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公开(公告)号：US20170328283A1
公开(公告)日：2017-11-16
申请号：US15150628
申请日：2016-05-10
CPC分类号： F02C9/18 , F01D5/02 , F01D5/04 , F01D9/04 , F01D25/12 , F02C3/04 , F02C3/05 , F02C3/08 , F02C6/08 , F05D2220/32 , F05D2240/127 , F05D2260/20 , F05D2260/209 , Y02T50/676
摘要： The present disclosure is directed to a system for bleeding air from a compressed gas path of a gas turbine engine. The system includes an impeller positioned at a downstream end of a compressor in the gas turbine engine. The impeller includes an impeller hub, an impeller arm coupled to the impeller hub, and a plurality of circumferentially spaced apart impeller vanes extending radially outwardly from the impeller arm. The impeller arm defines an impeller arm aperture extending therethrough. A vortex spoiler is positioned radially inwardly from the impeller arm and defines a vortex spoiler passage extending radially therethrough. Bleed air flows from the compressed gas path radially inwardly through both the impeller arm aperture and the vortex spoiler passage.
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公开(公告)号：US20160265360A1
公开(公告)日：2016-09-15
申请号：US14656230
申请日：2015-03-12
CPC分类号： F01D5/08 , F01D5/081 , F01D5/082 , F01D5/085 , F01D5/087 , F01D5/088 , F01D9/02 , F01D25/08 , F01D25/12 , F01D25/162 , F02C7/18 , F05D2220/32 , F05D2260/14 , F05D2260/202 , F05D2260/209 , F05D2260/2212 , F05D2270/3062 , Y02T50/676
摘要： A swirler tube is disclosed. A swirler is provided comprising a flange defining a first surface, a tube extending away from the first surface, a flow surface defined by a flange inner surface and a tube inner surface, the flange inner surface having an inlet diameter, and a metering feature disposed on the flow surface, wherein the metering feature is integral to the tube, the metering feature have a metering feature diameter that is less than the inlet diameter.
摘要翻译： 公开了一种旋流管。 提供了一种旋流器，其包括限定第一表面的凸缘，远离第一表面延伸的管，由凸缘内表面和管内表面限定的流动表面，凸缘内表面具有入口直径和设置的计量特征 在流动表面上，其中计量特征与管成一体，计量特征具有小于入口直径的计量特征直径。
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公开(公告)号：US20160208703A1
公开(公告)日：2016-07-21
申请号：US14600862
申请日：2015-01-20
CPC分类号： F02C7/18 , F01D5/081 , F01D5/082 , F01D9/02 , F01D25/12 , F02C3/04 , F02C6/06 , F02C6/08 , F02C7/12 , F02C7/185 , F02C9/18 , F02K3/115 , F05D2260/209 , F05D2260/211 , F05D2260/213 , F05D2300/175 , F23R3/04 , F23R3/045 , Y02T50/676
摘要： A cooling system is provided. The cooling system may comprise a heat exchanger and a first conduit fluidly coupled to an outlet of the heat exchanger. An annular passage may be fluidly coupled to the first conduit. A tangential onboard injector (TOBI) may be fluidly coupled to the annular passage. A gas turbine engine is also provided and may comprise a compressor, a combustor in fluid communication with the compressor, and a diffuser around the combustor and a turbine. A heat exchanger may have an inlet fluidly coupled to the diffuser. A second conduit may be fluidly coupled to an outlet of the heat exchanger. An annular passage may be fluidly coupled to the second conduit. A tangential onboard injector (TOBI) may be fluidly coupled to the annular passage.
摘要翻译： 提供冷却系统。 冷却系统可以包括热交换器和流体耦合到热交换器的出口的第一导管。 环形通道可流体地联接到第一导管。 切向板载喷油器（TOBI）可以流体地联接到环形通道。 还提供燃气涡轮发动机，并且可以包括压缩机，与压缩机流体连通的燃烧器，以及围绕燃烧器和涡轮机的扩散器。 热交换器可以具有流体地联接到扩散器的入口。 第二导管可以流体耦合到热交换器的出口。 环形通道可以流体地联接到第二导管。 切向板载喷油器（TOBI）可以流体地联接到环形通道。
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4.发明申请FLOW GUIDING SYSTEM, TURBO ENGINE WITH A FLOW GUIDING SYSTEM AND METHOD FOR MANUFACTURING A FLOW GUIDING SYSTEM 有权流动引导系统，具有流动引导系统的涡轮发动机和制造流动引导系统的方法公开(公告)号：US20150275759A1
公开(公告)日：2015-10-01
申请号：US14584242
申请日：2014-12-29
CPC分类号： F02C7/057 , F01D17/085 , F01D25/12 , F02C7/04 , F02C7/042 , F02C7/08 , F02C7/14 , F05D2260/209 , Y02T50/676 , Y10T29/49323
摘要： The invention relates to a flow guiding system for a turbo engine, in particular an aircraft engine, characterized by an air intake device taking a thermal management air stream from a free flowing air stream during the operation of the turbo engine and at least one flow guiding means for guiding the thermal management air stream to at least one target region to be thermally managed in the turbo engine. The invention also relates to a turbo engine with a flow guiding system and a method for manufacturing a flow guiding system.
摘要翻译： 本发明涉及一种用于涡轮发动机，特别是飞机发动机的流动引导系统，其特征在于，进气装置在涡轮发动机的运行期间从自由流动的气流中获取热管理空气流，并且至少一个流动引导 用于将热管理空气流引导到在涡轮发动机中进行热管理的至少一个目标区域的装置。 本发明还涉及具有流动引导系统的涡轮发动机和用于制造流动引导系统的方法。
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5.发明授权Stator of a high-pressure turbine of a turbomachine, and a method of assembling it 有权涡轮机的高压涡轮机的定子及其组装方法公开(公告)号：US07360987B2
公开(公告)日：2008-04-22
申请号：US11072280
申请日：2005-03-07
IPC分类号： F01D9/06
CPC分类号： F01D9/042 , F01D25/246 , F01D25/26 , F05D2260/209
摘要： A method of assembling sectored elements of an annular stator of a high-pressure turbine of a turbomachine about a longitudinal axis of said turbine, in which method an angular distribution pattern is defined for distributing elements of the stator over a predetermined angular sector, said pattern being defined so as to prevent inter-sector zones of stator elements being in radial alignment, said zones being defined between two adjacent sectors of the same stator element, and so as to repeat said distribution pattern around the entire circumference of the stator.
摘要翻译： 一种围绕所述涡轮机的纵向轴线组装涡轮机的高压涡轮机的环形定子的分段元件的方法，其中限定了角分布图案，用于在预定的角度扇区上分配定子的元件，所述图案 定义为防止定子元件的扇形间区域处于径向对准，所述区域被限定在相同定子元件的两个相邻扇区之间，并且围绕定子的整个圆周重复所述分布图案。
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公开(公告)号：US4293275A
公开(公告)日：1981-10-06
申请号：US75584
申请日：1979-09-14
CPC分类号： F01D5/187 , F02C7/185 , F05D2240/81 , F05D2260/209
摘要： A blade cooling construction comprising a cylindrical hollow and a nozzle, both of which are defined in and by the blade. The hollow and nozzle create a vortex of cooling gas introduced into the blade, which gas whirls about the axis of the hollow by tangentially injecting the cooling gas into the hollow through the nozzle. A portion of the cooling gas is lowered in temperature, and the other portion is raised in temperature. The lower temperature cooling gas is introduced first to a central portion of the blade height which is higher in temperature than the remaining portions of the blade. The higher temperature cooling gas is introduced to a lower temperature portion of the blade.
摘要翻译： 叶片冷却结构包括圆柱形中空和喷嘴，两者均被叶片限定在叶片中。 中空和喷嘴产生引入叶片的冷却气体的涡流，该气体通过将冷却气体通过喷嘴切向注入中空部而围绕中空轴线旋转。 一部分冷却气体的温度降低，另一部分温度上升。 首先将较低温度的冷却气体引入叶片高度的中心部分，其温度高于叶片的其余部分。 较高温度的冷却气体被引入叶片的较低温度部分。
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公开(公告)号：US10018116B2
公开(公告)日：2018-07-10
申请号：US13366450
申请日：2012-02-06
CPC分类号： F02C6/08 , F01D5/082 , F01D5/085 , F01D25/16 , F01D25/183 , F02C7/185 , F05D2260/209 , F05D2260/213 , F05D2260/4031 , Y02T50/676
摘要： A gas turbine engine includes a first zone and a second zone downstream from the first zone. A buffer system can communicate a buffer cooling air to at least the first zone. A bleed source can communicate a bleed air to the second zone.
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公开(公告)号：US20180023595A1
公开(公告)日：2018-01-25
申请号：US15215373
申请日：2016-07-20
CPC分类号： F04D29/701 , B01D45/12 , B04C3/06 , F01D5/085 , F01D25/12 , F02C6/08 , F02C7/052 , F04D17/02 , F05D2220/32 , F05D2260/209
摘要： The present disclosure generally relates to separating solid particles from an airflow in a gas turbine engine. A separator includes a plurality of vortex chambers arranged about a longitudinal axis of the gas turbine engine, each vortex chamber having a clean air outlet at a first end, a dirty outlet at a second end, and an air inlet transverse to the vortex chamber located at the first end. The separator also includes a sealable collection chamber in fluid communication with the dirty outlet of the each of the plurality of vortex chambers.
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公开(公告)号：US20170167381A1
公开(公告)日：2017-06-15
申请号：US14969566
申请日：2015-12-15
发明人： Bradley T. Duelm
CPC分类号： F02C7/12 , F01D5/187 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/11 , F05D2240/81 , F05D2250/20 , F05D2260/209 , F05D2260/2212 , F05D2260/22141
摘要： A gas turbine engine component includes a body defining a cooling airflow passage thereat configured for directing a cooling airflow therethrough. A plurality of turbulators are positioned at at least one passage wall of the cooling airflow channel. Each turbulator of the plurality of turbulators includes a plurality of facets extending outwardly from a central portion. A gas turbine engine includes a combustor and a plurality of gas turbine engine components positioned in fluid communication with the combustor. Each component includes a body defining a cooling airflow passage thereat configured for directing a cooling airflow therethrough. A plurality of turbulators are located at at least one passage wall of the cooling airflow channel, each turbulator of the plurality of turbulators including a plurality of facets extending outwardly from a central portion.
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公开(公告)号：US20160237852A1
公开(公告)日：2016-08-18
申请号：US15023309
申请日：2014-09-18
发明人： Dmitriy A. Romanov
CPC分类号： F01D25/12 , F01D11/08 , F01D11/24 , F05D2220/32 , F05D2230/211 , F05D2240/11 , F05D2240/12 , F05D2240/30 , F05D2250/15 , F05D2250/25 , F05D2260/202 , F05D2260/204 , F05D2260/209 , F05D2260/2214 , F05D2260/22141 , Y02T50/676
摘要： One exemplary embodiment of this disclosure relates to a gas turbine engine including a component having a body. The body includes a tortuous cooling passageway, which provides a flow path extending between an inlet in a first surface of the body and an exit in a second surface of the body.
摘要翻译： 本公开的一个示例性实施例涉及一种包括具有主体的部件的燃气涡轮发动机。 主体包括一个曲折的冷却通道，其提供在主体的第一表面中的入口与主体的第二表面中的出口之间延伸的流动路径。
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