公开(公告)号：US20210365086A1

公开(公告)日：2021-11-25

申请号：US17394088

申请日：2021-08-04

Applicant: General Electric Company

Inventor： Brian Magann Rush ,  Corey Bourassa ,  William Dwight Gerstler ,  Gary Mandrusiak

IPC: G06F1/20 ,  H05K7/20

Abstract: A multi-domain cooling assembly configured to be coupled with one or more heat sources includes a body having an outer surface and at least one cooling chamber disposed inside the body. The at least one cooling chamber extends in at least two orthogonal dimensions and includes a working fluid to extract thermal energy from the one or more heat sources. The assembly includes a cooling channel disposed within the body and fluidly coupled with a passageway that carries cooling fluid into and out of the cooling channel. At least a portion of the cooling fluid is a liquid phase, a gas phase, or a liquid-gas mix phase. The cooling channel is fluidly separate from the at least one cooling chamber. The cooling channel is thermally coupled with the at least one cooling chamber. The at least one cooling chamber transfers thermal energy from the working fluid to the cooling fluid.

公开(公告)号：US20210048255A1

公开(公告)日：2021-02-18

申请号：US16539807

申请日：2019-08-13

Applicant: General Electric Company

Inventor： Hendrik Pieter Jacobus de Bock ,  Corey Bourassa ,  William Dwight Gerstler

IPC: F28D15/02 ,  F28F13/12

Abstract: A cyclone cooler device includes a housing that defines an interior channel elongated along a center axis. One or more of the fluid passage or configuration of an inlet end of the channel is shaped to induce a swirling flow of a cooling fluid within the channel while the channel is thermally coupled with one or more heat sources. The swirling flow of the cooling fluid removes thermal energy from and cools the one or more heat sources. During the swirling flow, the cooling fluid rotates around the center axis of the channel while also moving along the length of the center axis. The cooling fluid changes phases during the swirling flow to cool the heat source(s).

公开(公告)号：US20200308989A1

公开(公告)日：2020-10-01

申请号：US16901568

申请日：2020-06-15

Applicant: General Electric Company

Inventor： Jared Peter Buhler ,  Christopher Charles Glynn ,  Corey Bourassa ,  Monty Lee Shelton ,  Robert Francis Manning ,  Victor Hugo Silva Correia

IPC: F01D25/32 ,  B01D46/24 ,  B01D45/12 ,  B01D46/42 ,  F01D25/12 ,  F01D9/06 ,  B01D45/08 ,  B01D45/16

Abstract: An assembly for removing particles from a fluid stream includes a first particle remover having a main flow outlet emitting a first reduced-particle stream and a scavenge flow outlet emitting a particle-laden stream, as well as a second particle remover fluidly coupled to the scavenge flow outlet and emitting a second reduced-particle stream.

公开(公告)号：US20180016944A1

公开(公告)日：2018-01-18

申请号：US15210783

申请日：2016-07-14

Applicant: General Electric Company

Inventor： Jared Peter Buhler ,  Christopher Charles Glynn ,  Corey Bourassa ,  Monty Lee Shelton ,  Robert Francis Manning ,  Victor Hugo Silva Correia

IPC: F01D25/32 ,  B01D45/12 ,  B01D46/10 ,  B01D45/04 ,  B01D46/24 ,  B01D46/42 ,  F01D25/12

Abstract: An assembly for removing entrained particles from a fluid stream passing through a gas turbine engine includes a first particle remover, a second particle remover fluidly coupled which receives a particle-laden stream from the first particle remover, and a venturi having a fluidly coupled to the second particle remover to increase the pressure differential across the assembly.

公开(公告)号：US20170138262A1

公开(公告)日：2017-05-18

申请号：US14940251

申请日：2015-11-13

Applicant: General Electric Company

Inventor： Satoshi Atsuchi ,  Erich Alois Krammer ,  Corey Bourassa ,  Byron Andrew Pritchard ,  Mehmet Dede

IPC: F02C7/052 ,  F02C9/18 ,  B01D45/04 ,  F02C3/06

CPC classification number: F02C7/052 ,  B01D45/04 ,  F02C7/12 ,  F05D2260/202 ,  F05D2260/607 ,  Y02T50/671 ,  Y02T50/676

Abstract: A particle separator for a turbomachine includes a first portion including a first end and a second end opposite the first end. The turbomachine includes a first wall and a second wall defining a primary fluid passage. The first wall further defines an auxiliary fluid passage. The first end is coupled to the first wall. The second end extends from the first wall into the at least one primary fluid passage and extends in a direction defined by the fluid flow through the primary fluid passage. The second end and the first wall define a fluid diversion passage coupled in flow communication with the primary fluid passage and the auxiliary fluid passage. The fluid diversion passage is configured to divert fluid from the primary fluid passage to the auxiliary fluid passage in a direction at least partially opposed to the fluid flow through the primary fluid passage.

公开(公告)号：US20170122209A1

公开(公告)日：2017-05-04

申请号：US14932162

申请日：2015-11-04

Applicant: General Electric Company

Inventor： Mehmet Muhittin Dede ,  Satoshi Atsuchi ,  Byron Andrew Pritchard ,  Erich Alois Krammer ,  Giridhar Jothiprasad ,  Shourya Prakash Otta ,  Corey Bourassa

IPC: F02C7/18 ,  F02C7/052

CPC classification number: F02C7/18 ,  B01D45/16 ,  F01D5/081 ,  F01D9/041 ,  F01D9/065 ,  F02C6/08 ,  F02C7/052 ,  F02C9/18 ,  F04D29/542 ,  F04D29/584 ,  F05D2240/124 ,  F05D2250/51 ,  F05D2260/232 ,  F05D2260/607 ,  Y02T50/671 ,  Y02T50/676

Abstract: The invention relates to a gas turbine engine comprising a casing having a compressor section, combustion section and turbine section, axially arranged in a flow direction about a rotational axis of the engine. The engine includes a rotor located within the casing and rotatable about the rotational axis, including multiple sets of circumferentially arranged blades, with at least one set corresponding to the compressor section and another set corresponding to the turbine section. The engine also includes a set of vanes circumferentially arranged about the rotational axis and at a location upstream of the combustion section, with the vanes having a pressure side and a suction side. The engine further includes a cooling conduit extending from upstream of the combustion section to downstream of the combustion section, with an inlet located on the suction side of at least one of the vanes which allows cooling air to enter the inlet and is directed through the cooling conduit for cooling.

公开(公告)号：US20170122202A1

公开(公告)日：2017-05-04

申请号：US14925190

申请日：2015-10-28

Applicant: General Electric Company

Inventor： John Joseph Rahaim ,  Corey Bourassa ,  Jared Peter Buhler ,  Jonathan Russell Ratzlaff

IPC: F02C3/13 ,  F02C3/34

CPC classification number: F02C3/13 ,  B01D45/16 ,  B04C3/06 ,  B04C2003/006 ,  F01D5/08 ,  F02C3/34 ,  F02C7/052 ,  F02C7/18 ,  F05D2220/32 ,  F05D2260/60 ,  F05D2260/607 ,  Y02T50/676

Abstract: A gas turbine engine comprising a cyclonic separator provides fluid communication between the compressor section and the turbine section. The cyclonic separator comprises an annular volume receiving a flow of cooling fluid from an inlet and dividing the airflow into a cleaner air outlet and a scavenge outlet. The flow of cooling fluid is provided to the cyclonic separator in a direction tangential to the annular volume such that a cyclonic flow of cooling fluid moves within the annular volume centrifugally separating particles entrained within the airflow to the radial outer area of the annular volume for removal through the scavenge outlet and providing a cleaner airflow to the cleaner air outlet.

公开(公告)号：US09617917B2

公开(公告)日：2017-04-11

申请号：US13955096

申请日：2013-07-31

Applicant: General Electric Company

Inventor： Corey Bourassa ,  William Dwight Gerstler ,  Bruce Philip Biederman

IPC: F02C7/18 ,  F02C9/16

CPC classification number: F02C7/18 ,  F02C9/16 ,  Y02T50/671 ,  Y02T50/675 ,  Y10T29/49323

Abstract: A flow control assembly for controlling cooling flow of a turbine engine is provided. The flow control assembly includes a first flow control device having a first sidewall and a second sidewall. The first sidewall is coupled to a compressor vane and is configured to define a first flow path from a compressor to a turbine vane. The second sidewall is coupled to a compressor vane and is configured to define a second flow path from the compressor to a turbine blade. A second flow control device is coupled to the compressor and includes an orifice device coupled to the compressor vane and a meter device coupled to the orifice, wherein the orifice is configured to direct a cooling flow to the meter device. A controller is configured to control the meter device to facilitate regulating the cooling flow into at least one of the first flow path and the second flow path.