公开(公告)号：US20250043734A1

公开(公告)日：2025-02-06

申请号：US18362116

申请日：2023-07-31

Applicant: RTX CORPORATION

Inventor： Federico Papa ,  Christopher Moore

IPC: F02C9/18 ,  F01D21/00 ,  F02C7/18

Abstract: A method includes the steps of providing an engine with a compressor. A tap taps air from the compressor and passes it through a bleed valve, and a precooler, and downstream of the precooler to a use on an associated aircraft. Fan cooling air passes through a fan air valve across the precooler to cool the tapped air before it passes to the use and then into a core engine downstream of the precooler to cool internal components. If shutdown of the engine is coming, the method runs the engine for a period of time, closes the bleed valve and opens the fan air valve to allow fan cooling air to continue passing through the precooler, and into the engine to cool the components. A combination and an aircraft are also disclosed.

公开(公告)号：US20250003375A1

公开(公告)日：2025-01-02

申请号：US18740613

申请日：2024-06-12

Applicant: General Electric Company

Inventor： Joseph George Rose ,  Thomas Ory Moniz ,  Tsuguji Nakano ,  Jeffrey S. Spruill ,  Brandon Wayne Miller ,  Randy M. Vondrell ,  David Marion Ostdiek ,  Craig William Higgins ,  Alexander Kimberley Simpson

IPC: F02K3/06 ,  F02C7/18 ,  F02C9/18

Abstract: A gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct, a primary fan driven by the turbomachine, a secondary fan located downstream of the primary fan within the inlet duct, a heat exchanger disposed in the fan duct, and a booster upstream of the heat exchanger, the booster including a booster cowl extending into the fan duct, the booster cowl separating an upstream portion of the fan duct into an upper fan duct having an upper fan duct inlet and a lower fan duct having a lower fan duct inlet, the upper fan duct inlet and lower fan duct inlet collectively forming the fan duct inlet.

公开(公告)号：US20250003371A1

公开(公告)日：2025-01-02

申请号：US18710368

申请日：2022-11-09

Applicant: BAE SYSTEMS PLC

Inventor： Jeremy Henry Owston

IPC: F02C6/18 ,  F02C9/18

Abstract: A heat engine system (100, 1100). The heat engine system (100, 1100) comprises a compressor (300) having an inlet (302) and an outlet (304), a heat source (400) having an inlet (402) and an outlet (404), and a turbine (500) having an inlet (502) and an outlet (504). The compressor (300), heat source (400) and turbine (500) define part of a working fluid flow circuit ( ). The heat engine system further comprises a housing (600) which is operable to be sealed to define a reservoir (602) in which the compressor (400), heat source (400), turbine (500) and working fluid flow circuit (700) are located. The working fluid flow circuit (700) further comprises a compressor-to-heat-source duct (800) which extends between the compressor outlet (304) and the heat source inlet (402), a heat-source-to-turbine duct (802) extends between the heat source outlet (404) and the turbine inlet (502), and a turbine-to-compressor duct (804) extends between the turbine outlet (504) and the compressor inlet (302). A bleed valve (806) is provided in flow communication with the compressor outlet (304), operable to bleed working fluid into the reservoir (602). An intake valve (808) is provided in flow communication with the compressor inlet (302) operable to allow the passage of working fluid from the reservoir (602) to the compressor inlet (302).

公开(公告)号：US12180897B2

公开(公告)日：2024-12-31

申请号：US18353741

申请日：2023-07-17

Applicant: General Electric Company

Inventor： Thomas Malkus ,  Trevor H. Wood ,  Giridhar Jothiprasad ,  Nageswar Ganji ,  Hiranya Kumar Nath ,  Ravindra Shankar Ganiger ,  Ambika Shivamurthy

IPC: F02C9/18 ,  F01D17/10 ,  F02C7/052 ,  F04D27/02

Abstract: Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.

公开(公告)号：US20240352896A1

公开(公告)日：2024-10-24

申请号：US18303111

申请日：2023-04-19

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Bruce David Reynolds ,  Nick Nolcheff ,  Ryan Bernaud ,  Greyson Boyll

IPC: F02C9/18 ,  F02C3/08 ,  F02C9/22

CPC classification number: F02C9/18 ,  F02C3/08 ,  F02C9/20 ,  F02C9/22 ,  F04D27/0223 ,  F04D27/0246 ,  F05D2270/101 ,  F05D2270/304

Abstract: Systems and methods for stable operation of a compressor of a gas turbine engine include axial stages, each including a series of rotor blades. A centrifugal stage has a centrifugal impeller disposed downstream from the axial stages. Air flows through the compressor first through the axial stages and then through the centrifugal stage. Each respective axial stage includes mechanisms for the avoidance of certain operating conditions of the compressor such as surge. The mechanisms include variable vane sets disposed upstream from a series of the rotor blades or a bleed port or ports around the respective axial stage downstream from the series of rotor blades to selectively extract air from the respective axial stage.

公开(公告)号：US12123360B2

公开(公告)日：2024-10-22

申请号：US17756970

申请日：2020-12-01

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Nicolas Bertrand Georges De Blois ,  Clément Dupays

IPC: G05B19/29 ,  B60R16/03 ,  F02C9/18 ,  H02P5/49

CPC classification number: F02C9/18 ,  B60R16/03 ,  H02P5/49 ,  F05D2220/323 ,  F05D2260/606 ,  F05D2270/62

Abstract: In an electromechanical actuation chain for controlling the movement of mobile loads of an aircraft turbine engine, from a control unit, one or more of these mobile loads being actuated by an electromechanical actuator, there is provided for control of this movement a single Ethernet controller having deterministic control that uses an Ethernet bus to control a set of converters acting selectively on the electromechanical actuators.

公开(公告)号：US12123359B2

公开(公告)日：2024-10-22

申请号：US15978097

申请日：2018-05-12

Applicant: GE Avio S.r.l.

Inventor： Mehdi Milani Baladi ,  Robert Jon McQuiston ,  Aniello Esposito ,  Joseph Donofrio ,  Nicholas William Simone ,  Simone Castellani

IPC: F02C9/18 ,  F02C6/08 ,  F04D27/02

CPC classification number: F02C9/18 ,  F02C6/08 ,  F04D27/0215 ,  F05D2220/323 ,  F05D2260/606 ,  F05D2270/101 ,  F05D2270/30

Abstract: An aircraft can comprise an engine, an environmental control system, an engine controller, and a plurality of sensors detecting engine or aircraft parameters. Engine or aircraft operation can be updated in real time based on input from the sensors, including airflow management or operation parameters.

公开(公告)号：US20240337219A1

公开(公告)日：2024-10-10

申请号：US18130514

申请日：2023-04-04

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Louis DURANLEAU-HENDRICKX ,  Daniel Coutu

IPC: F02C9/18

CPC classification number: F02C9/18 ,  F05D2260/80 ,  F05D2260/83 ,  F05D2270/301 ,  F05D2270/304 ,  F05D2270/71 ,  F05D2270/802

Abstract: Methods and systems for adjusting a modulation characteristic of a bleed-off valve of a gas turbine engine are described. The method comprises obtaining a first setpoint configuration associated with a first modulation characteristic of the bleed-off valve, obtaining operating conditions of the gas turbine engine, determining an adjustment factor based on the first setpoint configuration and the operating conditions of the gas turbine engine, and adjusting the bleed-off valve to a second setpoint configuration associated with a second modulation characteristic based on the first setpoint configuration and the adjustment factor, the second modulation characteristic being different from the first modulation characteristic.

公开(公告)号：US12085027B2

公开(公告)日：2024-09-10

申请号：US17470261

申请日：2021-09-09

Applicant: General Electric Company

Inventor： John Carl Glessner ,  Daniel John Oehrle ,  Mark Edward Linz

IPC: F02C9/18

CPC classification number: F02C9/18 ,  F05D2220/32

Abstract: A gas turbine engine includes a turbomachine defining a core flowpath extending through a first compressor and a second compressor, wherein a first compressor frame defines a compressor bypass passage extending from the core flowpath at the first compressor frame; and a forward compressor frame positioned between the first compressor and the second compressor, wherein the forward compressor frame defines at least in part a second portion of the core flowpath at a location downstream of the first portion of the core flowpath, wherein the forward compressor frame defines a compressor bleed passage extending from the core flowpath at a location downstream of the first compressor and upstream of the second compressor to egress a flow of air away from the core flowpath.

公开(公告)号：US12071903B2

公开(公告)日：2024-08-27

申请号：US16864881

申请日：2020-05-01

Applicant: Raytheon Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Martin Richard Amari ,  Geoffrey T. Blackwell

IPC: F02C9/18 ,  F02C7/26

CPC classification number: F02C9/18 ,  F02C7/26 ,  F05D2240/127 ,  F05D2260/606 ,  F05D2260/85

Abstract: A system for bleeding air from a core flow path of a gas turbine engine includes a bleed valve in a bleed air duct configured to receive bleed air from a first entrance point to the core flow path into the bleed air duct; a pressurized air valve in a pressurized air duct configured to receive pressurized air from a second entrance point to the core flow path, the pressurized air at a pressure greater than that received into the first entrance point; an eductor outlet from the pressurized air duct located in the bleed air duct; and a control system operable to control operation of the bleed valve and the pressurized air valve.