公开(公告)号：US10697372B2

公开(公告)日：2020-06-30

申请号：US15479750

申请日：2017-04-05

Applicant: General Electric Company

Inventor： Jeremy Kevin Payne ,  John Wilbur Acree ,  Anthony James Bailey ,  Satyambabu Kalyani ,  Thomas Alan Wall ,  Michael Alan Zupancic ,  Jonathan Russell Ratzlaff ,  Anthony Paul Greenwood ,  Kevin William Caldwell ,  Christophe Jude Day

IPC: F02C7/00 ,  F02C7/20 ,  F02C3/04 ,  F02C7/18 ,  F02C6/08

Abstract: An apparatus and method for a turbine engine having an engine core. A casing can contain a compressor section, a combustor section and a turbine section in axial flow arrangement. An air conduit can extend at least partially between the compressor section and the turbine section. A compliant interface can include a nut and a biasing device mount the air conduit to the casing.

公开(公告)号：US10450951B2

公开(公告)日：2019-10-22

申请号：US14925190

申请日：2015-10-28

Applicant: General Electric Company

Inventor： John Joseph Rahaim ,  Corey Bourassa ,  Jared Peter Buhler ,  Jonathan Russell Ratzlaff

IPC: F02C3/13 ,  F02C3/34

Abstract: A gas turbine engine comprising a cyclonic separator provides fluid communication between the compressor section and the turbine section. The cyclonic separator comprises an annular volume receiving a flow of cooling fluid from an inlet and dividing the airflow into a cleaner air outlet and a scavenge outlet. The flow of cooling fluid is provided to the cyclonic separator in a direction tangential to the annular volume such that a cyclonic flow of cooling fluid moves within the annular volume centrifugally separating particles entrained within the airflow to the radial outer area of the annular volume for removal through the scavenge outlet and providing a cleaner airflow to the cleaner air outlet.

公开(公告)号：US10443422B2

公开(公告)日：2019-10-15

申请号：US15040603

申请日：2016-02-10

Applicant: General Electric Company

Inventor： Jonathan Russell Ratzlaff ,  Michael Thomas Hogan ,  Julius John Montgomery

IPC: F01D11/04 ,  F01D5/02 ,  F01D9/04 ,  F01D11/00

Abstract: An apparatus relating to a rim seal for gas turbine engine comprising a wing extending into a buffer cavity with at least one set of protuberances including a first protuberance extending into the buffer cavity and a second protuberance extending from the wing into the buffer cavity, with the first and second protuberances being axially spaced from each other.

公开(公告)号：US10240461B2

公开(公告)日：2019-03-26

申请号：US14990885

申请日：2016-01-08

Applicant: General Electric Company

Inventor： Jonathan Russell Ratzlaff ,  Julius John Montgomery ,  Michael Thomas Hogan

IPC: F01D5/08 ,  F01D11/00 ,  F01D11/04 ,  F01D9/04 ,  F01D25/12

Abstract: A stator rim structure for a gas turbine engine comprises a stator having an end wall and a discourager defining a channel therebetween. The end wall is adjacent to a hot gas flow and the discourager is adjacent to a purge flow. A rotor has an angel wing extending into the channel. At least one supply passage is disposed within the stator and extends through the discourager and at least one aperture fluidly couples the supply passage with the channel. A flow of cooling air is fed from the supply passage into the aperture and into the channel to form a fluidic dam discouraging ingestion of the hot gas flow.

公开(公告)号：US20180291812A1

公开(公告)日：2018-10-11

申请号：US15479750

申请日：2017-04-05

Applicant: General Electric Company

Inventor： Jeremy Kevin Payne ,  John Wilbur Acree ,  Anthony James Bailey ,  Satyambabu Kalyani ,  Thomas Alan Wall ,  Michael Alan Zupancic ,  Jonathan Russell Ratzlaff ,  Anthony Paul Greenwood ,  Kevin William Caldwell ,  Christophe Jude Day

IPC: F02C7/20 ,  F02C3/04

Abstract: An apparatus and method for a turbine engine having an engine core. A casing can contain a compressor section, a combustor section and a turbine section in axial flow arrangement. An air conduit can extend at least partially between the compressor section and the turbine section. A compliant interface can include a nut and a biasing device mount the air conduit to the casing.

公开(公告)号：US20170226882A1

公开(公告)日：2017-08-10

申请号：US15016645

申请日：2016-02-05

Applicant: General Electric Company

Inventor： Jonathan Russell Ratzlaff ,  Ronald Scott Bunker

IPC: F01D11/02 ,  F01D5/08

CPC classification number: F01D11/02 ,  F01D5/081 ,  F01D5/082 ,  F01D11/001 ,  F01D11/04 ,  F05D2220/32 ,  F05D2240/10 ,  F05D2240/24 ,  F05D2250/184 ,  F05D2260/20 ,  Y02T50/676

Abstract: An apparatus and method of a gas turbine engine comprising a rotor having at least one disk with a rotor defining an axial face and a stator having at least one ring with a stator axial face confronting the rotor axial face, with terminal portions of the axial faces forming a fluid outlet there between. A recess formed in one of the axial faces defines a buffer cavity into which a wing extends from the other of the axial faces and having a surface confronting the fluid outlet. A flow reverser is further provided within at least one of the surface or the terminal portion of the other of the axial faces.

公开(公告)号：US11918943B2

公开(公告)日：2024-03-05

申请号：US17993082

申请日：2022-11-23

Applicant: General Electric Company

Inventor： Timothy Deryck Stone ,  Gregory Michael Laskowski ,  Robert Proctor ,  Curtis Stover ,  Robert Francis Manning ,  Victor Hugo Silva Correia ,  Jared Peter Buhler ,  Robert Carl Murray ,  Corey Bourassa ,  Byron Andrew Pritchard, Jr. ,  Jonathan Russell Ratzlaff

IPC: B01D45/16 ,  B04C3/00 ,  B04C3/06 ,  F01D5/18 ,  F01D9/06 ,  F02C6/08 ,  F02C7/052 ,  F02C7/18 ,  F02K3/04

CPC classification number: B01D45/16 ,  B04C3/06 ,  F01D5/189 ,  F01D9/065 ,  F02C6/08 ,  F02C7/052 ,  F02C7/18 ,  B04C2003/003 ,  B04C2003/006 ,  F02K3/04 ,  F05D2260/607 ,  Y02T50/60

Abstract: A turbine engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft that couples a portion of the turbine section and a portion of the compressor section. A bypass conduit couples the compressor section to the turbine section while bypassing at least the combustion section. At least one particle separator is located in the turbine engine having a separator inlet that receives a bypass stream, a separator outlet that receives a reduced-particle stream flows, and a particle outlet that receives a concentrated-particle stream comprising separated particles. A conduit, fluidly coupled to the particle outlet, extends through an interior of at least one stationary vane.

公开(公告)号：US11788469B2

公开(公告)日：2023-10-17

申请号：US17098998

申请日：2020-11-16

Applicant: General Electric Company

Inventor： Steven Douglas Johnson ,  Jonathan Russell Ratzlaff

IPC: F02C7/18 ,  F02C7/14 ,  F01D25/12 ,  F02C9/18 ,  F02C6/08 ,  B64D33/02

CPC classification number: F02C7/18 ,  F02C7/14 ,  B64D2033/0233 ,  F01D25/12 ,  F02C6/08 ,  F02C7/185 ,  F02C9/18 ,  F05D2260/20 ,  F05D2260/213

Abstract: A thermal management system for a gas turbine engine includes a heat exchanger including first and second sides, with the first side in contact with flow path air flowing through a flow path of the engine. Furthermore, the system includes a housing positioned relative to the heat exchanger such that the housing and the second side of the heat exchanger define a plenum configured to receive bleed air from the engine. Moreover, the system includes and at least one of a plurality of fins extending outward from the second side of the heat exchanger in a radial direction into the plenum and along the second surface of the heat exchanger in the circumferential direction or an impingement plate defining a plurality of impingement apertures, with each impingement aperture configured to direct an impingement jet of the bleed air within the plenum onto the second side of the heat exchanger.

公开(公告)号：US11541340B2

公开(公告)日：2023-01-03

申请号：US17325650

申请日：2021-05-20

Applicant: General Electric Company

Inventor： Timothy Deryck Stone ,  Gregory Michael Laskowski ,  Robert Proctor ,  Curtis Stover ,  Robert Francis Manning ,  Victor Hugo Silva Correia ,  Jared Peter Buhler ,  Robert Carl Murray ,  Corey Bourassa ,  Byron Andrew Pritchard, Jr. ,  Jonathan Russell Ratzlaff

IPC: B01D45/16 ,  F02C7/18 ,  B04C3/06 ,  B04C3/00 ,  F02C6/08 ,  F01D5/18 ,  F01D9/06 ,  F02C7/052 ,  F02K3/04

Abstract: A turbine engine having an inducer assembly. The inducer assembly includes a centrifugal separator fluidly coupled to an inducer with an inducer inlet and an inducer outlet. The centrifugal separator includes a body, an angular velocity increaser to form a concentrated-particle stream and a reduced-particle stream, a flow splitter, and an exit conduit fluidly coupled to the body to receive the reduced-particle stream and define a separator outlet.

公开(公告)号：US11306655B2

公开(公告)日：2022-04-19

申请号：US16356595

申请日：2019-03-18

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Daniel Endecott Osgood ,  Jonathan Russell Ratzlaff ,  Kirk D. Gallier

IPC: F01D25/32 ,  F01D25/12 ,  F02C7/052 ,  F02C7/18 ,  F01D9/04 ,  B01D45/16

Abstract: A component for a turbine engine includes a body having a wall at least partially defining an interior and separating a combustion air flow path from a cooling air flow path. The component also includes at least one fluid inlet supplying cooling air to the interior of the body, as well as a cyclone separator.