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公开(公告)号：US11573053B2
公开(公告)日：2023-02-07
申请号：US16539807
申请日：2019-08-13
摘要： 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).
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公开(公告)号：US11407488B2
公开(公告)日：2022-08-09
申请号：US17120674
申请日：2020-12-14
发明人： Nicholas William Rathay , Corey Bourassa , Douglas Carl Hofer , Gregory Alexander Natsui , Brian Magann Rush
摘要： A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a dual-modal cooling structure can enhance heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.
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公开(公告)号：US11006549B2
公开(公告)日：2021-05-11
申请号：US16271259
申请日：2019-02-08
发明人： Brian Magann Rush , Corey Bourassa , Lana Osusky , Karthik Bodla , Hendrik Pieter Jacobus de Bock , Naveenan Thiagarajan
摘要： A cooling assembly includes a body configured to be placed into thermal contact with a heat source and one or more non-planar, hermetic walls disposed within the body. The one or more non-planar hermetic walls extending around, enclosing, and defining a cooling channel configured to carry cooling fluid through the body such that the cooling fluid contacts internal surfaces of the cooling channel inside the body. The assembly including one or more enhancement structures disposed within the body and coupled with the one or more non-planar hermetic walls. The one or more enhancement structures shaped to change a flow path of the cooling fluid as the cooling fluid moves within the cooling channel and shaped to increase a surface area contacted by the cooling fluid within the cooling channel.
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公开(公告)号：US09915176B2
公开(公告)日：2018-03-13
申请号：US14715700
申请日：2015-05-19
发明人： Robert Carl Murray , Gregory Michael Laskowski , Corey Bourassa , Byron Andrew Pritchard, Jr. , Curtis Walton Stover
CPC分类号： F01D25/24 , F01D25/14 , F02C7/18 , F05D2240/11 , F05D2260/607 , Y02T50/675
摘要： A shroud assembly for a turbine engine includes a shroud having a front side confronting the blades of a turbine and a back side opposite the front side, a hanger configured to couple the shroud to with casing of the turbine, a cooling conduit extending through the hanger to supply a cooling fluid stream to the back side of the shroud, and a particle separator having a through passage forming part of the cooling conduit and a scavenge conduit branching from the through passage.
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5.发明申请公开(公告)号：US20170276141A1
公开(公告)日：2017-09-28
申请号：US15082524
申请日：2016-03-28
发明人： Swati Saxena , Ajay Keshava Rao , Rudolf Konrad Selmeier , Grover Andrew Bennett , Giridhar Jothiprasad , Corey Bourassa , Byron Andrew Pritchard
CPC分类号： F02C9/18 , F02C6/08 , F04D29/542 , F05D2260/607
摘要： A compressor assembly for a turbomachine includes a compressor wall including circumferentially spaced stator vanes defining at least one row of stator vanes. The at least one row of stator vanes defines at least one stator passage therein. Each stator vane includes a leading edge, an opposite trailing edge defining an axial chord distance, and a pressure side. The compressor assembly also includes, at least one bleed opening defined within the compressor wall and disposed adjacent the pressure side in the at least one stator passage within a range from approximately 20% the axial chord distance upstream of the leading edge to approximately 20% the axial chord distance downstream of the trailing edge. The compressor assembly further includes at least one bleed arm extending from the at least one bleed opening with at least a portion of compressor airflow extractable through the at least one bleed arm.
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公开(公告)号：US20140341723A1
公开(公告)日：2014-11-20
申请号：US13841366
申请日：2013-03-15
发明人： Corey Bourassa
CPC分类号： F01D9/065 , F01D5/188 , F05D2260/201 , F05D2260/607 , Y10T29/49321
摘要： A guide tube assembly in one embodiment includes a guide tube and a collection impingement feature. The guide tube includes an inlet and at least one first impingement opening. The inlet is configured to direct a cooling air flow along the length of the tube in an inlet direction. The at least one impingement feature is configured to direct at least a portion of the cooling air received via the inlet along a first impingement direction. The collection impingement feature receives the at least a portion of the cooling airflow directed in the first impingement direction, collects particulate matter from the cooling airflow upon impingement of the cooling airflow with the collection impingement feature, and directs the at least a portion of the cooling air flow in a second impingement direction toward a surface of the turbine component to be cooled by the cooling air flow.
摘要翻译： 在一个实施例中的导管组件包括导管和收集冲击特征。 引导管包括入口和至少一个第一冲击开口。 入口构造成沿着管的长度在入口方向上引导冷却空气流。 所述至少一个冲击特征构造成沿着第一冲击方向引导经由所述入口接收的所述冷却空气的至少一部分。 收集冲击特征接收沿着第一冲击方向引导的冷却气流的至少一部分，在冷却空气流碰撞时收集颗粒物质与集流冲击特征，并且引导至少一部分冷却 在第二冲击方向上的气流朝向要被冷却空气流冷却的涡轮机部件的表面。
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公开(公告)号：US20210156339A1
公开(公告)日：2021-05-27
申请号：US16698287
申请日：2019-11-27
摘要： A cooling system includes a conduit extending from an upstream end to a downstream end and retains a gas. A heat exchanger is fluidly coupled with and disposed within a surface of the conduit. A portion of the gas is directed into the heat exchanger via one or more passages extending between the conduit and the heat exchanger, and a portion of the gas is directed out of the heat exchanger via the one or more passages. The heat exchanger directs cooling fluid in one or more directions within the heat exchanger along one or more passageways of plural passageways. The heat exchanger directs the portion of the gas in one or more directions within the heat exchanger along one or more other passageways of the plural passageways. The heat exchanger cools the gas by exchanging heat from the gas to the cooling fluid within the heat exchanger.
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公开(公告)号：US10724437B2
公开(公告)日：2020-07-28
申请号：US15635519
申请日：2017-06-28
摘要： A particle separator system for use with a turbomachine is provided. The particle separator system includes a first end, a second end opposite the first end, a main separator body extending between the first and second ends, the main separator body including at least one step configured to cause a fluid flow to turn up to 180 degrees, and at least one transversely oriented cyclone separator disposed within the main separator body and defining at least one of a swirling cylinder, a bent cylinder, and a conical volume.
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公开(公告)号：US10227930B2
公开(公告)日：2019-03-12
申请号：US15082524
申请日：2016-03-28
发明人： Swati Saxena , Ajay Keshava Rao , Rudolf Konrad Selmeier , Grover Andrew Bennett , Giridhar Jothiprasad , Corey Bourassa , Byron Andrew Pritchard
摘要： A compressor assembly for a turbomachine includes a compressor wall including circumferentially spaced stator vanes defining at least one row of stator vanes. The at least one row of stator vanes defines at least one stator passage therein. Each stator vane includes a leading edge, an opposite trailing edge defining an axial chord distance, and a pressure side. The compressor assembly also includes, at least one bleed opening defined within the compressor wall and disposed adjacent the pressure side in the at least one stator passage within a range from approximately 20% the axial chord distance upstream of the leading edge to approximately 20% the axial chord distance downstream of the trailing edge. The compressor assembly further includes at least one bleed arm extending from the at least one bleed opening with at least a portion of compressor airflow extractable through the at least one bleed arm.
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公开(公告)号：US10196982B2
公开(公告)日：2019-02-05
申请号：US14932162
申请日：2015-11-04
发明人： Mehmet Muhittin Dede , Satoshi Atsuchi , Byron Andrew Pritchard , Erich Alois Krammer , Giridhar Jothiprasad , Shourya Prakash Otta , Corey Bourassa
IPC分类号： F02C7/18 , F02C9/18 , F01D9/06 , F02C7/052 , F02C6/08 , F01D5/08 , F01D9/04 , F04D29/54 , F04D29/58 , B01D45/16
摘要： 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.
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