divert a flow of cooling fluid in at least a counterclockwise direction improving jet mixing and placement of the cooling fluid.

公开(公告)号：US12203386B2

公开(公告)日：2025-01-21

申请号：US17675564

申请日：2022-02-18

Applicant: Raytheon Technologies Corporation

Inventor： Lawrence A. Binek ,  Sean R. Jackson ,  Jose R. Paulino

IPC: F01D5/18 ,  F01D25/12 ,  F02C7/12

Abstract: An assembly is provided for a gas turbine engine. This assembly includes a compressor rotor, a turbine rotor and a cooling circuit. The compressor rotor includes a gas path surface. The turbine rotor is rotatable with the compressor rotor about a rotational axis. The cooling circuit includes an inlet in the gas path surface. The cooling circuit extends from the inlet, through the compressor rotor and into the turbine rotor.

公开(公告)号：US12104530B2

公开(公告)日：2024-10-01

申请号：US17940035

申请日：2022-09-08

Applicant: ROLLS-ROYCE plc

Inventor： Benjamin J Sellers ,  Jonathan A Cherry ,  Craig Town

IPC: F02C7/32 ,  F02C3/06 ,  F02C7/12

CPC classification number: F02C7/12 ,  F02C3/06 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2260/40

Abstract: An aircraft turbofan gas turbine engine includes a fan assembly, a compressor module, and a turbine module. An electric machine positioned downstream of the fan assembly is rotationally connected to the turbine module. The fan assembly is in fluid communication with the compressor module by an intermediate duct and includes a highest pressure fan stage having a plurality of fan blades defining a fan diameter. The compressor module includes a lowest pressure compressor stage having a row of rotor blades. An intermediate flow axis is defined joining a radially outer tip of a trailing edge of one of the fan blades of the highest pressure fan stage, and a radially outer tip of a leading edge of one of the rotor blades of a leading edge of a lowest-pressure compressor blade. An intermediate flow axis angle and the intermediate flow axis angle is from −20 to −30 degrees.

公开(公告)号：US12104499B2

公开(公告)日：2024-10-01

申请号：US18330000

申请日：2023-06-06

Applicant: General Electric Company

Inventor： Scott Alan Schimmels ,  Daniel Alan Niergarth ,  Arthur William Sibbach ,  Brandon Wayne Miller

IPC: F02C7/12 ,  F01D25/10 ,  F01D25/12

CPC classification number: F01D25/10 ,  F01D25/12 ,  F02C7/12 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2260/213

Abstract: A method of regulating pressure in a thermal transport bus of a gas turbine engine, the method including: operating the gas turbine engine with the thermal transport bus having an intermediary heat exchange fluid flowing therethrough, the thermal transport bus including one or more heat source heat exchangers and one or more heat sink heat exchangers in thermal communication through the intermediary heat exchanger fluid; and adjusting a flow volume of the thermal transport bus using a variable volume device in fluid communication with the thermal transport bus in response to a pressure change associated with the thermal transport bus.

公开(公告)号：US12092035B2

公开(公告)日：2024-09-17

申请号：US18148199

申请日：2022-12-29

Applicant: General Electric Company

Inventor： Rajan Prakash ,  Shivani Agarwal

IPC: F02C7/25 ,  F02C7/057 ,  F02C7/12 ,  F23N5/02 ,  F23N5/24

CPC classification number: F02C7/25 ,  F02C7/057 ,  F02C7/12 ,  F23N5/022 ,  F23N5/242 ,  F23N2231/06 ,  F23N2241/20

Abstract: A fire detection system for a gas turbine system including fire risk zones is provided. The system includes a pipe intake port proximate to each of the fire risk zones within a gas turbine system enclosure, and a manifold in fluid communication with the pipe intake port. A temperature sensor is positioned in the manifold upstream of a cooling system. The cooling system reduces a temperature of a gas flow in the manifold, allowing use of an aspirating smoke detector. An aspirating smoke detector, which is downstream of the cooling system, draws in the gas flow and detects smoke in the gas flow. A controller generates a first alarm in response to the temperature sensor detecting a temperature of the gas flow exceeding a temperature threshold, or a second alarm in response to the aspirating smoke detector detecting smoke in the gas flow.

公开(公告)号：US12092030B2

公开(公告)日：2024-09-17

申请号：US17940055

申请日：2022-09-08

Applicant: ROLLS-ROYCE plc

Inventor： Natalie C Wong ,  Jonathan A Cherry ,  Paul R Davies ,  David A Jones ,  Andrew J Newman ,  Benjamin J Sellers ,  Stephen J Bradbrook

IPC: F02C7/12 ,  F02C6/20 ,  F02C7/32

CPC classification number: F02C7/12 ,  F02C6/20 ,  F02C7/32 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2260/213

Abstract: An aircraft gas turbine engine includes a heat exchanger module, and a core engine including an intermediate-pressure compressor, a high-pressure compressor, a high pressure turbine, and a low-pressure turbine. The high-pressure compressor is connected to the high-pressure turbine by a first shaft, and the intermediate-pressure compressor is connected to the low-pressure turbine by a second shaft. The heat exchanger module includes a central hub and heat transfer elements extending radially from the central hub and spaced in a circumferential array, for transferring heat energy from a fluid within the heat transfer elements to an inlet airflow passing over the heat transfer elements prior to entry of the airflow into an inlet to the core engine. The gas turbine engine further includes a first electric machine connected to the first shaft and positioned downstream of the heat exchanger module, and a second electric machines connected to the second shaft.

公开(公告)号：US20240301827A1

公开(公告)日：2024-09-12

申请号：US18179660

申请日：2023-03-07

Applicant: Rolls-Royce North American Technologies, Inc.

Inventor： Alan W. Smith ,  Sara Karaffa

IPC: F02C7/12 ,  F02C6/20

CPC classification number: F02C7/12 ,  F02C6/20 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2230/60 ,  F05D2260/20

Abstract: Gas turbine engines include an engine frame defining an inner radial surface, a shaft rotatably mounted in the engine frame along a longitudinal axis, and an electric machine that includes a rotor coupled to the shaft and a stator coupled to the engine frame and defining an outer radial surface. In some gas turbine engines, the engine frame includes inlet and outlet fluid passages, each extending to a portion of the inner radial surface. The portion of the inner radial surface of the engine frame is spaced from the outer radial surface of the stator to form an annular fluid passage around the stator of an electric machine. The annular fluid passage is configured to direct a cooling fluid around the stator to remove heat from the stator. Some gas turbine engines include two or more positioning keys configured to fix the stator relative to the engine frame.

公开(公告)号：US20240263561A1

公开(公告)日：2024-08-08

申请号：US18567254

申请日：2022-06-23

Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.

Inventor： Tomoko Morikawa ,  Satoshi Hada

IPC: F01D9/04 ,  F01D25/12 ,  F02C7/12

CPC classification number: F01D9/041 ,  F01D25/12 ,  F02C7/12 ,  F05D2240/12 ,  F05D2260/20

Abstract: A turbine stator vane comprising: a vane body; a shroud formed at an end of the vane body in a vane height direction; a fillet portion joining the vane body and the shroud; and a plurality of cooling holes in a bottom plate contacting a combustion gas flow path. The plurality of cooling holes connect to entry openings and downstream exit openings formed in the bottom plate. The entry openings and the exit openings are connected by cooling hole center lines having the same inclination with respect to an axial direction. The plurality of cooling holes constitute a set of cooling hole rows in which a linear first opening center line connecting the centers of the exit openings and a linear second opening center line connecting the centers of the entry openings are formed parallel to each other.

公开(公告)号：US20240229718A9

公开(公告)日：2024-07-11

申请号：US18148199

申请日：2022-12-29

Applicant: General Electric Company

Inventor： Rajan Prakash ,  Shivani Agarwal

IPC: F02C7/25 ,  F02C7/057 ,  F02C7/12 ,  F23N5/02 ,  F23N5/24

CPC classification number: F02C7/25 ,  F02C7/057 ,  F02C7/12 ,  F23N5/022 ,  F23N5/242 ,  F23N2231/06 ,  F23N2241/20

Abstract: A fire detection system for a gas turbine system including fire risk zones is provided. The system includes a pipe intake port proximate to each of the fire risk zones within a gas turbine system enclosure, and a manifold in fluid communication with the pipe intake port. A temperature sensor is positioned in the manifold upstream of a cooling system. The cooling system reduces a temperature of a gas flow in the manifold, allowing use of an aspirating smoke detector. An aspirating smoke detector, which is downstream of the cooling system, draws in the gas flow and detects smoke in the gas flow. A controller generates a first alarm in response to the temperature sensor detecting a temperature of the gas flow exceeding a temperature threshold, or a second alarm in response to the aspirating smoke detector detecting smoke in the gas flow.