公开(公告)号：US20240401546A1

公开(公告)日：2024-12-05

申请号：US18327629

申请日：2023-06-01

Applicant: General Electric Company

Inventor： Scott D. Hunter

IPC: F02K1/00

Abstract: A turbine engine includes a fan, a nacelle, and a thrust reverser system. The fan includes a plurality of fan blades. Each fan blade of the plurality of fan blades is rotatable about a pitch axis. The nacelle circumferentially surrounds the fan. The thrust reverser system includes a transcowl that forms a portion of the nacelle. The thrust reverser system translates the transcowl axially forward to an opened position during a reverse thrust condition and pitches the fan blades about the pitch axis to generate a reverse thrust through the turbine engine.

公开(公告)号：US20250084788A1

公开(公告)日：2025-03-13

申请号：US18463793

申请日：2023-09-08

Applicant: General Electric Company

Inventor： Brandon W. Miller ,  Andrew J. Hank ,  Scott D. Hunter ,  Geoffrey Whitener ,  Paul Pezzi ,  Jeffrey D. Clements

IPC: F02C6/08 ,  F02C3/06

Abstract: A turbine engine includes a high-pressure (HP) compressor and a bleed system. The HP compressor includes an HP compressor flowpath and a plurality of stages of HP compressor rotor blades and HP compressor stator vanes. The bleed system includes a plurality of bleed flowpaths including at least three bleed flowpaths in fluid communication with the HP compressor flowpath. The plurality of bleed flowpaths direct compressed air from the HP compressor flowpath. At least two of the bleed flowpaths are at successive stages of the plurality of stages.

公开(公告)号：US20250027427A1

公开(公告)日：2025-01-23

申请号：US18416269

申请日：2024-01-18

Applicant: General Electric Company

Inventor： Jeffrey D. Rambo ,  Brandon W. Miller ,  Arthur W. Sibbach ,  Scott D. Hunter ,  Ryan T. Roehm

IPC: F01D21/00 ,  F02C7/06 ,  F02C9/26 ,  F04C2/08 ,  F15B13/04

Abstract: A turbine engine having a longitudinal centerline axis. The turbine engine including a fan comprising a plurality of fan blades that rotate about the longitudinal centerline axis and a rotational component coupled to the fan. The turbine engine including a fluid circuit for supplying fuel or lubricant to the turbine engine and a hydraulic fan brake coupled to the fluid circuit to prevent rotation of the rotational component, thus preventing rotation of the fan. The hydraulic fan brake including a hydraulic cylinder fluidly coupled to the fluid circuit and a valve coupled to the hydraulic cylinder and having a first valve position that disengages the hydraulic fan brake to allow rotation of the rotational component and a second valve position that engages the hydraulic fan brake to prevent rotation of the rotational component.