公开(公告)号：US20230265764A1

公开(公告)日：2023-08-24

申请号：US18297835

申请日：2023-04-10

Applicant: General Electric Company

Inventor： Steven Douglas Johnson ,  Julius John Montgomery ,  Brandon Wayne Miller ,  Robert Proctor ,  Bradley W. Fintel ,  Jeffrey Douglas Rambo

IPC: F01D11/24 ,  F01D11/18 ,  F02C7/18 ,  F02C6/08

CPC classification number: F01D11/24 ,  F01D11/18 ,  F02C7/185 ,  F02C6/08 ,  F01D25/14

Abstract: A system for controlling blade clearances within a gas turbine engine includes a rotor disk and a rotor blade coupled to the rotor disk. Additionally, the system includes an outer turbine component positioned outward of the rotor blade such that a clearance is defined between the rotor blade and the outer turbine component. Furthermore, the system includes a heat exchanger configured to receive a flow of cooling air bled from the gas turbine engine and transfer heat from the received flow of the cooling air to a flow of coolant to generate cooled cooling air. Moreover, the system includes a valve configured to control the flow of the coolant to the heat exchanger. In this respect, the cooled cooling air is supplied to at least one of the rotor disk or the rotor blade to adjust the clearance between the rotor blade and the outer turbine component.

公开(公告)号：US11674405B2

公开(公告)日：2023-06-13

申请号：US17461142

申请日：2021-08-30

Applicant: General Electric Company

Inventor： Steven Douglas Johnson ,  Neelesh Nandkumar Sarawate

IPC: F01D11/12

CPC classification number: F01D11/125 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2240/55

Abstract: An abradable insert for a gas turbine engine, the abradable insert including: a base layer; a lattice layer connected to the base layer, wherein the lattice layer comprises a series of walls that define a plurality of cells; and a sheet layer connected to the lattice layer on an opposite side on the lattice layer from the base layer, wherein the sheet layer is curved and includes a direction of concavity that points away from the base layer, wherein the lattice layer and the sheet layer are integrally formed together and are a monolithic piece of material.

公开(公告)号：US11047481B2

公开(公告)日：2021-06-29

申请号：US16296620

申请日：2019-03-08

Applicant: General Electric Company

Inventor： Rahul Anil Bidkar ,  Steven Douglas Johnson ,  Nathan Evan McCurdy Gibson

IPC: F16J15/447 ,  F01D11/08 ,  F01D11/02 ,  F01D11/00

Abstract: A seal assembly of a rotary includes a radially oriented plate that axially opposes a front and rear support plates of a stator interface. The seal assembly also includes a film-riding shoe coupled with the radially oriented plate. The shoe forms a shoe fluid bearing between the shoe and a rotating component responsive to rotation of the rotating component and pressurization of fluid in the rotary machine upstream of the stator interface. One or more of the stator interface or the film-riding shoe includes one or more ports or pathways through which higher-pressure fluid upstream of the stator housing in the rotary machine flows to form an aft axial fluid bearing between the radially oriented plate and the rear support plate of the stator interface.

公开(公告)号：US10781709B2

公开(公告)日：2020-09-22

申请号：US15865359

申请日：2018-01-09

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Arnab Sen ,  Jeffrey Douglas Rambo ,  Rajesh Kumar ,  Nathan Evan McCurdy Gibson ,  Robert Proctor ,  Bhaskar Nanda Mondal ,  Steven Douglas Johnson

IPC: F01D11/00 ,  F01D25/12

Abstract: A turbine engine includes an engine core defining a higher pressure region and a lower pressure region. A seal can fluidly separate the higher pressure region from the lower pressure region and be movably mounted to a component within the turbine engine, where a side of the seal can confront the component.

公开(公告)号：US20200040940A1

公开(公告)日：2020-02-06

申请号：US16055333

申请日：2018-08-06

Applicant: General Electric Company

Inventor： Sean Christopher Binion ,  Steven Douglas Johnson ,  David Vickery Parker ,  Stephen Joseph Waymeyer ,  Nathan Evan McCurdy Gibson

IPC: F16C32/06 ,  F01D25/16 ,  F01D25/22 ,  F02C7/06 ,  F16C17/12

Abstract: A bearing assembly including a body defining an outer surface, an inner surface, and an aft surface is generally provided. A first inlet opening is defined through the outer surface in fluid communication with a first internal passage defined by a first internal wall. The first internal passage is in fluid communication with a first outlet opening defined through the inner surface. A second inlet opening is defined through the inner surface in fluid communication with a second internal passage defined by a second internal wall. The second internal passage is in fluid communication with a second outlet opening defined through the aft surface.

公开(公告)号：US20190383219A1

公开(公告)日：2019-12-19

申请号：US16008628

申请日：2018-06-14

Applicant: General Electric Company

Inventor： Steven Douglas Johnson ,  Jeffrey Rambo

IPC: F02C9/18 ,  F02C6/08 ,  F02C7/18 ,  F02C7/32

Abstract: A gas turbine engine includes: a compressor, a combustor, and a turbine arranged in sequential flow relationship along a primary flowpath, the turbine being connected in mechanical driving relationship to the compressor, so as to define at least one engine rotor that is rotatable about a centerline axis of the engine; a secondary flowpath connected in flow communication with the primary flowpath; and an air cycle machine including an air cycle rotor carrying an at least one air cycle compressor and at least one air cycle expander, wherein: the air cycle rotor is coupled in mechanical driving relationship with the at least one engine rotor; the air cycle rotor is coupled in fluid flow communication with the secondary flowpath; and the air cycle rotor is coupled in fluid flow communication with at least one heat exchanger.

公开(公告)号：US20170298742A1

公开(公告)日：2017-10-19

申请号：US15099887

申请日：2016-04-15

Applicant: General Electric Company

Inventor： Steven Douglas Johnson

IPC: F01D5/14 ,  F01D5/20

CPC classification number: F01D5/145 ,  F01D5/20 ,  F05D2220/32 ,  F05D2240/306 ,  F05D2240/307 ,  F05D2270/17 ,  Y02T50/671 ,  Y02T50/673

Abstract: An apparatus and method of minimizing airfoil boundary layer separation utilizing at least one bleed inlet disposed on the outer wall of the airfoil, such as the suction side, having at least one channel disposed within an interior of the airfoil providing fluid communication between the bleed inlet and the tip of the airfoil. Bleed gas drawn through the bleed inlet and provided to the tip can pressurize a seal disposed at the tip. Additionally, a flow control device can be disposed within the channel to control or meter the rate at which gas is bled into the channel.