公开(公告)号：US20230296251A1

公开(公告)日：2023-09-21

申请号：US17812278

申请日：2022-07-13

Applicant: General Electric Company

Inventor： Karthikeyan Sampath ,  Perumallu Vukanti ,  Pradeep Naik ,  Ravindra Shankar Ganiger ,  Daniel J. Kirtley ,  Arvind Namadevan ,  Ranganatha Narasimha Chiranthan ,  Hiranya Nath

IPC: F23R3/00

CPC classification number: F23R3/007 ,  F23R2900/00012 ,  F23R2900/00017 ,  F23R2900/03043

Abstract: A combustion liner assembly includes metal liner having a hot side and a cold side, a ceramic matrix composite (CMC) liner tile configured to provide a heat shield for the metal liner, the CMC liner tile having a different thermal conductivity than the metal liner, and a connection device configured to attach the CMC liner tile to the metal liner. The connection device accommodates the different thermal conductivity of the CMC liner tile and the metal liner. The connection device is free from a radial fastener exposed to hot gases on the hot side of the metal liner, and the connection device allows radial movement and axial movement between the metal liner and the CMC liner tile.

公开(公告)号：US11525400B2

公开(公告)日：2022-12-13

申请号：US16923198

申请日：2020-07-08

Applicant: General Electric Company

Inventor： Arvind Namadevan ,  Jeffrey Douglas Rambo ,  Arnab Sen

IPC: F02C7/18 ,  F01D5/08

Abstract: An aspect of the present disclosure is directed to a system for reducing thermal gradient at a heat engine. The heat engine includes a rotor assembly with a rotor disk and a seal assembly is provided. An interfacing structure at least partially surrounds the rotor assembly at the seal assembly. The seal assembly and the interfacing structure together form a first cavity defining a first environmental condition and a second cavity defining a second environmental condition. A fluid supply manifold is connected to the rotor assembly and is extended at least partially along a radial direction from the first cavity to an outlet opening in thermal communication with the rotor disk of the rotor assembly.

公开(公告)号：US12090462B2

公开(公告)日：2024-09-17

申请号：US18054739

申请日：2022-11-11

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Nath ,  Thomas D. Woodrow ,  Scott Alan Schimmels ,  Arvind Namadevan ,  Mohan Raju ,  Subramani Adhiachari ,  Prasant Bilaiya ,  Rajesh Kumar

IPC: F16N39/00 ,  B01J19/00

CPC classification number: B01J19/0026 ,  F16N39/00 ,  F16N2210/02

Abstract: A self-cleaning conduit for a hydrocarbon fluid. The conduit includes a tube and a movable sleeve. The tube has an interior surface defining a flow passage for the hydrocarbon fluid. The movable sleeve is positioned within the flow passage to abut the interior surface and is movable along the interior surface in response to a change in an operating characteristic of the conduit to break-up deposits on the interior surface.

公开(公告)号：US20240001324A1

公开(公告)日：2024-01-04

申请号：US18054739

申请日：2022-11-11

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Nath ,  Thomas D. Woodrow ,  Scott Alan Schimmels ,  Arvind Namadevan ,  Mohan Raju ,  Subramani Adhiachari ,  Prasant Bilaiya ,  Rajesh Kumar

IPC: B01J19/00 ,  F16N39/00

CPC classification number: B01J19/0026 ,  F16N39/00 ,  F16N2210/02

Abstract: A self-cleaning conduit for a hydrocarbon fluid. The conduit includes a tube and a movable sleeve. The tube has an interior surface defining a flow passage for the hydrocarbon fluid. The movable sleeve is positioned within the flow passage to abut the interior surface and is movable along the interior surface in response to a change in an operating characteristic of the conduit to break-up deposits on the interior surface.

公开(公告)号：US11852272B2

公开(公告)日：2023-12-26

申请号：US17362313

申请日：2021-06-29

Applicant: General Electric Company

Inventor： Arvind Namadevan ,  Urmi Tejaswini ,  Dharmaraj Pachaiappan ,  Hiranya Nath ,  Ravindra Shankar Ganiger

IPC: F16K15/03 ,  F16L55/10 ,  F16L55/027 ,  F16K47/02 ,  F16K47/08

CPC classification number: F16L55/1022 ,  F16K47/023 ,  F16K47/08 ,  F16L55/02709 ,  F16L55/02727 ,  F16K15/038

Abstract: A check valve assembly for a supply pipe. The check valve assembly includes a hinge pin, a first flapper, and a second flapper. The first flapper is pivotally coupled to the second flapper with the hinge pin. The check valve assembly also includes a stopper located between the first flapper and the second flapper. The stopper is configured to limit movement of the first flapper and the second flapper. The check valve assembly further includes a plate assembly located downstream of the stopper. The plate assembly is configured to break vortices formed in a fluid flow across the first flapper and the second flapper.

公开(公告)号：US20220412499A1

公开(公告)日：2022-12-29

申请号：US17362313

申请日：2021-06-29

Applicant: General Electric Company

Inventor： Arvind Namadevan ,  Urmi Tejaswini ,  Dharmaraj Pachaiappan ,  Hiranya Nath ,  Ravindra Shankar Ganiger

IPC: F16L55/10 ,  F16L55/027

Abstract: A check valve assembly for a supply pipe. The check valve assembly includes a hinge pin, a first flapper, and a second flapper. The first flapper is pivotally coupled to the second flapper with the hinge pin. The check valve assembly also includes a stopper located between the first flapper and the second flapper. The stopper is configured to limit movement of the first flapper and the second flapper. The check valve assembly further includes a plate assembly located downstream of the stopper. The plate assembly is configured to break vortices formed in a fluid flow across the first flapper and the second flapper.

公开(公告)号：US11267577B2

公开(公告)日：2022-03-08

申请号：US16705384

申请日：2019-12-06

Applicant: General Electric Company

Inventor： Bhaskar Nanda Mondal ,  Arvind Namadevan ,  Shankar Jayaraman ,  Keith EJ Blodgett ,  Arnab Sen

IPC: B64D29/02 ,  B64C3/36 ,  B64D27/02 ,  B64C9/32 ,  B64C5/06 ,  B64C5/08

Abstract: An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft includes a fuselage extending longitudinally between the forward end of the aircraft and the aft end of the aircraft; a primary wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; a first engine mounted to the primary wing assembly; and a first engine wing assembly extending outward from the first engine.

公开(公告)号：US20180231026A1

公开(公告)日：2018-08-16

申请号：US15433366

申请日：2017-02-15

Applicant: General Electric Company

Inventor： Arvind Namadevan ,  Sivaprakaash Karuppanchetty ,  Rajesh Kumar ,  Rajendra Mahadeorao Wankhade

IPC: F04D29/58 ,  F04D29/08 ,  F04D29/54 ,  F02C7/18

CPC classification number: F02C7/18 ,  F01D11/001 ,  F01D11/04 ,  F04D29/083 ,  F04D29/542 ,  F04D29/584 ,  F05D2240/81 ,  Y02T50/676

Abstract: A compressor for a turbine engine comprises radially spaced inner and outer bands defining a flow path between them, at least one vane extending between the inner and outer bands, a seal adjacent the inner band, and a cooling air circuit through the inner band proximate the seal.