公开(公告)号：US20240352876A1

公开(公告)日：2024-10-24

申请号：US18685562

申请日：2022-08-23

Applicant: Nuovo Pignone Tecnologie - S.r.l.

Inventor： Vanessa MARIOTTI

IPC: F01K7/38 ,  F01D17/14 ,  F01K7/34

CPC classification number: F01K7/38 ,  F01D17/145 ,  F01K7/345 ,  F05D2220/31 ,  F05D2240/12 ,  F05D2260/60

Abstract: A balanced grid valve for steam extraction from a multi-stage steam turbine comprising a first balancing chamber and a second balancing chamber which are configured to receive steam at high pressure through at least one duct. The balancing chambers are preferably in the form of annular grooves and are arranged at two different radial distances from the axis of the valve in order to reduce mechanical distortion of the valve.

公开(公告)号：US20240280050A1

公开(公告)日：2024-08-22

申请号：US18171092

申请日：2023-02-17

Applicant: Raytheon Technologies Corporation

Inventor： Marc J. Muldoon ,  William K. Ackermann ,  Anthony R. Bifulco

IPC: F02C6/08 ,  F01D9/02

CPC classification number: F02C6/08 ,  F01D9/02 ,  F05D2220/323 ,  F05D2240/126 ,  F05D2260/60

Abstract: A gas turbine engine includes a compressor section having a downstream most location and more upstream locations. A compressor housing surrounds the compressor rotors. A combustor is downstream of the compressor and a turbine section is downstream of the combustor. At least one bleed inlet passage bleeds air compressed from the compressor section, and delivers the air for use on an associated aircraft. A baffle plate is intermediate the at least one bleed inlet passage and a bleed exit port from the gas turbine engine. The baffle plate has a plurality of holes for allowing the air to flow from the bleed inlet passage to the bleed exit port, with an area of the holes increasing from a location adjacent the at least one bleed inlet passage and in a circumferential direction away from the at least one bleed inlet passage. An aircraft air supply system and an aircraft are also disclosed.

公开(公告)号：US20240247611A1

公开(公告)日：2024-07-25

申请号：US18158690

申请日：2023-01-24

Applicant: General Electric Company

Inventor： Trevor H. Wood ,  Michael J. McMahon

IPC: F02C7/042 ,  F02C7/057

CPC classification number: F02C7/042 ,  F02C7/057 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2260/60 ,  F05D2260/96

Abstract: A turboprop engine includes a main nacelle body, a rotatable hub provided on the main nacelle body, a plurality of propellers connected to the rotatable hub, and a nacelle extension coupled to the main nacelle body, the nacelle extension including at least one wall defining an air intake inlet. The air intake inlet is movable in an airflow axis with respect to a trailing edge of a propeller in the plurality of propellers to vary a distance between the air intake inlet and the trailing edge of the propeller during various phases of operation of the turboprop engine.

公开(公告)号：US20240159247A1

公开(公告)日：2024-05-16

申请号：US18197429

申请日：2023-05-15

Applicant: Raytheon Technologies Corporation

Inventor： Michael M. JOLY ,  Joseph KATZ

IPC: F04D29/52 ,  F04D27/02

CPC classification number: F04D29/526 ,  F04D27/0238 ,  F05D2240/14 ,  F05D2250/75 ,  F05D2260/60

Abstract: Compressor sections of gas turbine engines include a casing, a rotor arranged within with casing, the rotor having a plurality of blades that are rotatable relative to the casing, and a casing treatment applied to the casing. The casing treatment includes a plurality of covered channels each having an inlet and an outlet and a partially covered cavity defined between the inlet and the outlet in an axial direction and between a cover wall and a casing wall in a radial direction relative to an axis through the casing. A core flow through the casing is in a core flow direction and a recirculation flow through the plurality of covered channels is in a recirculation flow direction, the recirculation flow direction being counter to the core flow direction, and the inlet is at a position downstream relative to the outlet in the core flow direction.

公开(公告)号：US11920515B2

公开(公告)日：2024-03-05

申请号：US17744379

申请日：2022-05-13

Applicant: Raytheon Technologies Corporation

Inventor： Abbas A. Alahyari

IPC: F02C7/141

CPC classification number: F02C7/141 ,  F05D2220/323 ,  F05D2220/60 ,  F05D2260/213 ,  F05D2260/2214 ,  F05D2260/60

Abstract: A propulsion system for an aircraft includes a hydrogen fuel system suppling hydrogen fuel to the combustor through a fuel flow path. A condenser extracts water from a high energy gas flow. The condenser includes a plurality of rotating passages that are disposed within a collector. The passages are configured to rotate about a condenser axis to generate a transverse pressure gradient to direct water out of the high energy gas flow toward the collector.

公开(公告)号：US11920481B2

公开(公告)日：2024-03-05

申请号：US17785217

申请日：2020-12-18

Applicant: SAFRAN AERO BOOSTERS SA

Inventor： Cédric Carl Nathan Cracco

IPC: F01D17/16 ,  F02C9/20 ,  F01D9/04 ,  F01D9/06 ,  F01D25/16 ,  F04D29/54 ,  F04D29/56

CPC classification number: F01D17/16 ,  F02C9/20 ,  F01D9/041 ,  F01D9/065 ,  F01D17/162 ,  F01D25/162 ,  F04D29/544 ,  F04D29/563 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2260/60

Abstract: A turbomachine compressor module, comprising an annular array of structural arms defining inter-arm spaces between two circumferentially adjacent arms; and an annular array of stator vanes with variable orientation about a respective axis (A) and disposed at least partially within the inter-arm spaces. The arms are provided with flaps pivotable about a respective axis (B). Also, a turbomachine provided with such a module and a row of rotor blades directly downstream of the module.

公开(公告)号：US20240068404A1

公开(公告)日：2024-02-29

申请号：US17896522

申请日：2022-08-26

Applicant: Hamilton Sundstrand Corporation

Inventor： Brandon P. Williams ,  Jason A. Ryon ,  Murtuza Lokhandwalla ,  Todd Haugsjaahabink ,  Charles E. Reuter

IPC: F02C7/232 ,  F02C7/22 ,  F16K31/06 ,  F16K31/08

CPC classification number: F02C7/232 ,  F02C7/222 ,  F16K31/0613 ,  F16K31/0679 ,  F16K31/082 ,  F05D2260/60

Abstract: A system includes an injector having a scheduling valve assembly and a nozzle in fluid communication with the valve assembly. The scheduling valve assembly is configured for regulation of flow from an inlet of the injector to the nozzle. An electromagnetic device is operatively connected to a hydromechanical valve spool of the valve assembly to selectively adjust position of the valve spool in the valve assembly.

公开(公告)号：US11885242B2

公开(公告)日：2024-01-30

申请号：US17662143

申请日：2022-05-05

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Hervé Turcotte ,  Kenneth Parkman ,  Oleg Morenko ,  Nicholas Guglielmin ,  Gavin Kisun ,  Ryan Miskie

IPC: F01D9/06 ,  F01D25/24 ,  F01D25/16

CPC classification number: F01D9/065 ,  F01D25/162 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/53 ,  F05D2260/60

Abstract: An aircraft engine has: a compressor section having a compressor rotor rotatable about a central axis; a diffuser downstream of the compressor rotor, the diffuser including a diffuser ring extending circumferentially around the central axis; a bearing housing secured to the diffuser ring, the bearing housing contained within a volume located radially inwardly of the diffuser ring; and an air manifold secured to the diffuser ring, the air manifold defining inlets in fluid flow communication with the compressor section and an outlet in fluid flow communication with the volume.

公开(公告)号：US11873737B1

公开(公告)日：2024-01-16

申请号：US17871582

申请日：2022-07-22

Applicant: Pratt & Whitney Canada Corp.

Inventor： Tahereh Mirmohammadi Ghoojdi

IPC: F01D9/02 ,  F01D5/14 ,  F04D29/68 ,  F01D25/14 ,  F04D27/02 ,  F04D29/18 ,  F01D1/02

CPC classification number: F01D9/02 ,  F01D1/023 ,  F01D5/143 ,  F01D5/145 ,  F01D25/14 ,  F04D27/023 ,  F04D27/0215 ,  F04D29/18 ,  F04D29/68 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2260/60

Abstract: A system is provided for a gas turbine engine. This gas turbine engine system includes a flowpath wall and a deflector. The flowpath wall includes a surface and an opening to a blind aperture. The surface forms a peripheral boundary of an internal engine flowpath. The opening is disposed in the surface. The blind aperture extends vertically into the flowpath wall from the opening. The deflector projects vertically out from the flowpath wall into the internal engine flowpath. The deflector is configured to deflect gas flowing within the internal engine flowpath over the opening.

公开(公告)号：US20230358145A1

公开(公告)日：2023-11-09

申请号：US17662143

申请日：2022-05-05

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Hervé TURCOTTE ,  Kenneth PARKMAN ,  Oleg MORENKO ,  Nicholas GUGLIELMIN ,  Gavin KISUN ,  Ryan MISKIE

IPC: F01D9/06 ,  F01D25/16

CPC classification number: F01D9/065 ,  F01D25/162 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/53 ,  F05D2260/60

Abstract: An aircraft engine has: a compressor section having a compressor rotor rotatable about a central axis; a diffuser downstream of the compressor rotor, the diffuser including a diffuser ring extending circumferentially around the central axis; a bearing housing secured to the diffuser ring, the bearing housing contained within a volume located radially inwardly of the diffuser ring; and an air manifold secured to the diffuser ring, the air manifold defining inlets in fluid flow communication with the compressor section and an outlet in fluid flow communication with the volume.