公开(公告)号：US20200149399A1

公开(公告)日：2020-05-14

申请号：US15891401

申请日：2018-02-08

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nicholas Joseph Kray ,  Nitesh Jain ,  Nagashiresha Gontla ,  Narendra Digamber Joshi ,  Paul Gerard Marsland ,  Wayne Allen Spence

IPC: F01D5/12 ,  F01D5/30

Abstract: A blade and a turbomachine engine having the blade are disclosed. The blade includes an airfoil having a root portion, a tip portion, and a plurality of fins integrally coupled to the root portion. The plurality of fins is disposed along a thickness of the airfoil.

公开(公告)号：US20200072174A1

公开(公告)日：2020-03-05

申请号：US16118895

申请日：2018-08-31

Applicant: General Electric Company

Inventor： Nicholas William Rathay ,  Matthew Patrick Boespflug ,  Narendra Digamber Joshi

IPC: F02M53/06 ,  F02P15/00 ,  F02M47/04

Abstract: A flow control actuator includes at least one side wall, an upstream wall coupled to an upstream end of the side wall, a downstream cap coupled to a downstream end of the side wall, the downstream cap comprising at least one orifice disposed therein, at least one fuel injector disposed in at least one of the upstream wall, and the sidewall, the fuel injector dispersing fuel into the interior of the flow control actuator, and at least one oxidizer inlet disposed in at least one of the upstream wall and the sidewall, the at least one oxidizer inlet introducing an oxidizer into the interior of the flow control actuator. The flow control actuator includes at least one external fuel injector disposed adjacent to the side wall. The fuel from the fuel injector and oxidizer from the oxidizer inlet ignite in the interior of the flow control actuator.

公开(公告)号：US20190226398A1

公开(公告)日：2019-07-25

申请号：US16133362

申请日：2018-09-17

Applicant: General Electric Company

Inventor： Venkat Eswarlu Tangirala ,  Narendra Digamber Joshi ,  Peter Daniel Silkowski

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

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：US20190165652A1

公开(公告)日：2019-05-30

申请号：US15827335

申请日：2017-11-30

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Anoop Kumar Jassal ,  Mohamed Osama ,  Francesco Papini ,  Narendra Digamber Joshi

IPC: H02K9/08 ,  H02K3/22 ,  H02K3/12 ,  H02K1/32

Abstract: An electric machine comprising a rotor, a stator, a plurality of bare conductors forming a plurality of windings in at least one of the stator and the rotor, and a fluid in direct physical contact with a plurality of outer surfaces of the plurality of bare conductors, wherein the fluid is electrically insulating and provides direct fluid cooling, to provide cooling for the plurality of bare conductors and electrical insulation between consecutive bare conductors of the plurality of bare conductors

公开(公告)号：US10280760B2

公开(公告)日：2019-05-07

申请号：US14870853

申请日：2015-09-30

Applicant: General Electric Company

Inventor： Narendra Digamber Joshi ,  Christian Lee Vandervort ,  Krishan Lal Luthra ,  Ronald Scott Bunker ,  Joel Meier Haynes ,  Venkat Eswarlu Tangirala

IPC: F02C1/00 ,  F02C3/34 ,  F02C1/08 ,  F01D5/18 ,  F23R3/00 ,  F02C6/00 ,  F02C7/18 ,  F23C9/08 ,  F01D25/32

Abstract: A turbine assembly is provided. The turbine assembly includes a gas turbine engine including at least one hot gas path component formed at least partially from a ceramic matrix composite material. The turbine assembly also includes a treatment system positioned to receive a flow of exhaust gas from the gas turbine engine. The treatment system is configured to remove water from the flow of exhaust gas to form a flow of treated exhaust gas, and to channel the flow of treated exhaust gas towards the at least one hot gas path component. The at least one hot gas path component includes a plurality of cooling holes for channeling the flow of treated exhaust gas therethrough, such that a protective film is formed over the at least one hot gas path component.

公开(公告)号：US20190086091A1

公开(公告)日：2019-03-21

申请号：US15705954

申请日：2017-09-15

Applicant: General Electric Company

Inventor： Owen James Sullivan Rickey ,  Venkat Eswarlu Tangirala ,  Narendra Digamber Joshi ,  Shashank Yellapantula

IPC: F23R3/16 ,  F02C7/22 ,  F02C6/18 ,  F23R3/56 ,  F23R3/28

Abstract: A rotating detonation combustor includes a combustion chamber configured for a rotating detonation process to produce a flow of combustion gas and an air plenum configured to contain a volume of air. The rotating detonation combustor also includes a flow passage coupled in flow communication between the combustion chamber and the air plenum and configured to channel an airflow from the air plenum. The rotating detonation combustor also includes a fuel inlet coupled in flow communication with the flow passage and configured to channel a fuel flow into the flow passage. The flow passage includes a plurality of fuel mixing mechanisms configured to mix the airflow and the fuel flow within the combustion chamber.

公开(公告)号：US20190017437A1

公开(公告)日：2019-01-17

申请号：US15649093

申请日：2017-07-13

Applicant: General Electric Company

Inventor： Venkat Eswarlu Tangirala ,  Aaron Glaser ,  Sibtosh Pal ,  Narendra Digamber Joshi

IPC: F02C3/16 ,  F02C3/04 ,  F01D5/06 ,  F01D9/04 ,  F02C9/18 ,  F23R3/46

Abstract: A gas turbine engine includes a primary combustor, a secondary combustor, a high pressure (HP) turbine, and a mixing duct. The HP turbine is downstream of the primary combustor and fluidly connected to a rear end of the primary combustor via a first exhaust duct. The mixing duct is disposed downstream of the HP turbine and the secondary combustor. The mixing duct has a first inlet fluidly connected to the HP turbine via a turbine exit duct, a second inlet fluidly connected to a rear end of the secondary combustor via a second exhaust duct, and an outlet. The turbine exit duct directs a primary exhaust stream, which is emitted from the primary combustor and expanded through the HP turbine, into the mixing duct. The second exhaust duct directs a secondary exhaust stream emitted from the secondary combustor into the mixing duct.

公开(公告)号：US10119460B2

公开(公告)日：2018-11-06

申请号：US14489565

申请日：2014-09-18

Applicant: General Electric Company

Inventor： Roy James Primus ,  Adam Edgar Klingbeil ,  Narendra Digamber Joshi ,  Omowoleola Chukwuemeka Akinyemi ,  Thomas Michael Lavertu

IPC: F02C3/13 ,  F02B63/04 ,  F02C3/10 ,  F02D41/00 ,  F02C6/08 ,  F02C6/00 ,  F02C6/12 ,  F02C6/20 ,  F01D15/10

Abstract: A system includes an engine coupled with a primary shaft that drives a first electric generator for generating electrical power via a gear subsystem. The system also includes a turbocharger assembly having at least one gas turbine engine configured for driving the primary shaft and coupled in parallel with the engine. The turbocharger assembly includes multiple compressors configured to provide a flow of compressed fluid into both the engine and the at least one gas turbine engine and multiple turbines configured to utilize exhausts from both the engine and the one gas turbine for driving the primary shaft. Further, the system includes a controller configured to operate a plurality of valves for controlling optimal intake fluid pressure into the engine and the turbocharger assembly and fuel injections into the engine and the at least one gas turbine engine.

公开(公告)号：US10072846B2

公开(公告)日：2018-09-11

申请号：US14791684

申请日：2015-07-06

Applicant: General Electric Company

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

IPC: F23R3/28 ,  F23R3/34 ,  F23C5/08 ,  F23R3/58 ,  F23R3/12 ,  F23R3/04 ,  F23C5/00 ,  F23R3/42 ,  F23C5/32 ,  F23R3/02 ,  F23R3/10 ,  F23C5/24 ,  F23R3/06

CPC classification number: F23R3/286 ,  F05D2240/35 ,  F23C5/00 ,  F23C5/08 ,  F23C5/10 ,  F23C5/24 ,  F23C5/32 ,  F23R3/02 ,  F23R3/04 ,  F23R3/045 ,  F23R3/06 ,  F23R3/10 ,  F23R3/12 ,  F23R3/34 ,  F23R3/346 ,  F23R3/42 ,  F23R3/58 ,  F23R2900/00015 ,  F23R2900/03041 ,  F23R2900/03042 ,  Y02T50/675

Abstract: A gas turbine engine and combustor assembly including a combustor liner defining therein a combustion chamber for the downstream flow of a main fluid. At least two axially spaced apart annular trapped vortex cavities are located on the combustor liner and staged axially and radially spaced apart. A cavity opening is located at a radially inner end of each of the at least two annular trapped vortex cavities. A plurality of injectors are configured tangentially relative to circular radially outer wall extending between an aft wall and a forward wall of each cavity to provide for an injection of air and fuel to form an annular rotating trapped vortex of a fuel and air mixture within a respective annular trapped vortex cavity. The annular rotating trapped vortex of the fuel and air mixture at the cavity openings is substantially perpendicular to the downstream flow of the main fluid.

公开(公告)号：US20170328569A1

公开(公告)日：2017-11-16

申请号：US15150844

申请日：2016-05-10

Applicant: General Electric Company

Inventor： Shashank Yellapantula ,  Anthony John Dean ,  Narendra Digamber Joshi ,  Mehmet Muhittin Dede ,  Jin Yan ,  Owen James Sullivan Rickey

IPC: F23R3/34

Abstract: A fuel nozzle assembly includes a centerbody including an outer wall. The outer wall defines a plurality of fuel injection apertures. The fuel injection apertures include a first portion of the plurality of fuel injection apertures configured to induce a first fuel flow rate. The fuel injection apertures also include a second portion of the plurality of fuel injection apertures configured to induce a second fuel flow rate. The second fuel flow rate is less than the first fuel flow rate.