公开(公告)号：US20250146438A1

公开(公告)日：2025-05-08

申请号：US19018995

申请日：2025-01-13

Applicant: RTX Corporation

Inventor： PAUL M. LUTJEN ,  JOSE R. PAULINO ,  TRACY A. PROPHETER-HINCKLEY

IPC: F02C7/05 ,  F01D11/10

Abstract: An accessible debris separator for a gas turbine engine is provided. The accessible debris separator including a chamber formed by a entrance wall, an exit wall, an inner wall, and an outer wall; a plurality of inlet openings in the entrance wall; a plurality of outlet openings in the exit wall; and a component within the chamber, the component forcing cooling air with debris particulates entering the chamber via an inlet opening of the plurality of inlet openings to take a circuitous path thereby separating the debris particulates from the cooling air prior to the cooling air exiting the chamber via an outlet opening of the plurality of outlet openings.

公开(公告)号：US12241411B1

公开(公告)日：2025-03-04

申请号：US18458495

申请日：2023-08-30

Applicant: RTX Corporation

Inventor： Paul M Lutjen ,  Jose R Paulino ,  Tracy A Propheter-Hinckley

IPC: F02C7/052 ,  F01D11/10 ,  F02C7/05

Abstract: An accessible debris separator for a gas turbine engine is provided. The accessible debris separator including a chamber formed by a entrance wall, an exit wall, an inner wall, and an outer wall; a plurality of inlet openings in the entrance wall; a plurality of outlet openings in the exit wall; and a component within the chamber, the component forcing cooling air with debris particulates entering the chamber via an inlet opening of the plurality of inlet openings to take a circuitous path thereby separating the debris particulates from the cooling air prior to the cooling air exiting the chamber via an outlet opening of the plurality of outlet openings.

公开(公告)号：US20240410317A1

公开(公告)日：2024-12-12

申请号：US18809927

申请日：2024-08-20

Applicant: General Electric Company

Inventor： Arthur William Sibbach ,  Brandon Wayne Miller

IPC: F02C7/05 ,  F02C6/20 ,  F02C7/04 ,  F02K3/00

Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan; an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle; and a means for directing incoming objects towards an outer portion of the turbofan engine in communication with the inlet pre-swirl feature.

公开(公告)号：US20240271564A1

公开(公告)日：2024-08-15

申请号：US18643733

申请日：2024-04-23

Applicant: Textron Innovations Inc.

Inventor： Daniel John Simpson ,  Tim Nobel ,  Mitchell Jay Griffith ,  Henry Roger Bredenkamp, Jr. ,  David H. Loe ,  Paul Park

IPC: F02C7/057 ,  B64D29/00 ,  B64D33/02 ,  F02C7/05

CPC classification number: F02C7/057 ,  B64D29/00 ,  B64D33/02 ,  F02C7/05 ,  B64D2033/0246

Abstract: A rotatable nacelle includes an engine inlet configured to receive air and an inlet air management system (IAMS). The IAMS includes a primary inlet configured to selectively allow air to flow into a duct associated with the engine air inlet via the primary inlet and a secondary inlet configured to selectively allow air to flow into the duct associated with the engine air inlet via the secondary inlet. The secondary inlet is configured to receive an air filter.

公开(公告)号：US20240253801A1

公开(公告)日：2024-08-01

申请号：US18102508

申请日：2023-01-27

Applicant: Rohr, Inc.

Inventor： Johann Schrell ,  Brian A. Sherman

IPC: B64D33/02 ,  F02C7/05

CPC classification number: B64D33/02 ,  F02C7/05 ,  B64D2033/022

Abstract: An air inlet for an aircraft propulsion system nacelle includes an outer skin, an inner skin, a lip skin, and a forward bulkhead. The lip skin extends between and to an outer end and an inner end. The outer end is disposed at the outer skin. The inner end is disposed at the inner skin. The forward bulkhead includes a first bulkhead portion and a second bulkhead portion. The first bulkhead portion and the second bulkhead portion are mounted to the outer skin. The first bulkhead portion and the second bulkhead portion are mounted to the inner skin. The first bulkhead portion includes a rigid body material and the second bulkhead portion includes a flexible body material.

公开(公告)号：US11988142B2

公开(公告)日：2024-05-21

申请号：US18112296

申请日：2023-02-21

Applicant: General Electric Company

Inventor： Laxmikant Merchant ,  Dinesh Venugopal Setty ,  Mukesh Niddodi Kamath ,  Prithviraj Pandian

IPC: F02C7/05

CPC classification number: F02C7/05 ,  F05D2240/35 ,  F05D2250/221 ,  F05D2260/607

Abstract: An inlet filter housing includes a plurality of components that collectively form a complete filtering and conditioning system for filtering and conditioning a fluid along a housing flow path. Each component is fitted within an external structure of an International Organization of Standards (ISO) shipping container, which provides a rectangular cuboid enclosure. Each component includes operative structure of at least one of: a) only a portion of an axial extent of the filtering and conditioning system, and b) only a portion of a lateral cross-sectional area of the housing flow path.

公开(公告)号：US11702982B2

公开(公告)日：2023-07-18

申请号：US16663075

申请日：2019-10-24

Applicant: The Boeing Company

Inventor： Daniel F. Gelzer ,  Jennifer Bender Zielinski

IPC: F02C7/05 ,  F01D21/04 ,  F01D25/24 ,  B23P15/00 ,  B64D29/06 ,  B64D29/00 ,  B23P6/00 ,  B64D33/02

CPC classification number: F02C7/05 ,  B23P6/005 ,  B23P15/008 ,  B64D29/00 ,  B64D29/06 ,  F01D21/045 ,  F01D25/24 ,  B23P2700/01 ,  B64D2033/022 ,  F05D2230/80 ,  F05D2240/14 ,  F05D2250/283 ,  Y10T29/4932

Abstract: A barrier device is provided for an inlet cowl for an aircraft engine including an inner barrel circumferentially surrounding an opening in the inlet cowl formed along an axis of rotation of the aircraft engine, through which air passes to the aircraft engine, the inner barrel including a face sheet disposed on a radially inward side of the inner barrel relative to the axis. The barrier device includes a containment doubler of the inner barrel, disposed on a radially outward side of the inner barrel, and a blade fragment barrier including one or more strips disposed between the containment doubler and the face sheet, so as to extend circumferentially at least partially around the opening and to occupy a radial distance between the containment doubler and the face sheet.

公开(公告)号：US20220412259A1

公开(公告)日：2022-12-29

申请号：US17358196

申请日：2021-06-25

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Martin DOBSON ,  Oleg ISKRA ,  Michael FRYER ,  Marc LAVOIE ,  Ivan SIDOROVICH PARADISO ,  Louis DURANLEAU-HENDRICKX ,  Domenico DI FLORIO

IPC: F02C7/05 ,  F02C9/18

Abstract: Methods and systems for filtering pressurized air used to control a compressor bleed valve of a gas turbine engine are provided. One method comprises receiving the pressurized air in a conduit via an inlet of the conduit, releasing a first portion of the pressurized air out of the conduit via an outlet of the conduit, releasing a second portion of the pressurized air from the conduit via a port disposed between the inlet and the outlet of the conduit, directing the second portion of the pressurized air from the port to a filter along an upward flow path, filtering the second portion of the pressurized air using the filter, and directing the second portion of the pressurized air from the filter toward the compressor bleed valve.

公开(公告)号：US20220056844A1

公开(公告)日：2022-02-24

申请号：US16997459

申请日：2020-08-19

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： John Pearson ,  Daniel Aukland ,  Yogendra Sheoran

IPC: F02C7/05 ,  B01D45/16

Abstract: A particle separator associated with a compressor section of a gas turbine engine includes a duct that defines a fluid flow path from a diffuser to a deswirl section. The duct includes a curved portion between an outlet of the diffuser and an inlet of the deswirl section. The curved portion is configured to have at least one low velocity region and a high velocity region. The particle separator includes at least one cluster of inlet passages defined at the at least one low velocity region. The particle separator includes a scavenge plenum coupled to the duct and in fluid communication with the at least one cluster of inlet passages. At least one outlet slot is defined through the duct downstream of the at least one cluster of inlet passages in the high velocity region and is in fluid communication with the scavenge plenum.

公开(公告)号：US11181044B2

公开(公告)日：2021-11-23

申请号：US17020491

申请日：2020-09-14

Applicant: Michael J. Kline

Inventor： Michael J. Kline

IPC: B01D39/00 ,  F02C7/055 ,  B64D29/00 ,  F02C7/05 ,  B29C45/00 ,  C08F120/56 ,  C04B41/52 ,  F01D9/02 ,  C08F8/12 ,  F01D9/04 ,  B29L31/30

Abstract: An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.