公开(公告)号：US20200024956A1

公开(公告)日：2020-01-23

申请号：US16226703

申请日：2018-12-20

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Narendra Digamber Joshi ,  Samar Jyoti Kalita ,  Paul Gerard Marsland ,  Wayne Allen Spence

IPC: F01D5/14 ,  F01D11/18 ,  B22F3/105 ,  B22F5/04 ,  B22F7/06 ,  B33Y80/00 ,  B33Y10/00 ,  F01D5/28 ,  F01D9/04

Abstract: A turbine engine airfoil apparatus, including an airfoil defined by a plurality of airfoil sections arrayed along a stacking axis that extends between a root and a tip, wherein at least two of the airfoil sections spaced apart from each other have differing airfoil section thermal expansion properties.

公开(公告)号：US10381889B2

公开(公告)日：2019-08-13

申请号：US14317294

申请日：2014-06-27

Applicant: General Electric Company

Inventor： Narendra Digamber Joshi ,  Manoj Ramprasad Shah ,  James William Bray ,  Randy Marinus Vondrell ,  Kurt David Murrow ,  Jeffrey Anthony Hamel ,  Samuel Jacob Martin

IPC: H02K1/28 ,  H02K1/27 ,  H02K1/18 ,  H02K1/30 ,  H02K21/24 ,  H02K49/10 ,  H02K21/02

Abstract: A permanent magnet machine and a rotor assembly for the permanent magnet machine. The permanent magnet machine includes a stator assembly including a stator core configured to generate a magnetic field and extending along a longitudinal axis with an inner surface defining a cavity and a rotor assembly including a rotor core and a rotor shaft. The rotor core is disposed inside the stator cavity and configured to rotate about the longitudinal axis. The rotor assembly further including a plurality of permanent magnets for generating a magnetic field which interacts with the stator magnetic field to produce torque. The permanent magnets are disposed within one or more cavities formed in a sleeve component. The sleeve component configured to include a plurality of cavities or voids therein and thus provide minimal weight to the permanent magnet machine. The permanent magnet machine providing increased centrifugal load capacity, increased power density and improved electrical performance.

公开(公告)号：US20190136761A1

公开(公告)日：2019-05-09

申请号：US15805878

申请日：2017-11-07

Applicant: General Electric Company

Inventor： Andrew Philip Shapiro ,  Narendra Digamber Joshi

IPC: F02C6/10 ,  H01M8/04111 ,  H01M8/1246 ,  H01M8/04082 ,  F02C3/20 ,  F02C6/06

Abstract: An integrated fuel cell and engine combustor assembly includes an engine combustor having a combustion chamber fluidly coupled with a compressor and a turbine. The assembly also includes a fuel cell stack circumferentially extending around the combustion chamber of the combustor. The fuel cell stack includes fuel cells configured to generate electric current. The fuel cell stack is positioned to receive discharged air from the compressor and fuel from a fuel manifold. The fuel cells in the fuel cell stack generate electric current using the discharged air and at least some of the fuel. The fuel cell stack is positioned to radially direct partially oxidized fuel from the fuel cells into the combustion chamber of the combustor. The combustor combusts the partially oxidized fuel into one or more gaseous combustion products that are directed into and drive the downstream turbine.

公开(公告)号：US20190120492A1

公开(公告)日：2019-04-25

申请号：US16164474

申请日：2018-10-18

Applicant: General Electric Company

Inventor： Venkat Eswarlu Tangirala ,  Narendra Digamber Joshi

IPC: F23R3/42 ,  F23R3/28 ,  F23R3/02 ,  F02C3/14 ,  F02C7/22

Abstract: A fuel and air injection handling system for a rotating detonation engine is provided. The system includes a compressor configured to compress air received via a compressor inlet and configured to output the air that is compressed as swirling, compressed air through a compressor outlet. The system also includes an annular rotating detonation combustor fluidly coupled with the compressor outlet. The annular rotating detonation combustor has a detonation cavity that extends around an annular axis, the annular rotating detonation combustor configured to combust the compressed air from the compressor in detonations that rotate within the detonation cavity around the annular axis of the annular rotating detonation combustor. The annular rotating detonation combustor is fluidly and directly coupled with the compressor outlet.

公开(公告)号：US20190003315A1

公开(公告)日：2019-01-03

申请号：US15424021

申请日：2017-02-03

Applicant: General Electric Company

Inventor： Daniel Jason Erno ,  Narendra Digamber Joshi ,  William Dwight Gerstler

IPC: F01D5/18 ,  F02K3/06 ,  F01D9/06

CPC classification number: F01D5/187 ,  F01D9/065 ,  F01D25/162 ,  F01D25/18 ,  F02C7/14 ,  F02K3/06 ,  F05D2220/36 ,  F05D2240/121 ,  F05D2250/185 ,  F05D2260/201 ,  F05D2260/213 ,  F05D2260/22141 ,  F16N39/02

Abstract: A heat exchanger includes an airfoil configured to be positioned in a coolant stream. The airfoil includes a pressure sidewall and a suction sidewall coupled to the pressure sidewall. The suction sidewall and the pressure sidewall define a leading edge and a trailing edge opposite the leading edge. The leading edge defines an impingement zone wherein the coolant stream is configured to impinge the airfoil. The heat exchanger also includes at least one channel defined within the airfoil between the pressure sidewall and the suction sidewall. The at least one channel is at least partially defined within the impingement zone proximate the leading edge.

公开(公告)号：US10082076B2

公开(公告)日：2018-09-25

申请号：US14706679

申请日：2015-05-07

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Venkat Eswarlu Tangirala ,  Narendra Digamber Joshi

IPC: F23R3/04 ,  F02C3/14 ,  F23R3/14 ,  F02C3/04 ,  F04D29/54 ,  B23P15/04 ,  F23R3/00 ,  F23R3/34 ,  F23R3/44 ,  F23R3/12 ,  F23R3/26 ,  F23R3/28 ,  F23R3/50 ,  F01D9/02 ,  F04D27/02 ,  F04D29/56

CPC classification number: F02C3/14 ,  B23P15/04 ,  F01D9/023 ,  F02C3/04 ,  F04D27/0246 ,  F04D29/542 ,  F04D29/544 ,  F04D29/563 ,  F05D2240/35 ,  F23R3/002 ,  F23R3/04 ,  F23R3/12 ,  F23R3/14 ,  F23R3/26 ,  F23R3/28 ,  F23R3/34 ,  F23R3/44 ,  F23R3/50 ,  Y10T29/49323

Abstract: Embodiments of a combustor for a gas turbine engine are provided herein. In some embodiments, a combustion chamber for a gas turbine engine comprising may include a combustor having an inner volume defined at least partially by a front wall, wherein the wall comprises a plurality of facets each having a through hole fluidly coupled to the inner volume, and wherein the plurality of facets are oriented such that an axis of each of the plurality of facets is offset from a central axis of the combustor by an angle.

公开(公告)号：US20180187888A1

公开(公告)日：2018-07-05

申请号：US15398496

申请日：2017-01-04

Applicant: General Electric Company

Inventor： Venkat Eswarlu Tangirala ,  Narendra Digamber Joshi ,  Sarah Marie Monahan

IPC: F23R3/00 ,  F02C3/04

CPC classification number: F23R3/002 ,  F23R3/06 ,  F23R3/58 ,  F23R2900/03042

Abstract: A combustor for use in a turbine engine that includes an inner combustion liner and an outer combustion liner. An interior is defined between the inner combustion liner and the outer combustion liner, and the interior includes a cavity portion and a main portion extending radially inward from the cavity portion. The cavity portion includes a flow inlet and the main portion includes a flow outlet. A plurality of film cooling holes are formed in at least one of the inner combustion liner and the outer combustion liner. The plurality of film cooling holes are configured such that cooling airflow discharged therefrom flows helically relative to a centerline of the turbine engine and towards the flow outlet.

公开(公告)号：US09963981B2

公开(公告)日：2018-05-08

申请号：US14735260

申请日：2015-06-10

Applicant: General Electric Company

Inventor： Narendra Digamber Joshi ,  Michael Solomon Idelchik

IPC: F01D7/00 ,  F02K3/06 ,  F02K3/075 ,  F02K1/66 ,  F01D15/10

CPC classification number: F01D7/00 ,  F01D15/10 ,  F02K1/66 ,  F02K3/06 ,  F02K3/075 ,  F05D2220/32 ,  F05D2220/327 ,  F05D2220/36 ,  F05D2220/768 ,  F05D2240/51 ,  F05D2260/74 ,  Y02T50/672

Abstract: A shrouded fan assembly for use with a gas turbine engine includes a central hub and a plurality of variable-pitch fan blades coupled to and extending radially outward from the central hub. Each variable-pitch fan blade includes a radially outer tip is rotatable about a longitudinal axis extending therethrough. A shroud is coupled to each radially outer tip.

公开(公告)号：US09599017B2

公开(公告)日：2017-03-21

申请号：US13930122

申请日：2013-06-28

Applicant: General Electric Company

Inventor： Narendra Digamber Joshi ,  Joel Meier Haynes ,  Venkat Eswarlu Tangirala ,  Christian Lee Vandervort

IPC: F01K23/10 ,  F02C3/34 ,  F02C3/30 ,  F02C6/00 ,  F02C7/16 ,  F02C9/18 ,  F23R3/34

CPC classification number: F02C3/30 ,  F01K23/10 ,  F02C3/34 ,  F02C6/003 ,  F02C7/16 ,  F02C9/18 ,  F05D2260/61 ,  F23R3/34 ,  F23R2900/03341 ,  Y02E20/16 ,  Y02E20/18

Abstract: A turbine system and method of operating is provided. The system includes a compressor configured to generate a compressed low-oxygen air stream and a combustor configured to receive the compressed low-oxygen air stream and to combust a fuel stream to generate a post combustion gas stream. The turbine system also includes a turbine for receiving the post combustion gas stream to generate a low-NOx exhaust gas stream, a heat recovery system configured to receive the low-NOx exhaust gas stream and generate a cooled air stream and an auxiliary compressor configured to generate an oxygen and water vapor deficient cooled and compressed air stream. A portion of the oxygen and water vapor deficient cooled and compressed air stream is directed to the combustor to generate an Oxygen and H2O deficient film on exposed portions of the combustor, and another portion is directed to the turbine to provide a cooling flow.

公开(公告)号：US09551492B2

公开(公告)日：2017-01-24

申请号：US13691017

申请日：2012-11-30

Applicant: General Electric Company

Inventor： Joel Meier Haynes ,  Narendra Digamber Joshi ,  Huijuan Chen

IPC: F23R3/28 ,  F23R3/34 ,  F01D9/02 ,  F23R3/46 ,  F02K3/00

CPC classification number: F23R3/346 ,  F01D9/023 ,  F02K3/00 ,  F23R3/286 ,  F23R3/34 ,  F23R3/46

Abstract: A gas turbine engine system includes a compressor, a combustor, and a turbine. The combustor is coupled to the compressor and disposed downstream of the compressor. The combustor includes a secondary combustor section coupled to a primary combustor section and disposed downstream of the primary combustor section. The combustor also includes a transition nozzle coupled to the secondary combustor section and disposed downstream of the secondary combustor section. The combustor further includes an injector coupled to the secondary combustor section, for injecting an air-fuel mixture to the secondary combustor section. The turbine is coupled to the combustor and disposed downstream of the transition nozzle; wherein the transition nozzle is oriented substantially tangential to the turbine.

Abstract translation: 燃气涡轮发动机系统包括压缩机，燃烧器和涡轮机。 燃烧器联接到压缩机并设置在压缩机的下游。 燃烧器包括联接到主燃烧器部分并且设置在主燃烧器部分的下游的次级燃烧器部分。 燃烧器还包括连接到次级燃烧器部分并设置在次级燃烧器部分的下游的过渡喷嘴。 燃烧器还包括联接到次级燃烧器部分的喷射器，用于将空气 - 燃料混合物喷射到次级燃烧器部分。 涡轮联接到燃烧器并设置在过渡喷嘴的下游; 其中所述过渡喷嘴基本上与所述涡轮相切。