公开(公告)号：US20190078516A1

公开(公告)日：2019-03-14

申请号：US15702730

申请日：2017-09-12

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Karthikeyan Sampath ,  Atanu Saha ,  Bhaskar Nanda Mondal ,  Sanjeev Sai Kumar Manepalli

IPC: F02C7/16 ,  F02C7/14 ,  B64D33/08

Abstract: A gas turbine engine having a heat absorption device and an associated method are disclosed. The gas turbine engine includes a compressor, a combustor, a turbine, a bleed fluid cavity, and the heat absorption device. The combustor is coupled to the compressor. The turbine is coupled to the compressor and the combustor. The bleed fluid cavity is formed at a first predefined location in the compressor. The heat absorption device is disposed in the bleed fluid cavity and includes a casing, a flow path, and a phase change material. The casing includes an inlet and an outlet. The flow path is within the casing, extends between the inlet and the outlet, and directs an input bleed fluid separated from a fluid stream discharged from the compressor. The phase change material is filled in the casing, separated from the flow path.

公开(公告)号：US20180313276A1

公开(公告)日：2018-11-01

申请号：US15499743

申请日：2017-04-27

Applicant: General Electric Company

Inventor： Steven Mitchell Taylor ,  Vishnu Das K ,  Manish Singhal ,  Atanu Saha ,  Michael Anthony Thomas

IPC: F02C9/18 ,  F02C3/06

Abstract: A compressor bleed slot apparatus includes: an annular compressor casing; a stator vane row disposed inside the compressor casing; a blade row mounted for rotation about a centerline axis inside the compressor casing, axially downstream of the stator row; a bleed slot passing through the compressor casing, wherein the bleed slot is bounded by inboard and outboard walls defined within the compressor casing, the bleed slot having an inlet positioned axially between the stator vane row and the blade row, the bleed slot extending along a slot axis, at least a portion of the bleed slot lying within an axial extent of the blade row; an annular array of struts interconnecting the inboard and outboard walls; and an annular supplemental flange extending radially outward from the compressor casing, wherein at least a portion of the supplemental flange is axially positioned within an axial extent of the bleed slot.

公开(公告)号：US20170342851A1

公开(公告)日：2017-11-30

申请号：US15168581

申请日：2016-05-31

Applicant: General Electric Company

Inventor： Jagata Laxmi Narasimharao ,  Thomas Ory Moniz ,  Mohamed Musthafa Thoppil ,  Bhaskar Nanda Mondal ,  Atanu Saha

IPC: F01D11/04 ,  F01D5/12 ,  F01D25/12

CPC classification number: F01D11/04 ,  F01D3/00 ,  F01D5/082 ,  F01D5/085 ,  F01D5/12 ,  F01D11/001 ,  F01D11/02 ,  F01D25/12 ,  F02C7/28 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/55 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine assembly includes a rotor assembly including a shaft coupled to a plurality of rotor stages including a plurality of turbine blades. The shaft and the plurality of turbine blades define a wheelspace therein. The turbine assembly further includes a plurality of seals in series, at least one seal of the plurality of seals is coupled between a static support member and a respective rotor stage such that a plurality of turbine cavities in series are defined within the wheelspace. Each turbine cavity of the plurality of turbine cavities defined by the plurality of seals receives a pressurized fluid flow that applies an axially aft force to the respective rotor stage of the plurality of rotor stages that at least partially reduces net rotor thrust generated by the rotor assembly during operation, the pressurized fluid flow further provides turbine purge within the wheel space.