公开(公告)号：US11879345B2

公开(公告)日：2024-01-23

申请号：US16805456

申请日：2020-02-28

Applicant: Rosemount Aerospace Inc.

Inventor： Andrew Holl ,  Scott Wigen ,  Robert Edward Sable ,  Scott D. Isebrand ,  Brian Boyd

IPC: F01D25/02 ,  F01D21/12 ,  G01K13/02 ,  G01K13/024 ,  F01D17/08 ,  F01D21/00 ,  F01D25/10

CPC classification number: F01D25/02 ,  F01D21/12 ,  G01K13/02 ,  F01D17/085 ,  F01D21/003 ,  F01D25/10 ,  G01K13/024

Abstract: A sensor includes a mount arranged along a sensor axis, an airfoil body fixed to the mount and having a first face and second face extending along the sensor axis, a heater element, and a temperature probe. The heater element and the temperature probe are positioned within the airfoil body and extend axially along the airfoil body. The airfoil body defines within its interior a pressure channel having an inlet segment extending between the heater element and the first face of the airfoil body to prevent ice formation and/or melt ice entrained within air traversing the pressure channel. Gas turbine engines, methods of removing ice or preventing ice formation, and methods of making sensors are also described.

公开(公告)号：US11814977B1

公开(公告)日：2023-11-14

申请号：US17822990

申请日：2022-08-29

Applicant: RTX Corporation

Inventor： Mason Adam Kessler ,  Joon Won Ha ,  Subhadeep Gan ,  Michael Carl Weber

IPC: F01D25/24 ,  F01D25/10

CPC classification number: F01D25/243 ,  F01D25/10 ,  F05D2240/14 ,  F05D2260/232 ,  F05D2260/31

Abstract: A flange arrangement of a gas turbine engine includes a first flange of a first component, and a second flange of a second component axially offset from the first flange along an engine central longitudinal axis. The first flange is secured to the second flange. One or more flange flowpaths are defined between the first flange and the second flange to convey a flange airflow from an interior of the second component thereby thermally conditioning the flange arrangement. The flange airflow is driven through the one or more flange flowpaths by a pressure differential.

公开(公告)号：US11808159B2

公开(公告)日：2023-11-07

申请号：US18045864

申请日：2022-10-12

Applicant: ROLLS-ROYCE plc

Inventor： Geoffrey B Jones

IPC: F01D25/02 ,  F01D25/10 ,  F01D9/04 ,  F02C7/00

CPC classification number: F01D25/10 ,  F01D9/04 ,  F02C7/00 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2260/20

Abstract: A gas turbine engine comprises a fan; an engine core comprising a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox; an Engine Section Stator (ESS) comprising a plurality of ESS vanes with an external surface washed by the core airflow; an ESS heating system adapted to heat the ESS vanes, and a temperature sensor adapted to detect the temperature of the external surface of the ESS vanes and send a signal to the ESS heating system when said temperature is below a reference temperature. Upon detection and/or inference of ice crystal conditions and receiving from the temperature sensor the signal that the temperature is below the reference temperature, the ESS heating system is activated to heat at least a portion of the external surface of the ESS vanes and promote melting and adhering of ice crystals thereto.

公开(公告)号：US11808157B1

公开(公告)日：2023-11-07

申请号：US17899324

申请日：2022-08-30

Applicant: General Electric Company

Inventor： Naveena K P ,  Ravindra Shankar Ganiger ,  Domala Uma Maheshwar ,  Kishore Budumuru ,  Kudum Shinde ,  Abhishek Goverdhan

IPC: F01D11/24 ,  F01D25/24 ,  F01D25/10

CPC classification number: F01D11/24 ,  F01D25/10 ,  F01D25/24 ,  F05D2240/11 ,  F05D2260/20 ,  F05D2260/50 ,  F05D2270/821 ,  F05D2300/50212

Abstract: Disclosed herein are example variable flowpath casings for blade tip clearance control. An example casing for a turbine engine includes an annular substrate extending along an axial direction, the annular substrate defining a cavity at a radially inward surface of the annular substrate, and a smart structure coupled to the annular substrate, the smart structure including a support structure; an actuator structure to at least one of expand or contract in response to a change in temperature of the actuator structure, and a variable surface coupled to the support structure, the support structure to move the variable surface in a radial direction.

公开(公告)号：US20230332513A1

公开(公告)日：2023-10-19

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: F01D25/10 ,  F02C7/12 ,  F01D25/12

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

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：US11761344B1

公开(公告)日：2023-09-19

申请号：US17724074

申请日：2022-04-19

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Brian Lewis Devendorf ,  Jeffrey Douglas Rambo ,  Brian Gene Brzek ,  Kevin Edward Hinderliter ,  Erich Alois Krammer ,  Arthur William Sibbach

IPC: F01D19/02 ,  F01D25/10 ,  F01D25/18

CPC classification number: F01D19/02 ,  F01D25/10 ,  F01D25/18 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2260/607 ,  F05D2260/85 ,  F05D2260/98

Abstract: A method is provided for operating a thermal management system of a gas turbine engine. The method includes: operating the gas turbine engine to start-up the gas turbine engine; receiving data indicative of a state of a thermal transport bus of the thermal management system using a sensor, the state of the thermal transport bus including a phase of a thermal fluid within the thermal transport bus; and starting a pump of a pump assembly in response to receiving data indicative of the state of the thermal transport bus of the thermal management system, the pump in fluid communication with the thermal transport bus.

公开(公告)号：US11649736B2

公开(公告)日：2023-05-16

申请号：US17495418

申请日：2021-10-06

Applicant: ROLLS-ROYCE PLC

Inventor： Stephen J Bradbrook ,  Martin N Goodhand ,  Paul M Hield ,  Andrew Parsley ,  Natalie C Wong ,  Robert J Corin ,  Thomas S Binnington

IPC: B64D33/10 ,  F02C7/14 ,  F01D25/10 ,  F01D5/18 ,  F02C7/141 ,  F02K3/06

CPC classification number: F01D25/10 ,  B64D33/10 ,  F01D5/18 ,  F02C7/141 ,  F02K3/06 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2260/221 ,  F05D2270/303 ,  F05D2270/306

Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly includes a plurality of fan blades defining a fan diameter. The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and the heat exchanger module including a plurality of heat transfer elements for transfer of heat from a first fluid contained within the heat transfer elements to an airflow passing over a surface of the heat transfer elements prior to entry of the airflow into an inlet to the fan assembly. Each heat transfer element may be individually and independently fluidly isolated from the remaining heat transfer elements.

公开(公告)号：US20190203611A1

公开(公告)日：2019-07-04

申请号：US15860804

申请日：2018-01-03

Applicant: General Electric Company

Inventor： Michael Alan Stieg ,  Nicholas John Bloom ,  Eric Ryan Newburn ,  Brett Joseph Geiser

IPC: F01D25/10 ,  F01D19/02 ,  F02C9/18 ,  F23R3/00 ,  F23R3/04

CPC classification number: F01D25/10 ,  F01D19/02 ,  F02C9/18 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2260/941 ,  F05D2300/6033 ,  F23R3/002 ,  F23R3/007 ,  F23R3/04

Abstract: A combustor assembly for a gas turbine engine includes a dome defining a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. At least a portion of the forward end is received within the slot of the dome. The forward end of the liner defines a plurality of warming holes that allow for a warming airflow to flow therethrough to warm the forward end at a faster rate during transient operating conditions of the engine thereby reducing transient stresses and increasing liner durability.

公开(公告)号：US20180320548A1

公开(公告)日：2018-11-08

申请号：US16033356

申请日：2018-07-12

Applicant: United Technologies Corporation

Inventor： Michael F. Blair ,  Tracy A. Propheter-Hinckley ,  Mark F. Zelesky

IPC: F01D25/12 ,  F28F7/02 ,  F28F1/40 ,  F01D25/10 ,  F28D15/00 ,  F02C7/14 ,  F28F1/12

CPC classification number: F01D25/12 ,  F01D25/10 ,  F02C7/14 ,  F05D2260/205 ,  F05D2260/213 ,  F05D2260/232 ,  F28D15/00 ,  F28F1/124 ,  F28F1/40 ,  F28F7/02 ,  F28F2255/18 ,  Y02T50/676

Abstract: A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.

公开(公告)号：US20180058339A1

公开(公告)日：2018-03-01

申请号：US15247153

申请日：2016-08-25

Applicant: General Electric Company

Inventor： David August Snider ,  Lewis Berkley Davis, JR. ,  Randy Scott Rosson ,  Michael Joseph Alexander

IPC: F02C9/52 ,  F01D21/00 ,  F01D25/10 ,  F02C6/18 ,  F01K13/00 ,  F01K23/10 ,  G05B19/418 ,  G05D7/06

CPC classification number: F02C9/52 ,  F01D21/00 ,  F01D21/003 ,  F01D25/10 ,  F01D25/30 ,  F01K13/003 ,  F01K23/10 ,  F01K23/101 ,  F02C6/18 ,  F02C9/00 ,  F02C9/26 ,  F05D2220/32 ,  F05D2220/72 ,  F05D2270/303 ,  F05D2270/304 ,  F05D2270/306 ,  F05D2270/54 ,  F22B35/00 ,  G05B19/41835 ,  G05B2219/34315 ,  G05D7/0623

Abstract: A system includes a controller of a power generation system including a memory storing instructions and a processor that executes the instructions. The instructions cause the controller to control the power generation system to provide inlet bleed heat flow to a gas turbine during deceleration of the gas turbine. The instructions also cause the controller to receive a first temperature, a rotational speed of the gas turbine, and an inlet bleed heat flow rate. Additionally, the instructions cause the controller to calculate an exhaust flow rate based on at least the first temperature, the rotational speed, and the inlet bleed heat flow rate. Further, the instructions cause the controller to control the power generation system to isolate a fuel source from the gas turbine at a portion of normal operating speed of the gas turbine sufficient to achieve a purging volume during coast down of the gas turbine.