公开(公告)号：US12234737B2

公开(公告)日：2025-02-25

申请号：US18263624

申请日：2022-01-26

Applicant: SAFRAN

Inventor： Nicolas Claude Parmentier ,  Gabriel Perez

IPC: F01D17/10 ,  F01D17/14 ,  F02C6/08 ,  F02C9/18 ,  F04D27/00 ,  F04D27/02

Abstract: A system for controlling discharge doors of a turbomachine includes: a ring and a device connecting the ring to each discharge door. The ring is made up of bars connected end-to-end by rotary links ensuring that a bar pivoting on itself causes the other bars to pivot on themselves, with each discharge door being connected to a corresponding bar in order to open or close when this bar pivots.

公开(公告)号：US12196088B2

公开(公告)日：2025-01-14

申请号：US18052942

申请日：2022-11-07

Applicant: MTU Aero Engines AG

Inventor： Julia Schmidt-Petersen ,  Franz-Josef Ertl ,  Florian Neuberger

IPC: F01D17/14 ,  F01D17/12 ,  F01D17/16

Abstract: An adjustment lever adjusts a stator vane of a turbomachine. The adjustment lever has: a first connection site, of a plurality of connection sites, the first connection site being configured to join to an adjustment ring; a second connection site, of the connection sites, the second connection stie being configured to join to the stator vane; and a joining member arranged between the first connection site and the second connection site. The joining member is shaped having at least two struts which adjoin at least one of the connection sites.

公开(公告)号：US12146414B2

公开(公告)日：2024-11-19

申请号：US18048611

申请日：2022-10-21

Applicant: Rolls-Royce North American Technologies Inc.

Inventor： Timothy Unton ,  Andrew Eifert ,  Michael Moser

IPC: F01D17/14 ,  F01D9/04

Abstract: A vane assembly includes vanes, an actuator assembly, and a controller. The vanes are configured to rotate about their pitch axes. The actuator assembly includes an annular ring arranged radially outward of the vanes and coupled to the vanes, a magnet arranged on the annular ring, and a stator arranged adjacent the magnet. The ring is configured to rotate the vanes about the pitch axes in response to rotation of the ring about the central axis and the stator is configured to selectively rotate the magnet and annular ring about the central axis. The controller controls movement of the ring via the stator and magnets in response to at least one of (i) at least one operating condition of the gas turbine engine, or (ii) at least one operating parameter of the at least one first vane.

公开(公告)号：US12140033B2

公开(公告)日：2024-11-12

申请号：US18494907

申请日：2023-10-26

Applicant: ABB Schweiz AG

Inventor： Camilo Lopez ,  Mark Foltz ,  Steve Miller ,  Kevin Dowdell ,  Mark Wieland ,  Alan Majors

IPC: F01C20/28 ,  F01D17/06 ,  F01D17/14 ,  F01D17/26 ,  F01D21/02 ,  F01K13/00 ,  F01K13/02 ,  F02C7/232 ,  F02C9/26 ,  F02C9/28 ,  F02C9/52 ,  F02C9/54 ,  F16K37/00 ,  G01P21/02 ,  G01R31/28 ,  H02J3/38 ,  H02J3/40

Abstract: A system for controlling a turbine valve is provided. The system includes a hydraulic pilot valve section being moveable in a first direction and a second direction; a main hydraulic valve section being moveable in a first direction to close the turbine valve and a second direction to open the turbine valve; a position demand indicating a desired position of the turbine valve; a first feedback indicating an actual position of the hydraulic pilot valve section; and aa second feedback indicating an actual position of the main hydraulic valve section. The system also includes a pilot valve error; a main valve error; a turbine valve error; and a pilot valve adjustment moving the hydraulic pilot valve section in response to the turbine valve error. The turbine valve error is repeatedly determined and the pilot valve adjustment repeatedly moves the hydraulic pilot valve section to minimize the turbine valve error.

公开(公告)号：US12110810B2

公开(公告)日：2024-10-08

申请号：US18158618

申请日：2023-01-24

Applicant: General Electric Company

Inventor： Kudum Shinde ,  Sesha Subramanian ,  Yashpal Patel

IPC: F01D9/06 ,  F01D17/10 ,  F01D17/14 ,  F02C6/08 ,  F02C9/18

CPC classification number: F01D9/06 ,  F01D17/105 ,  F01D17/145 ,  F02C6/08 ,  F02C9/18 ,  F05D2220/323 ,  F05D2240/14 ,  F05D2260/232 ,  F05D2260/605 ,  F05D2260/606

Abstract: A gas turbine engine includes a compressor with an inner casing and an outer casing. The inner casing defines a primary flow path for airflow through the compressor, the inner casing and the outer casing define a bleed air cavity therebetween. The inner casing at least partially defines a first bleed air channel between the primary flow path and the first bleed air cavity. The first bleed air channel is defined between a first wall and a second wall, wherein the first wall is upstream from the second wall. The first wall includes a plurality of holes in fluid communication with the primary flow path and fluidly coupled to a suction manifold. The plurality of holes is configured to energize a fluid boundary layer along the first wall.

公开(公告)号：US12065937B1

公开(公告)日：2024-08-20

申请号：US18394669

申请日：2023-12-22

Applicant: RTX Corporation

Inventor： Michael G. McCaffrey ,  Nathan L. Messersmith

IPC: F01D17/14 ,  B64D27/10 ,  B64D33/04 ,  F01D17/16

CPC classification number: F01D17/14 ,  B64D27/10 ,  B64D33/04 ,  F01D17/16 ,  F05D2220/323 ,  F05D2250/90

Abstract: A variable area nozzle assembly includes a fixed center plug, a fixed outer nozzle, and an inner nozzle. The fixed center plug includes a plug body and a protrusion. The fixed outer nozzle extends about the fixed center plug. The inner nozzle extends about the fixed center plug. The inner nozzle is disposed between the fixed center plug and the fixed outer nozzle. The inner nozzle forms a primary duct between the inner nozzle and the fixed outer nozzle. The primary duct includes an exit plane. The inner nozzle body forms a secondary duct and a gap. The gap is a nozzle outlet of the secondary duct. The gap includes a gap inlet and a gap outlet. The gap inlet is disposed upstream of the protrusion. The gap outlet is disposed downstream of the protrusion. The inner nozzle body is translatable between a first position and a second position. In the first position, the primary duct has a first area at the exit plane and the inner nozzle body is disposed at the protrusion. In the second position, the primary duct has a second area at the exit plane and the inner nozzle body is spaced from the protrusion.

公开(公告)号：US20240133312A1

公开(公告)日：2024-04-25

申请号：US18048611

申请日：2022-10-20

Applicant: Rolls-Royce North American Technologies Inc.

Inventor： Timothy Unton ,  Andrew Eifert ,  Michael Moser

IPC: F01D17/14 ,  F01D9/04

CPC classification number: F01D17/14 ,  F01D9/041

Abstract: A vane assembly includes vanes, an actuator assembly, and a controller. The vanes are configured to rotate about their pitch axes. The actuator assembly includes an annular ring arranged radially outward of the vanes and coupled to the vanes, a magnet arranged on the annular ring, and a stator arranged adjacent the magnet. The ring is configured to rotate the vanes about the pitch axes in response to rotation of the ring about the central axis and the stator is configured to selectively rotate the magnet and annular ring about the central axis. The controller controls movement of the ring via the stator and magnets in response to at least one of (i) at least one operating condition of the gas turbine engine, or (ii) at least one operating parameter of the at least one first vane.

公开(公告)号：US11952943B2

公开(公告)日：2024-04-09

申请号：US18213823

申请日：2023-06-24

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Karan Anand ,  Hong Yu

IPC: F02C9/20 ,  F01D17/14 ,  F02C3/04 ,  F02C7/042 ,  F02C9/54

CPC classification number: F02C7/042 ,  F01D17/141 ,  F02C3/04 ,  F02C9/20 ,  F02C9/54

Abstract: Assemblies and methods for directing a flow of air through a compressor section of a gas turbine engine are disclosed. A method includes receiving the flow of air over a strut extending radially across a substantially annular gas path of the gas turbine engine, and at least partially confining and modifying a strut wake generated in the flow of air by the strut using one or more variable orientation guide vanes.

公开(公告)号：US20240076991A1

公开(公告)日：2024-03-07

申请号：US18505595

申请日：2023-11-09

Applicant: Rolls-Royce North American Technologies, Inc.

Inventor： Ryan C. Humes

IPC: F01D9/02 ,  F01D17/14 ,  F23R3/00

CPC classification number: F01D9/023 ,  F01D17/145 ,  F23R3/002 ,  F05D2240/35 ,  F05D2260/232 ,  F05D2260/60 ,  F23R2900/03043

Abstract: A gas turbine engine comprises a turbine, a combustor fluidly coupled to the turbine, and a cooling air system. The turbine includes including a turbine rotor having a shaft mounted for rotation about an axis of the gas turbine engine and a set of turbine blades coupled to the turbine rotor for rotation therewith. The combustor includes an outer combustor case and an inner combustor case that cooperate to define a combustion chamber. The cooling air system is configured to cool the turbine using air form the combustion chamber of the combustor.

公开(公告)号：US11835000B2

公开(公告)日：2023-12-05

申请号：US14972289

申请日：2015-12-17

Applicant: United Technologies Corporation

Inventor： Victor Pascu ,  Anthony C. Jones

IPC: F02C9/00 ,  F02C9/18 ,  F01D17/14 ,  F02C6/08

CPC classification number: F02C9/18 ,  F01D17/145 ,  F02C6/08 ,  F05D2220/323 ,  F05D2240/128 ,  F05D2240/35 ,  F05D2260/232 ,  F05D2270/101

Abstract: Methods and systems for a gas turbine engine comprising a modulated bleed valve are provided. The gas turbine engine may comprise a turbine nozzle coupled to a controller, a modulated bleed valve in communication with the controller, and a tangible, non-transitory memory providing instructions to the controller to perform operations. The operations may include receiving parameter values from the parameter sensor at various times, determining desired bleed airflows to flow through the modulated bleed valve at various times, and/or commanding the modulated bleed valve to assume an open configuration or a closed configuration at various times. The modulated bleed valve may be configured to allow bleed airflow to bypass a nozzle choke area of the turbine nozzle and join a nozzle airflow.