公开(公告)号：US11867121B2

公开(公告)日：2024-01-09

申请号：US17211345

申请日：2021-03-24

Applicant: General Electric Company ,  General Electric Deutschland Holding GmbH

Inventor： Paul Hadley Vitt ,  Michael Simonetti ,  Ashish Sharma

IPC: F02C7/141 ,  F02C7/16 ,  F01D25/12

CPC classification number: F02C7/141 ,  F01D25/12 ,  F02C7/16 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2260/205 ,  F05D2260/232

Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An outlet guide vane assembly includes multiple outlet guide vanes located in an exhaust airflow path downstream of the turbine section. The multiple outlet guide vanes being spaced-apart circumferentially from each other over an angular range of about 360 degrees, and each multiple outlet guide vane defining a radial extent. At least one of the multiple outlet guide vanes includes a cold fluid passageway extending at least partially radially therethrough through which a fluid coolant flows and another of the multiple guide vanes includes a heated fluid passageway extending at least partially radially therethrough through which the fluid coolant flows and receives heat from exhaust airflow from the core airflow path.

公开(公告)号：US11519333B2

公开(公告)日：2022-12-06

申请号：US17016670

申请日：2020-09-10

Applicant: General Electric Company

Inventor： Christopher Ryan Johnson ,  Paul Hadley Vitt ,  Eric Joseph Schroeder ,  Carlos Gilberto Fernandez-Soto

IPC: F02C7/24

Abstract: Aspects of the disclosure generally relate to a turbine engine and method of operating a turbine engine having an engine core including a compressor, combustor, and turbine in axial flow arrangement, whereby a working airflow passes through the engine core from the compressor to the turbine to define a flow direction through the engine core. The method includes generating a shockwave in the working airflow that propagates in the flow direction, and at least partially attenuating the shockwave.

公开(公告)号：US20220074315A1

公开(公告)日：2022-03-10

申请号：US17526313

申请日：2021-11-15

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Paul Hadley Vitt ,  Andrew Breeze-Stringfellow

IPC: F01D11/16 ,  F01D5/22 ,  F01D25/24

Abstract: A shroud assembly for a turbine engine having a centerline axis. The shroud assembly having a shroud hanger, at least one shroud segment, and at least one biasing element extending between the two. The biasing element configured to radially bias the at least one shroud segment between an outboard position and an inboard position radially outward from the outboard position with respect to the centerline axis.

公开(公告)号：US20210079799A1

公开(公告)日：2021-03-18

申请号：US16568730

申请日：2019-09-12

Applicant: General Electric Company

Inventor： Paul Hadley Vitt ,  Wilson Frost ,  Mark Broomer

IPC: F01D9/04

Abstract: An apparatus for a nozzle assembly for a turbine engine and a method of forming the nozzle assembly are described herein. The nozzle assembly can include a set of nozzles including an inner band and an outer band, with one or more airfoils extending between the inner and outer bands. The nozzles can be coupled to adjacent nozzles at the inner and outer bands to form the nozzle assembly. A throat can be defined at the minimum cross-sectional area between adjacent airfoils in the nozzle assembly. A formed portion can be formed on either of or both of the inner or outer band at the throat.

公开(公告)号：US12228048B2

公开(公告)日：2025-02-18

申请号：US18487495

申请日：2023-10-16

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Thomas William Vandeputte ,  Paul Hadley Vitt ,  Daniel Endecott Osgood ,  Brian David Keith

IPC: F01D5/18 ,  F02C7/12

Abstract: A turbine engine includes a compressor section, a combustion section, and a turbine section, and an airfoil with an outer wall defining a pressure side and a suction side and extending between a leading edge and a trailing edge to define a mean camber line. A first thickness is defined between the pressure side and the suction side at a first location along the mean camber line.

公开(公告)号：US12071889B2

公开(公告)日：2024-08-27

申请号：US17713649

申请日：2022-04-05

Applicant: General Electric Company ,  General Electric Deutschland Holding GmbH ,  GE Avio Srl

Inventor： Paul Hadley Vitt ,  Lyle Douglas Dailey ,  Matteo Renato Usseglio ,  Andreas Peters ,  Jonathan Ong

IPC: F02C3/06 ,  F02C3/067 ,  F02C7/14 ,  F02C7/141 ,  F02C7/36

CPC classification number: F02C3/067 ,  F02C7/141 ,  F02C7/36 ,  F05D2220/60 ,  F05D2260/213 ,  F05D2260/40311

Abstract: A turbine section and an exhaust section for a gas turbine engine includes a low pressure (LP) turbine having first stage LP turbine blades that rotate in a first direction at a first speed, and final stage LP turbine blades downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed. The second speed is lower than the first speed.

公开(公告)号：US20240247614A1

公开(公告)日：2024-07-25

申请号：US18625749

申请日：2024-04-03

Applicant: General Electric Company

Inventor： Christopher Ryan Johnson ,  Paul Hadley Vitt ,  Eric Joseph Schroeder ,  Carlos Gilberto Fernandez-Soto

IPC: F02C7/24

CPC classification number: F02C7/24

Abstract: A turbine engine and method of operating includes an engine core with a compressor, a combustor, and a turbine in axial flow arrangement. A flow path extends through the engine core from the compressor to the turbine to define a flow direction for a working airflow through the engine core.

公开(公告)号：US11970979B2

公开(公告)日：2024-04-30

申请号：US17979057

申请日：2022-11-02

Applicant: General Electric Company

Inventor： Christopher Ryan Johnson ,  Paul Hadley Vitt ,  Eric Joseph Schroeder ,  Carlos Gilberto Fernandez-Soto

IPC: F02C7/24

CPC classification number: F02C7/24

Abstract: A turbine engine and method of operating includes an engine core with a compressor, a combustor, and a turbine in axial flow arrangement. A flow path extends through the engine core from the compressor to the turbine to define a flow direction for a working airflow through the engine core.

公开(公告)号：US11939880B1

公开(公告)日：2024-03-26

申请号：US17980134

申请日：2022-11-03

Applicant: General Electric Company

Inventor： Paul Hadley Vitt ,  Matthew Brian Surprenant ,  Brian David Keith ,  Prem Venugopal ,  Thomas William Vandeputte

IPC: F01D5/02 ,  F01D5/14

CPC classification number: F01D5/02 ,  F01D5/14 ,  F05D2220/30

Abstract: A turbine engine stage includes a plurality of airfoils extending between an inner band and an outer band. Each airfoil in the plurality of airfoils can have an outer wall defining a pressure side and a suction side, with the outer wall extending between a leading edge and a trailing edge. An intervening flow passage is defined between two adjacent airfoils in the plurality of airfoils.

公开(公告)号：US20240093644A1

公开(公告)日：2024-03-21

申请号：US17946499

申请日：2022-09-16

Applicant: General Electric Company ,  GE Avio S.r.l.

Inventor： Paul Hadley Vitt ,  Matteo Renato Usseglio ,  Brian Lewis Devendorf

IPC: F02C7/22 ,  F02C6/00 ,  F02K3/08

CPC classification number: F02C7/22 ,  F02C6/00 ,  F02K3/08

Abstract: An aircraft engine is provided. The aircraft engine includes a compressor section having a compressor. A turbine section is downstream of the compressor section. The turbine section includes a turbine having turbine blades arranged in counter rotating stages. The aircraft engine further includes one or more fluid supply lines and a fuel cell assembly fluidly coupled to the one or more fluid supply lines for receiving one or more input fluids. The fuel cell assembly is in fluid communication with the turbine section to provide one or more output products to the turbine section. The aircraft engine further includes a heat exchanger in fluid communication with the turbine downstream of the counter rotating stages of turbine blades to receive exhaust gases from the turbine. The heat exchanger is thermally coupled to the one or more fluid supply lines of the fuel cell assembly.