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1. 发明申请

US20180363678A1 INLET PRE-SWIRL GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20180363678A1
公开(公告)日：2018-12-20
申请号：US15625212
申请日：2017-06-16
申请人： General Electric Company
发明人： Christopher James Kroger , Brandon Wayne Miller , Trevor Wayne Goerig , David William Crall , Tsuguji Nakano , Jeffrey Donald Clements , Bhaskar Nanda Mondal
IPC分类号： F04D29/56 , F04D29/54 , F04D29/68
CPC分类号： F04D29/563 , F01D9/041 , F02C3/04 , F02C7/04 , F02K3/06 , F04D29/542 , F04D29/545 , F04D29/684 , F05D2220/32 , F05D2240/12 , F05D2240/122 , F05D2250/182 , F05D2250/184 , F05D2260/14
摘要： A gas turbine engine includes a turbomachine and a fan rotatable by the turbomachine. The fan includes a plurality of fan blades, each of the plurality of fan blades defining a fan blade span along a radial direction. The gas turbine engine further includes an outer nacelle surrounding the plurality of fan blades and a plurality of part-span inlet guide varies attached to the outer nacelle at a location forward of the plurality of fan blades along an axial direction. Each of the plurality of inlet guide vanes defines an IGV span along the radial direction, the IGV span being at least about five percent of the fan blade span and up to about fifty-five percent of the fan blade span.

2. 发明授权

US09896939B2 Integral metering feature, systems and methods 有权
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.

3. 发明申请

US20170370361A1 INLET SYSTEM FOR A RADIAL COMPRESSOR WITH A WIDE FLOW RANGE REQUIREMENT 审中-公开
公开(公告)号：US20170370361A1
公开(公告)日：2017-12-28
申请号：US15630768
申请日：2017-06-22
申请人： Steven Don Arnold
发明人： Steven Don Arnold
IPC分类号： F04C29/12 , F02B37/14 , F02B33/30 , F04D29/28 , F01D5/04
CPC分类号： F04C29/122 , F01D5/043 , F02B33/30 , F02B37/14 , F04D17/10 , F04D29/284 , F04D29/4213 , F05D2260/14 , Y02T10/144
摘要： A radial compressor employs a compressor wheel having an inducer. An inlet air passage has a first region and a second region separated from the first region by a divider wall. The divider wall extends from an inlet plane of the inducer and connects the first region to a first air filter and said second region to a second air filter.

4. 发明申请

US20170298739A1 Bolt On Seal Ring 审中-公开
公开(公告)号：US20170298739A1
公开(公告)日：2017-10-19
申请号：US15130042
申请日：2016-04-15
申请人： Siemens Energy, Inc.
发明人： Chirag B. Patel , Michael Skarbowski , Kevin M. Light , William J. Curtin
IPC分类号： F01D5/08 , F01D11/00
CPC分类号： F01D5/085 , F01D11/00 , F01D11/001 , F05D2220/32 , F05D2260/14 , F05D2260/20
摘要： A device to route cooling air to a turbine blade is provided. The device includes a seal ring having an L-shaped cross section configured to abut a turbine disc. The seal ring includes a radial portion extending radially with respect to a rotor and an axial portion extending axially with respect to the rotor. The seal ring also includes a plurality of radial cooling holes disposed within the radial portion of the seal ring and arranged circumferentially around the seal ring. The plurality of cooling holes route cooling air from a device configured to impart tangential momentum to the cooling air to a turbine blade in order to cool the turbine blade. A system and a method to improve a flow of rotor cooling air to a turbine blade are also provided.

5. 发明申请

US20170089263A1 TURBINE ENGINE ADVANCED COOLING SYSTEM 审中-公开
公开(公告)号：US20170089263A1
公开(公告)日：2017-03-30
申请号：US14871382
申请日：2015-09-30
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies Inc.
发明人： Joseph Clegg , Craig English , Behram Kapadia , Kenneth M. Pesyna , Jason Lee Swindle , Jason Wayne Rector , Christopher Vincent , Nicholas D. Metzger , Daniel G. Edwards
IPC分类号： F02C7/12 , F02C7/24 , F04D29/58 , F01D25/12 , F04D29/32 , F02C3/04 , F01D5/02
CPC分类号： F02C7/12 , F01D5/02 , F01D5/046 , F01D5/08 , F01D5/081 , F01D5/082 , F01D25/08 , F01D25/12 , F02C3/04 , F02C6/08 , F02C7/18 , F02C7/185 , F02C7/24 , F04D29/321 , F04D29/582 , F05D2220/32 , F05D2240/12 , F05D2240/15 , F05D2240/35 , F05D2240/60 , F05D2260/14 , F05D2260/20 , F05D2260/205 , F05D2260/231
摘要： A cooling system for a gas turbine is provided that may include a drive shaft, a shield of a combustor of the gas turbine engine, and a conduit. The drive shaft may be configured to mechanically couple a compressor of the gas turbine engine to a turbine of the gas turbine engine. The shield may be positioned between the compressor and the turbine. The combustor may be configured to drive the turbine. The conduit may be configured to supply a cooling fluid to a gap between an outer surface of the drive shaft and the shield of the combustor.

6. 发明申请

US20160305248A1 TURBINE COOLING 审中-公开
标题翻译：涡轮冷却
公开(公告)号：US20160305248A1
公开(公告)日：2016-10-20
申请号：US15082416
申请日：2016-03-28
申请人： ROLLS-ROYCE plc
发明人： Keith C. SADLER , Frederic GOENAGA , Andrew J. MYLREA
IPC分类号： F01D5/08 , F01D25/12
CPC分类号： F01D5/082 , F01D5/081 , F01D25/12 , F05D2260/14 , F05D2260/20
摘要： A coolant feed arrangement for delivering coolant to an axially facing surface of a rotor disc configured for carrying a row of turbine blades on its radially outer surface, the coolant delivered through a conduit upstream of the rotor disc, which has an outlet arranged radially inwardly of the blades and directed at the axially facing surface, the arrangement including two or more impediments; at least one impediment including a work extractor device arranged in the conduit to extract work from the coolant on route to a last impediment arranged at or adjacent the outlet, the last impediment including a row of static nozzles configured for accelerating the flow of coolant circumferentially in the direction of rotation of the axially facing surface of the disc whereby to match the speed and direction of rotation of the axially facing surface as the coolant is delivered to the axially facing surface.
摘要翻译：一种冷却剂供给装置，用于将冷却剂输送到转子盘的面向轴向的表面，所述转子盘构造成用于在其径向外表面上承载一排涡轮叶片，所述冷却剂通过转子盘上游的导管输送，叶片并且指向轴向面向的表面，该装置包括两个或更多个障碍物; 至少一个障碍物，其包括布置在导管中的工作提取器装置，用于在布置在出口处或邻近出口处的路线上从冷却剂中提取工作，最后一个障碍物包括一排静止喷嘴，其被配置用于加速周向冷却剂中的冷却剂流盘的轴向面向表面的旋转方向，从而当冷却剂被输送到面向轴向的表面时，以匹配轴向面向表面的旋转速度和方向。

7. 发明申请

US20160195017A1 Recuperated Gas Turbine Engine 审中-公开
标题翻译：再生燃气轮机发动机
公开(公告)号：US20160195017A1
公开(公告)日：2016-07-07
申请号：US14849556
申请日：2015-09-09
申请人： Michael J. Vick
发明人： Michael J. Vick
IPC分类号： F02C7/10 , F02C7/052 , F02C7/22 , F02C3/14
CPC分类号： F02C7/10 , F01D5/284 , F02C1/10 , F02C3/14 , F02C7/052 , F02C7/08 , F02C7/22 , F05D2220/32 , F05D2220/764 , F05D2220/766 , F05D2250/80 , F05D2260/14 , Y02E20/14 , Y02T50/672 , Y02T50/673
摘要： A gas turbine engine that includes a compressor, a turbine, a heat exchanger, and a combustor. The compressor is mounted on a rotating shaft with at least one rotor with an inlet and an outlet, and at least one diffuser downstream from each rotor. The turbine includes at least one stator, and at least one rotor with an inlet and outlet located downstream of each stator, and mounted on the rotating shaft as the at least one of the compressor rotors. The inlet of the compressor rotor faces toward the outlet of the turbine rotor. The heat exchanger is configured to preheat the compressed air leaving the compressor by transferring heat from the turbine exhaust. The combustor can be configured for mixing fuel with the compressed air, either upstream or downstream from the heat exchanger, and further configured for igniting the preheated fuel/air mixture located downstream from the heat exchanger.
摘要翻译：一种燃气涡轮发动机，其包括压缩机，涡轮机，热交换器和燃烧器。压缩机安装在具有至少一个具有入口和出口的转子的旋转轴上，并且至少一个扩散器在每个转子的下游。涡轮机包括至少一个定子和至少一个转子，其具有位于每个定子下游的入口和出口，并且安装在作为至少一个压缩机转子的旋转轴上。压缩机转子的入口面向涡轮转子的出口。热交换器被配置为通过从涡轮排气传递热量来预热离开压缩机的压缩空气。燃烧器可以被配置为将燃料与压缩空气混合，在热交换器的上游或下游，并进一步构造成用于点燃位于热交换器下游的预热的燃料/空气混合物。

8. 发明申请

US20160177833A1 ENGINE AND METHOD FOR OPERATING SAID ENGINE 审中-公开
标题翻译：发动机和操作发动机的方法
公开(公告)号：US20160177833A1
公开(公告)日：2016-06-23
申请号：US14979152
申请日：2015-12-22
申请人： General Electric Technology GmbH
发明人： Carlos SIMON-DELGADO , Oliver Joseph TAHENY , Sven OLMES , Armin BUSEKROS , Luca ALBERTI , Daniel JEMORA , Eugenio ROSSI , Christophe SIMONET
IPC分类号： F02C7/18 , F01D5/08 , F01D9/02 , F02C3/06
CPC分类号： F02C7/185 , F01D5/084 , F01D5/085 , F01D9/02 , F01D11/001 , F01D25/12 , F02C3/06 , F02C6/08 , F04D29/321 , F04D29/544 , F05D2260/14 , F05D2260/201 , F05D2260/232 , Y02T50/676
摘要： Disclosed is an engine, the engine having a compressor, an expansion machine, and a shaft, the shaft having a direction of rotation. The engine includes a compressed fluid main flow path, a flow divider arranged at and fluidly connected to the compressed fluid main flow path, and a duct fluidly connecting the flow divider and components of the expansion machine. The duct is arranged such that, when the engine is operated, a fluid is guided through the duct from the flow divider towards the expansion machine components. A flow deflector device is arranged within a flow path and configured to deflect and thereby accelerate a flow therethrough directed form the flow divider towards the expansion machine components in a tangential direction, wherein the deflection can be effected into the shaft direction of rotation.
摘要翻译：公开了一种发动机，具有压缩机，膨胀机和轴的发动机，该轴具有旋转方向。发动机包括压缩流体主流路，布置在流体连接到压缩流体主流路的流动分配器和流体连接分流器和膨胀机组件的导管。管道被布置成使得当发动机被操作时，流体从分流器朝向膨胀机部件被引导通过管道。导流装置布置在流动路径内并且构造成偏转并从而加速从切向方向朝向膨胀机构件的流动分流器指向的流动，其中偏转可以进入轴的旋转方向。

9. 发明申请

US20160177831A1 COOLING-AIR SUPPLY DEVICE FOR A GAS TURBINE 审中-公开
标题翻译：用于气体涡轮机的冷却空气供应装置
公开(公告)号：US20160177831A1
公开(公告)日：2016-06-23
申请号：US14972767
申请日：2015-12-17
申请人： MTU Aero Engines AG
发明人： Stefan Sasse , Erwin Bayer
IPC分类号： F02C7/18 , F01D25/24 , F01D5/02 , F02C3/04
CPC分类号： F02C7/18 , F01D5/02 , F01D5/082 , F01D25/24 , F02C3/04 , F05D2220/3213 , F05D2230/54 , F05D2240/35 , F05D2240/61 , F05D2260/14 , F05D2260/20 , F05D2260/201 , F05D2300/6033 , F05D2300/702 , Y02T50/672 , Y02T50/676
摘要： A cooling-air supply device for a gas turbine, in particular an aircraft gas turbine, including a cooling air chamber, that is disposed about a turbine shaft of the gas turbine, at least one cooling-air inlet opening, and at least one cooling-air outlet orifice; the cooling-air supply device having a first and a second axial bounding wall, and a peripheral wall that joins the two axial bounding walls, which, together, form the cooling air chamber; in at least one of the axial bounding walls, a plurality of cooling-air outlet orifices being provided, which are circumferentially distributed about the turbine shaft and are adapted to allow the cooling air to essentially be discharged from the individual cooling-air outlet orifices in the direction of rotation of the gas turbine. In the axial direction, the respective axial bounding wall having the cooling-air outlet orifices has a layer-type structure; the cooling-air outlet orifices being formed by deformation of at least one first cooling air chamber-side layer and by deformation of at least one second, turbine-side layer.
摘要翻译：一种用于燃气轮机的冷却空气供应装置，特别是包括冷却空气室的飞机燃气轮机，其设置在燃气轮机的涡轮机轴周围，至少一个冷却空气入口，以及至少一个冷却出口孔; 所述冷却空气供应装置具有第一和第二轴向边界壁，以及连接两个轴向边界壁的周壁，所述两个轴向边界壁一起形成冷却空气室; 在轴向边界壁中的至少一个中，设置有多个冷却空气出口孔，其周向分布在涡轮轴上并且适于允许冷却空气基本上从单独的冷却空气出口孔排出燃气轮机的旋转方向。在轴向方向上，具有冷却空气出口孔的相应轴向边界壁具有层型结构; 所述冷却空气出口孔由至少一个第一冷却空气室侧层的变形和至少一个第二涡轮机侧层的变形形成。

10. 发明授权

US09181816B2 Seal assembly including grooves in an aft facing side of a platform in a gas turbine engine 有权
标题翻译：密封组件包括在燃气涡轮发动机中的平台的面向后方的槽
公开(公告)号：US09181816B2
公开(公告)日：2015-11-10
申请号：US14189227
申请日：2014-02-25
申请人： Siemens Aktiengesellschaft
发明人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Erik Johnson , Dustin Muller , Steven Coppess , Manjit Shivanand , Kahwai G. Muriithi
IPC分类号： F01D11/00 , F01D11/02
CPC分类号： F01D11/001 , F01D11/02 , F05D2240/80 , F05D2250/37 , F05D2250/38 , F05D2250/71 , F05D2260/14
摘要： A seal assembly between a disc cavity and a hot gas path in a gas turbine engine includes a stationary vane assembly and a rotating blade assembly axially upstream from the vane assembly. A platform of the blade assembly has a radially outwardly facing first surface, an axially downstream facing second surface defining an aft plane, and a plurality of grooves extending into the second surface such that the grooves are recessed from the aft plane The grooves are arranged such that a circumferential space is defined between adjacent grooves During operation of the engine, the grooves impart a circumferential velocity component to purge air flowing out of a disc cavity through the grooves to guide the purge air toward a hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.
摘要翻译：燃气涡轮发动机中的盘腔和热气路之间的密封组件包括固定叶片组件和在叶片组件的轴向上游的旋转叶片组件。叶片组件的平台具有径向向外的第一表面，限定了后平面的轴向下游的第二表面，以及延伸到第二表面中的多个凹槽，使得凹槽从后平面凹陷。凹槽被布置成在相邻槽之间限定周向空间在发动机工作期间，槽赋予圆周速度分量，以通过槽吹扫从盘腔流出的空气，以将吹扫空气引向热气路径，使得吹扫空气流动相对于热气体流过热气体路径的方向在期望的方向上。

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