公开(公告)号：US20240352895A1

公开(公告)日：2024-10-24

申请号：US18304129

申请日：2023-04-20

Applicant: Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce Corporation

Inventor： Govindaraj Kalyanasamy ,  Peter Schenk

IPC: F02C9/00 ,  F01D25/10

CPC classification number: F02C9/00 ,  F01D25/08 ,  F01D25/10 ,  F02C9/18 ,  F05D2260/20

Abstract: An example system includes a thermal energy system configured to transport thermal energy harvested from a first portion of a gas turbine engine to a second portion of the gas turbine engine after the gas turbine engine was in operation, wherein the transported thermal energy minimizes or prevents undesired contact or seizing of a rotor with another component of the gas turbine engine due to warping of the rotor due to uneven cooling of the gas turbine engine after the operation. The thermal energy system includes a cavity configured to flow a fluid, wherein the fluid is configured to transport thermal energy from the first portion to the second portion.

公开(公告)号：US12078102B2

公开(公告)日：2024-09-03

申请号：US17951972

申请日：2022-09-23

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Stephen H. Taylor ,  Alan Retersdorf ,  Oliver V. Atassi ,  Nathan A. Snape

IPC: F02C6/08 ,  F02C3/13 ,  F02C7/08 ,  F02C7/10 ,  F02C7/32 ,  F02C9/18 ,  F02C9/52 ,  F02G5/00 ,  F02K3/02

CPC classification number: F02C6/08 ,  F02C3/13 ,  F02C7/08 ,  F02C7/10 ,  F02C7/32 ,  F02C9/18 ,  F02C9/52 ,  F02G5/00 ,  F02K3/02

Abstract: A gas turbine engine assembly including a tap that is at a location up stream of the combustor section for drawing a bleed airflow. An exhaust heat exchanger is configured to transfer thermal energy from the exhaust gas flow into the bleed airflow and communicate the heated bleed airflow into the turbine section where it is expanded to drive the turbine section.

公开(公告)号：US12071912B2

公开(公告)日：2024-08-27

申请号：US17734324

申请日：2022-05-02

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Steven W. Burd

IPC: F02K3/02 ,  F02C3/04 ,  F02C7/36 ,  F02C9/18

CPC classification number: F02K3/02 ,  F02C3/04 ,  F02C7/36 ,  F02C9/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/606

Abstract: A turboshaft engine includes a core engine, including a fan section, a compressor section, a primary combustor and a turbine section positioned within a core flow path of the gas turbine engine; a bypass splitter positioned radially outward of the core engine and configured to house the compressor section, the primary combustor and the turbine section; a bypass duct positioned radially outward of the bypass splitter; and a power spool operably coupled to the core engine and configured rotationally drive a fan included within the fan section.

公开(公告)号：US20240280059A1

公开(公告)日：2024-08-22

申请号：US18581952

申请日：2024-02-20

Applicant: Textron Aviation Inc.

Inventor： Trey Marcus Siemens ,  Burl Justin Fletcher

IPC: F02C9/18 ,  B64D13/06

CPC classification number: F02C9/18 ,  B64D13/06 ,  B64D2013/0618 ,  F05D2220/323 ,  F05D2260/606 ,  F05D2270/306 ,  F05D2270/335

Abstract: A pneumatic flow control system for an aircraft includes a control system operating and implementing a software program through a digital environment, the software program having one or more rules; a sensor in digital communication with the control system, the sensor to relay engine power data to the control system; an electronically controlled valve in digital communication with the control system, the electronically controlled valve to control an amount of bleed air flowing therethrough; a first rule defining an engine power parameter and a valve position for the electronically controlled valve and using the engine power data relayed from the sensor, receiving data equating to the engine power parameter activates transmitting a command to the electronically controlled valve to adjust to the valve position; and the valve position is set to restrict flow through the valve to below a threshold limit.

公开(公告)号：US20240229725A9

公开(公告)日：2024-07-11

申请号：US17969415

申请日：2022-10-19

Applicant: Mitsubishi Power Aero LLC

Inventor： Ruurd Vanderleest

IPC: F02C9/18

CPC classification number: F02C9/18 ,  F05D2220/32 ,  F05D2220/76 ,  F05D2270/335

Abstract: A controller for a gas turbine engine comprises a fuel flow sensor interface for receiving input signals indicative of a fuel flow into a combustor, a power output sensor interface for receiving input signals indicative of power output of an electrical generator driven via the gas turbine engine, a bleed valve interface for providing an output signal to a bleed valve that controls bleed air to vent a compressor of the gas turbine engine, and memory having stored therein instructions for determining functionality of the bleed valve based on evaluating efficiency of the gas turbine engine when the output signal is issued. A method comprises sensing efficiency of a gas turbine engine in response to actuation of a compressor bleed valve, comparing the efficiency to baseline efficiency, and outputting indicia of a differential between the efficiency and the baseline efficiency as an indication of operability of the first bleed valve.

公开(公告)号：US20240229677A9

公开(公告)日：2024-07-11

申请号：US18275082

申请日：2022-03-08

Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.

Inventor： Tatsuki UEDA ,  Kazushige KUWAZURU ,  Daiki FUJIMURA ,  Motohiro GOSHIMA

IPC: F01D25/00 ,  F02C6/18 ,  F02C9/18

CPC classification number: F01D25/002 ,  F02C6/18 ,  F02C9/18

Abstract: A method for cleaning a steam system including an intermittent operation processing step and a commissioning processing step are executed. The intermittent operation processing step includes: a no-load operation step in which a gas turbine is operated with no load, with a steam stop valve and a bypass valve closed; during the no-load operation step, a pressure accumulating step in which steam is accumulated in a pressure accumulation region; and, after the pressure accumulating step, an intermittent blowing step in which the bypass valve is opened, and steam in the pressure accumulation region is allowed to flow into a condenser. The commissioning processing step includes: a commissioning step in which the gas turbine is commissioned with the steam stop valve closed and the bypass valve open; and a continuous blowing step in which steam from a waste heat recovery boiler is allowed to flow into the condenser.

公开(公告)号：US12031481B2

公开(公告)日：2024-07-09

申请号：US18459716

申请日：2023-09-01

Applicant: RTX CORPORATION

Inventor： Alan Retersdorf ,  Stephen H. Taylor ,  Oliver V. Atassi

IPC: F02C6/18 ,  F02C7/32 ,  F02C9/18

CPC classification number: F02C6/18 ,  F02C7/32 ,  F02C9/18 ,  F05D2220/62 ,  F05D2260/10 ,  F05D2260/213 ,  F05D2260/232

Abstract: A turbine engine assembly includes a tap is at a location upstream of the combustor section where a bleed airflow is drawn. The bleed air is pressurized in an auxiliary compressor section, heated in an exhaust heat exchanger, and expanded through a power turbine that is coupled to drive the auxiliary compressor section.

公开(公告)号：US12031478B2

公开(公告)日：2024-07-09

申请号：US17951991

申请日：2022-09-23

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Stephen H. Taylor ,  Alan Retersdorf ,  Oliver V. Atassi

IPC: F02C6/08 ,  F02C3/10 ,  F02C7/18 ,  F02C7/32 ,  F02C7/36 ,  F02C9/18

CPC classification number: F02C6/08 ,  F02C3/10 ,  F02C7/18 ,  F02C7/32 ,  F02C7/36 ,  F02C9/18 ,  F05D2220/323 ,  F05D2220/36

Abstract: An aircraft propulsion system includes a core engine that includes a core flow path where a core airflow is compressed in a compressor section, communicated to a combustor section, mixed with fuel and ignited to generate a gas flow that is expanded through a turbine section for powering a primary propulsor. The aircraft propulsion system further includes a tap that is at a location upstream of the combustor section where a bleed airflow is drawn, a heat exchanger where the bleed airflow is heated by the gas flow, a power turbine through which heated bleed airflow is expanded to generate a work output, and a secondary propulsor that is driven by the work output that is generated by the power turbine.

公开(公告)号：US20240209783A1

公开(公告)日：2024-06-27

申请号：US18457439

申请日：2023-08-29

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Scott SMITH

IPC: F02C7/22 ,  F02C9/18

CPC classification number: F02C7/22 ,  F02C9/18 ,  F05D2220/323 ,  F05D2260/608

Abstract: In accordance with at least one aspect of this disclosure, there is provided a system for an aircraft engine. In embodiments, the system includes an accessory box and a fuel accessory located in an interior space within the accessory box, where a vent is defined through a wall of the accessory box. In embodiments, the vent includes a plurality of holes or slots in an outer wall of the accessory box for passage of gaseous fuel from the interior space. In embodiments, the vent is configured for passive ventilation of the interior space.

公开(公告)号：US20240200495A1

公开(公告)日：2024-06-20

申请号：US18539813

申请日：2023-12-14

Applicant: Rolls-Royce plc

Inventor： Zahid M. HUSSAIN ,  Vasileios Kyritsis

IPC: F02C7/18 ,  F02C9/18

CPC classification number: F02C7/18 ,  F02C9/18 ,  F05D2240/14 ,  F05D2260/213 ,  F05D2260/31 ,  F05D2260/606

Abstract: A thermal management system for a gas turbine engine includes a plurality of inlet and outlet vanes extending from a bypass inner wall towards an outer cowl, a plurality of first removable shims, a plurality of second removable shims, and a third removable shim. Each first removable shim extends between and engages the outer cowl and a corresponding inlet vane. Each second removable shim extends between and engages the outer cowl and a corresponding outlet vane. The third removable shim extends between and engages a heat exchanger and the outer cowl. Each of the plurality of first removable shims, each of the plurality of second removable shims, and the third removable shim is removable for positionally adjusting the outer cowl relative to the bypass inner wall.