公开(公告)号：US20190010821A1

公开(公告)日：2019-01-10

申请号：US16001561

申请日：2018-06-06

Applicant: General Electric Company

Inventor： Debabrata MUKHOPADHYAY ,  James ADAICKALASAMY ,  Muralikrishna RANGHARAJHAN

IPC: F01D11/20 ,  F02C9/50

Abstract: This disclosure provides systems and methods for controlling gas turbine airfoil clearance using virtual clearance measurement. The disclosure includes a gas turbine system having a stage of airfoils and a casing adjacent the stage of airfoils that define a clearance distance between them. A clearance control mechanism controllably adjusts the clearance distance based upon a clearance control signal. The clearance control signal to the clearance control mechanism is based on a virtual clearance function that generates a clearance value from at least one system measurement of the gas turbine system.

公开(公告)号：US20170067365A1

公开(公告)日：2017-03-09

申请号：US14849112

申请日：2015-09-09

Applicant: General Electric Company

Inventor： Debabrata MUKHOPADHYAY ,  Rohit PRUTHI

IPC: F01D25/14 ,  F01D25/24

CPC classification number: F01D25/162 ,  F01D9/065 ,  F05D2250/182 ,  F05D2250/294 ,  F05D2260/2214 ,  F05D2260/22141 ,  Y02T50/676 ,  Y02T50/6765

Abstract: A system is provided including a turbine exhaust section. The turbine exhaust section includes an exhaust flow path. The turbine exhaust section also includes an outer structure having an outer casing and an outer exhaust wall disposed along the exhaust flow path. An inner structure of the turbine exhaust section includes an inner exhaust wall disposed along the exhaust flow path. A strut extends between the outer structure and the inner structure, and the strut is configured to convey a flow of fluid from the inner structure toward the outer structure. The strut includes a plurality of cooling fins to facilitate heat transfer from the strut to the flow of fluid.

Abstract translation: 提供了一种包括涡轮机排气部分的系统。 涡轮排气部包括排气流路。 涡轮机排气部还包括外部结构，其具有沿着排气流路设置的外壳和外排气壁。 涡轮排气部的内部结构包括沿排气流路设置的内排气壁。 支柱在外部结构和内部结构之间延伸，并且支柱构造成将流体流从内部结构传送到外部结构。 支柱包括多个冷却翅片，以便于从支柱到流体流的热传递。

公开(公告)号：US20190022803A1

公开(公告)日：2019-01-24

申请号：US16042355

申请日：2018-07-23

Applicant: General Electric Company

Inventor： Dheepa SRINIVASAN ,  Joydeep PAL ,  Debabrata MUKHOPADHYAY

IPC: B23P6/00 ,  B33Y10/00 ,  B23K26/342 ,  F01D5/00

Abstract: A method for repairing a component is disclosed. The method includes removing a portion originally including a plurality of cooling holes, of the component to form a cavity, forming by additive manufacturing a replacement portion including a plurality of cooling holes, and varying a surface roughness and a diameter of at least one cooling hole of the plurality of cooling holes during the forming by additive manufacturing the replacement portion. The replacement portion replaces the portion of the component.

公开(公告)号：US20180371999A1

公开(公告)日：2018-12-27

申请号：US15985737

申请日：2018-05-22

Applicant: General Electric Company

Inventor： Rajesh MAVURI ,  Debabrata MUKHOPADHYAY

IPC: F02C7/141 ,  F01D5/08 ,  F04D29/58 ,  F04D29/32 ,  F02C3/073

Abstract: A cooling system for a turbine engine is provided. The turbine engine includes a compressor, a compressor discharge chamber (CDC), a combustor assembly, and a turbine coupled in a serial flow relationship such that a first portion of air from the CDC is channeled to the combustor assembly. The turbine is coupled to the compressor via a rotor. The cooling system includes an air duct configured to channel a second portion of air from the CDC to a mid-rotor region of the rotor, and a fluid supply system coupled to the air duct at a coupling. The fluid supply system is configured to channel a flow of fluid to the coupling. The coupling is configured to cool the second portion of CDC air via absorption of heat by the fluid from the second portion of CDC air.

公开(公告)号：US20150159498A1

公开(公告)日：2015-06-11

申请号：US14097753

申请日：2013-12-05

Applicant: General Electric Company

Inventor： Debabrata MUKHOPADHYAY ,  Xiaoqing Zheng

IPC: F01D11/08

CPC classification number: F01D11/08 ,  F01D11/001 ,  F05D2240/56 ,  F16J15/3288 ,  F16J15/441 ,  F16J15/4472

Abstract: A seal arrangement between radially-opposed rotating and stationary components in a turbomachine includes a first rotating component, a second stationary component, and a brush seal located radially therebetween. The brush seal has an axially-extending portion secured to the second stationary component, and an inwardly-extending portion extending across a gap between the first and second components. An inner ring portion of the second stationary component is located radially inward of, and in engagement with the axially-extending portion and at least part of the inwardly-extending portion of the brush seal, wherein an end of the axially-extending portion of the brush seal remote from the inwardly-extending portion is sandwiched between a pair of side rails fixed between the inner ring portion and an outer ring portion of the second stationary component.

Abstract translation: 在涡轮机中的径向相对的旋转和静止部件之间的密封装置包括第一旋转部件，第二固定部件和径向位​​于其间的刷子密封件。 刷密封具有固定到第二固定部件的轴向延伸部分，以及延伸穿过第一和第二部件之间的间隙的向内延伸的部分。 第二固定部件的内环部分位于电刷密封件的轴向延伸部分和向内延伸部分的至少部分的径向内侧并与其接合，其中轴向延伸部分的端部 远离所述向内延伸部分的刷密封夹在固定在所述第二固定部件的所述内环部分和外环部分之间的一对侧轨之间。