公开(公告)号：US09328616B2

公开(公告)日：2016-05-03

申请号：US13756653

申请日：2013-02-01

申请人： Andreas Heselhaus

发明人： Andreas Heselhaus

IPC分类号： F01D5/18

CPC分类号： F01D5/186 ,  F05D2260/209 ,  F05D2260/2212

摘要： A turbine blade for a turbomachine has an outer wall which delimits an inner cavity. Cooling fluid flows in the inner cavity. A through duct is arranged in the outer wall through which the cooling fluid flows from the inner cavity to an outside of the turbine blade. The through duct is inclined with respect to a trailing edge of the turbine blade, wherein a marginal portion of an entrance of the through duct is designed on an upstream side to be sharp-edged in relation to other marginal portions of the entrance such that a separation zone of a cooling fluid flow is formed in the through duct. A pair of swirls builds up in the through duct, wherein velocity vectors of the cooling fluid flow between the swirl centers point toward a downstream side of the through duct.

摘要翻译： 用于涡轮机的涡轮机叶片具有限定内腔的外壁。 冷却液在内腔中流动。 通气管布置在外壁中，冷却流体通过该外壁从内腔流到涡轮叶片的外部。 贯通管道相对于涡轮机叶片的后缘倾斜，其中贯通管道入口的边缘部分被设计在相对于入口的其它边缘部分被锐化的上游侧，使得 在通气管中形成冷却流体流的分离区。 在通气管中形成一对漩涡，其中冷却流体在涡流中心之间流动的速度矢量指向通过管道的下游侧。

公开(公告)号：US20130192253A1

公开(公告)日：2013-08-01

申请号：US13366450

申请日：2012-02-06

申请人： William K. ACKERMANN ,  Philip S. STRIPINIS

发明人： William K. ACKERMANN ,  Philip S. STRIPINIS

IPC分类号： F02C6/08

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.

摘要翻译： 燃气涡轮发动机包括第一区域和在第一区域下游的第二区域。 缓冲系统可以将缓冲冷却空气传送到至少第一区域。 泄放源可以将排出的空气传送到第二区域。

公开(公告)号：US20190211683A1

公开(公告)日：2019-07-11

申请号：US15864925

申请日：2018-01-08

申请人： UNITED TECHNOLOGIES CORPORATION

发明人： Matthew E. Bintz ,  Enzo DiBenedetto ,  Paul E. Coderre

IPC分类号： F01D5/08 ,  F02C7/18 ,  F02C7/141 ,  F01D5/06

CPC分类号： F01D5/087 ,  F01D5/06 ,  F01D11/001 ,  F01D11/02 ,  F02C7/141 ,  F02C7/18 ,  F04D29/321 ,  F04D29/582 ,  F05D2210/12 ,  F05D2220/3218 ,  F05D2220/3219 ,  F05D2240/11 ,  F05D2240/12 ,  F05D2240/24 ,  F05D2240/55 ,  F05D2260/20 ,  F05D2260/209 ,  F05D2260/213

摘要： A gas turbine engine is disclosed. The gas turbine engine includes a first rotor supporting a first plurality of circumferentially spaced rotor blades and a second rotor disposed axially downstream of the first rotor and supporting a second plurality of circumferentially spaced rotor blades, a first bore cavity between the first rotor and the second rotor, a first fluid passageway configured to provide cooled air to the first bore cavity and a first anti-vortex component positioned proximate the first bore cavity and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the first bore cavity.

公开(公告)号：US09896939B2

公开(公告)日：2018-02-20

申请号：US14656230

申请日：2015-03-12

申请人： United Technologies Corporation

发明人： Alberto A. Mateo ,  Anthony P. Cherolis

IPC分类号： F01D5/08 ,  F01D25/12 ,  F01D25/16 ,  F02C7/18 ,  F01D9/02 ,  F01D25/08

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.

公开(公告)号：US09719424B2

公开(公告)日：2017-08-01

申请号：US14584242

申请日：2014-12-29

申请人： Rolls-Royce Deutschland Ltd & Co KG

发明人： Luis Daniel Teia Dos Santos Mendes Gomes

IPC分类号： F02C7/057 ,  F01D17/08 ,  F01D25/12 ,  F02C7/042 ,  F02C7/14 ,  F02C7/04 ,  F02C7/08

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.

公开(公告)号：US20080314019A1

公开(公告)日：2008-12-25

申请号：US11984472

申请日：2007-11-19

申请人： Annegret W. Siebert

发明人： Annegret W. Siebert

IPC分类号： F02K11/00

CPC分类号： F02C7/16 ,  B64D29/00 ,  F05D2260/208 ,  F05D2260/209 ,  Y02T50/675

摘要： Cavities 4 are defined within an engine nacelle 1 with an inner surface 2 and an outer surface 3. Within these cavities 4, an evaporatable liquid 5 is arranged such that a proportion of the liquid 5 is in a gaseous phase in order to facilitate heat transfer between the inner surface 2 or the outer surface 3 and a hot surface. The liquid condenses upon the inner surface 2 or the outer surface 3 and collects into a pool for subsequent further evaporation by the hot surface of an insulated gate bi-polar transistor or convertor/generator components in order to facilitate further cooling of electric components housed or arranged in the nacelle 1 or nearby.

摘要翻译： 空腔4限定在具有内表面2和外表面3的发动机舱1内。在这些空腔4内，布置可蒸发的液体5，使得一部分液体5处于气相以促进热传递 在内表面2或外表面3之间和热表面之间。 液体在内表面2或外表面3上冷凝并收集到池中，以便随后由绝缘栅极双极晶体管或转换器/发生器部件的热表面进一步蒸发，以便于进一步冷却所容纳的或 安排在机舱1或附近。

公开(公告)号：US20050238477A1

公开(公告)日：2005-10-27

申请号：US11072280

申请日：2005-03-07

申请人： Anne-Marie Arraitz ,  Thierry Fachat ,  Jerome Friedel ,  Alain Gendraud ,  Delphine Roussin

发明人： Anne-Marie Arraitz ,  Thierry Fachat ,  Jerome Friedel ,  Alain Gendraud ,  Delphine Roussin

IPC分类号： F01D25/24 ,  F01D9/04 ,  F01D11/24 ,  F01D25/08 ,  F02C7/00 ,  F01D1/00

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。

公开(公告)号：US3973396A

公开(公告)日：1976-08-10

申请号：US515174

申请日：1974-10-16

申请人： Sven-Olof Kronogard

发明人： Sven-Olof Kronogard

IPC分类号： F02C7/18 ,  F25B9/04 ,  F02C7/08 ,  F25B9/02

CPC分类号： F02C7/18 ,  F02C7/185 ,  F25B9/04 ,  F05D2260/209

摘要： The cooling of a gas turbine is a critical problem and will consume a considerable quantity of compressed air at the temperature ordinarily available. To improve the cooling properties, a portion of the air delivered by the compressor is divided off and is conveyed to an expansion member, where it is further divided into a hot and a cold fraction. This cold fraction, which can have a temperature well below the freezing point, is used, preferably mixed with air delivered directly from the compressor, for cooling the turbine inlet means.

摘要翻译： 燃气轮机的冷却是关键问题，并且在通常可用的温度下将消耗相当数量的压缩空气。 为了提高冷却性能，由压缩机输送的空气的一部分被分离并被输送到膨胀构件，在该膨胀构件中进一步分为热和冷部分。 使用可以具有远低于凝固点的温度的这种冷部分，优选与直接从压缩机输送的空气混合，以冷却涡轮机入口装置。

公开(公告)号：US20180216852A1

公开(公告)日：2018-08-02

申请号：US15887978

申请日：2018-02-02

申请人： James Thomas Clements

发明人： James Thomas Clements

IPC分类号： F25B9/04 ,  F04D25/16 ,  F04D25/08 ,  F01D25/12

CPC分类号： F25B9/04 ,  F01D25/12 ,  F04D19/002 ,  F04D25/04 ,  F04D25/08 ,  F04D25/166 ,  F05D2210/12 ,  F05D2260/209

摘要： Embodiments are provided for a cooling fan that has a vortex tube, an air turbine, and one or more fan blades. The vortex tube is capable of being supplied with compressed air and splitting the compressed air into a cold stream and a hot stream. The cold stream can spins said air turbine with attached fan blades, causing said fan blades to spin and blow cold air.

公开(公告)号：US20160076379A1

公开(公告)日：2016-03-17

申请号：US14851912

申请日：2015-09-11

申请人： United Technologies Corporation

发明人： Matthew P. Forcier ,  Paul J. Hiester

IPC分类号： F01D5/08

CPC分类号： F01D5/081 ,  F02C6/08 ,  F02C9/18 ,  F04D29/321 ,  F04D29/584 ,  F05D2260/209

摘要： A turbomachine includes an aft stage including a rotor disk having a rotor disk bore hole and a rotor disk rim, and a valve disposed within the turbomachine and in fluid communication with the rotor disk bore hole. The valve is in selective fluid communication with a first pressure source such that, in an first position, the valve allows fluid to flow from the first pressure source through the rotor disk bore hole and radially outward along the aft rotor disk toward the aft rotor disk rim.

摘要翻译： 涡轮机包括后台，其包括具有转子盘孔和转子盘轮缘的转子盘，以及设置在涡轮机内并与转子盘钻孔流体连通的阀。 阀与第一压力源选择性地流体连通，使得在第一位置，阀允许流体从第一压力源流过转子盘钻孔并且沿着后转子盘朝向后转子盘径向向外流动 轮缘。