公开(公告)号：US10823001B2

公开(公告)日：2020-11-03

申请号：US15710146

申请日：2017-09-20

Applicant: General Electric Company

Inventor： Peeyush Pankaj ,  Shashank Suresh Puranik ,  Darek Tomasz Zatorski ,  Christopher Charles Glynn ,  Richard Schmidt ,  Bhaskar Nanda Mondal ,  Ramana Reddy Kollam

IPC: F01D25/16 ,  F01D5/30 ,  F02C3/04 ,  F02K3/04 ,  F02C3/067 ,  F02C7/06 ,  F02C3/107 ,  F02C3/113 ,  F02C7/36

Abstract: A turbomachine includes a spool and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The turbomachine also includes a bearing assembly substantially completely supporting rotation of the turbine, the bearing assembly including a total of four bearings, each of the four bearings aligned with, or positioned aft of, the turbine center frame.

公开(公告)号：US20200063606A1

公开(公告)日：2020-02-27

申请号：US16108732

申请日：2018-08-22

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Randy M. Vondrell ,  Darek Tomasz Zatorski ,  Christopher Charles Glynn

IPC: F01D25/28 ,  B64D27/10 ,  F01D15/10

Abstract: A method is provided for maintaining a gas turbine engine installed on an aircraft, the gas turbine engine including an electric machine mounted at least partially inward of a core air flowpath of the gas turbine engine. The method includes removing a rotor mount connecting a rotor of the electric machine to a rotary component of the gas turbine engine; removing a stator mount connecting a stator of the electric machine to a stationary component of the gas turbine engine; and removing in situ the electric machine.

公开(公告)号：US10480322B2

公开(公告)日：2019-11-19

申请号：US15870313

申请日：2018-01-12

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Arnab Sen ,  Jeffrey Douglas Rambo ,  Rajesh Kumar ,  Bhaskar Nanda Mondal ,  Alan Roy Stuart ,  Robert Proctor ,  Christopher Charles Glynn

IPC: F01D5/08 ,  F01D1/24 ,  F02K3/072 ,  F01D11/00 ,  F02C7/18

Abstract: An apparatus and method for cooling a portion of a turbine engine comprising an outer casing defining an axial centerline, a turbine section through which a flow of combustion gasses flows in a forward to aft direction, an outer drum located between the outer casing and the turbine section defining an annular cavity therebetween. A set of seals extends between the outer casing and outer drum to define at least one cooled cavity.

公开(公告)号：US10415897B2

公开(公告)日：2019-09-17

申请号：US15037432

申请日：2014-11-17

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Thomas Kupiszewski ,  Mehdi Milani Baladi ,  John Andrew Kemme ,  Christopher Charles Glynn ,  Steven Douglas Johnson ,  Michael Jay Epstein

IPC: F28F7/02 ,  F28F1/40 ,  F28F19/02 ,  F28F21/08 ,  F28F1/06 ,  F28F13/12 ,  F28D21/00

Abstract: A cross-flow heat exchanger for gas turbine engines which may be utilized to transfer heat from one fluid flow to a second independent fluid flow wherein one of the fluid flows has a high differential inlet pressure and temperature. The heat exchanger has robust construction to inhibit mixing of the fluid flows during a single burst duct event.

公开(公告)号：US20190085720A1

公开(公告)日：2019-03-21

申请号：US15710138

申请日：2017-09-20

Applicant: General Electric Company

Inventor： Peeyush Pankaj ,  Shashank Suresh Puranik ,  Darek Tomasz Zatorski ,  Christopher Charles Glynn ,  Richard Schmidt

IPC: F01D25/16 ,  F01D5/30 ,  F02C7/36 ,  F02C3/04 ,  F02K3/04

CPC classification number: F01D25/16 ,  F01D5/30 ,  F01D25/164 ,  F02C3/04 ,  F02C3/067 ,  F02C7/06 ,  F02C7/32 ,  F02C7/36 ,  F02K3/04 ,  F05D2240/24 ,  F05D2240/40 ,  F05D2240/50 ,  F05D2260/4031

Abstract: A turbomachine includes a spool and a turbine section. The turbine section includes a turbine center frame and a turbine, with the turbine including a first plurality of turbine rotor blades and a second plurality of turbine rotor blades. The first plurality of turbine rotor blades and second plurality of turbine rotor blades are alternatingly spaced along the axial direction. The turbomachine also includes a gearbox aligned with, or positioned aft of, a midpoint of the turbine. The gearbox includes a first gear coupled to the first plurality of rotor blades, a second gear coupled to the second plurality of rotor blades, and a third gear coupled to the turbine center frame. The turbomachine also includes a support member, the first plurality of turbine rotor blades coupled to the spool through the support member, the support member extending aft of the gearbox.

公开(公告)号：US10914194B2

公开(公告)日：2021-02-09

申请号：US15710176

申请日：2017-09-20

Applicant: General Electric Company

Inventor： Peeyush Pankaj ,  Shashank Suresh Puranik ,  Darek Tomasz Zatorski ,  Christopher Charles Glynn ,  Richard Schmidt ,  Bhaskar Nanda Mondal

IPC: F01D25/16 ,  F01D5/30 ,  F02C3/04 ,  F02K3/04 ,  F01D5/03 ,  F02C7/06 ,  F02C3/067 ,  F01D1/26 ,  F02C7/36

Abstract: A turbomachine includes a spool and a turbine section including a turbine rear frame, a turbine, and a support member. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The support member extends between the first plurality of turbine rotor blades and the spool and couples the first plurality of turbine rotor blades to the spool. The turbomachine also includes a bearing assembly including a bearing, the bearing rotatably supporting the support member and supported by the turbine rear frame, the bearing spaced apart from the spool along the radial direction.

公开(公告)号：US20200308989A1

公开(公告)日：2020-10-01

申请号：US16901568

申请日：2020-06-15

Applicant: General Electric Company

Inventor： Jared Peter Buhler ,  Christopher Charles Glynn ,  Corey Bourassa ,  Monty Lee Shelton ,  Robert Francis Manning ,  Victor Hugo Silva Correia

IPC: F01D25/32 ,  B01D46/24 ,  B01D45/12 ,  B01D46/42 ,  F01D25/12 ,  F01D9/06 ,  B01D45/08 ,  B01D45/16

Abstract: An assembly for removing particles from a fluid stream includes a first particle remover having a main flow outlet emitting a first reduced-particle stream and a scavenge flow outlet emitting a particle-laden stream, as well as a second particle remover fluidly coupled to the scavenge flow outlet and emitting a second reduced-particle stream.

公开(公告)号：US10781717B2

公开(公告)日：2020-09-22

申请号：US15710191

申请日：2017-09-20

Applicant: General Electric Company

Inventor： Peeyush Pankaj ,  Shashank Suresh Puranik ,  Darek Tomasz Zatorski ,  Christopher Charles Glynn ,  Richard Schmidt

IPC: F01D25/16 ,  F01D5/30 ,  F02C3/04 ,  F02K3/04 ,  F02C7/36 ,  F02K3/072 ,  F02C3/067

Abstract: A turbomachine includes a turbine frame and a turbine, the turbine including a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The turbomachine also includes a first support member assembly including a first support member supporting the first plurality of turbine rotor blades; a second support member assembly including a second support member supporting the second plurality of turbine rotor blades; a frame support member assembly including a frame support member coupled to and extending from the turbine frame; and a bearing assembly including a first bearing and a second bearing. The first bearing is positioned between the first support member and the second support member, and the second bearing is positioned between the frame support member and one of the first support member or the second support member.

公开(公告)号：US10738617B2

公开(公告)日：2020-08-11

申请号：US15710123

申请日：2017-09-20

Applicant: General Electric Company

Inventor： Peeyush Pankaj ,  Shashank Suresh Puranik ,  Darek Tomasz Zatorski ,  Christopher Charles Glynn ,  Richard Schmidt

IPC: F01D5/03 ,  F01D1/26 ,  F01D25/16 ,  F02C7/36 ,  F02C3/067

Abstract: A turbomachine includes a turbine section including a turbine center frame and a turbine, the turbine including a plurality of low-speed turbine rotor blades and a plurality of high-speed turbine rotor blades alternatingly spaced along the axial direction. The plurality of low-speed turbine rotor blades each extend between a radial inner end and a radial outer end. At least two of the plurality of low-speed turbine rotor blades are spaced from one another along the axial direction and coupled to one another at the radial outer ends. The turbomachine also includes a gearbox aligned with, or positioned forward of, a midpoint of the turbine. The gearbox includes a first gear coupled to the plurality of low-speed turbine rotor blades, a second gear coupled to the plurality of high-speed turbine rotor blades, and a third gear coupled to the turbine center frame.

公开(公告)号：US20200088037A1

公开(公告)日：2020-03-19

申请号：US16675918

申请日：2019-11-06

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Arnab Sen ,  Jeffrey Douglas Rambo ,  Rajesh Kumar ,  Bhaskar Nanda Mondal ,  Alan Roy Stuart ,  Robert Proctor ,  Christopher Charles Glynn

IPC: F01D5/08 ,  F01D25/14 ,  F02C7/12 ,  F01D11/00 ,  F01D1/26 ,  F01D1/24 ,  F02K3/072 ,  F02C7/18

Abstract: An apparatus for a turbine engine comprising an outer casing, an engine core provided within outer casing and having a at least one set of blades, and through which gasses flow in a forward to aft direction, an outer drum located within the outer casing to define an annular cavity. A set of seals extending between the first surface and the second surface to define at least one cooled cavity within the annular cavity.