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公开(公告)号：US20170101896A1
公开(公告)日：2017-04-13
申请号：US15314341
申请日：2015-05-28
发明人： Robert Francis MANNING , Timothy Deryck STONE , Jared Peter BUHLER , Victor Hugo Silva CORREIA , Gregory Michael LASKOWSKI , Robert Carl MURRAY , Jonathan Russell RATZLAFF , Robert PROCTOR , John Howard STARKWEATHER , Curtis Walton STOVER
CPC分类号： F01D25/32 , B01D45/16 , B04C3/00 , B04C3/06 , B04C2003/003 , B04C2003/006 , B64D33/08 , B64D2033/022 , B64D2033/024 , B64D2033/0246 , F01D5/08 , F01D25/12 , F02C3/04 , F02C7/05 , F02C7/052 , F02C7/18 , F02C9/18 , F05D2220/32 , F05D2240/35
摘要： A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser configured to increase the angular velocity of a fluid stream, a flow splitter configured to split the fluid stream to form a concentrated-particle stream and a reduced-particle stream, and an exit conduit configured to receive the reduced-particle stream. An inducer assembly for a turbine engine includes an inducer with a flow passage having an inducer inlet and an inducer outlet in fluid communication with a turbine section of the engine, and a particle separator, which includes a particle concentrator that receives a compressed stream from a compressor section of the engine and a flow splitter. A turbine engine includes a cooling air flow circuit which supplies a fluid stream to a turbine section of the engine for cooling, a particle separator located within the cooling air flow circuit, and an inducer forming a portion of the cooling air flow circuit in fluid communication with the particle separator. A method of cooling a rotating blade of a turbine engine having an inducer includes directing a cooling fluid stream from a portion of turbine engine toward the rotating blade, separating particles from the cooling fluid stream by passing the cooling fluid stream through a inertial separator, accelerating a reduced-particle stream emitted from the inertial separator to the speed of the rotating blade, and orienting the reduced-particle stream by emitting the reduced-particle stream from the inertial separator into a cooling passage in the inducer.
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公开(公告)号：US20170101893A1
公开(公告)日：2017-04-13
申请号：US15128492
申请日：2014-05-08
申请人： Siemens Energy, Inc.
CPC分类号： F01D25/12 , F01D5/08 , F01D5/18 , F01D5/187 , F01D5/188 , F01D9/041 , F05D2220/32 , F05D2240/123 , F05D2240/124 , F05D2250/185 , F05D2260/221 , F05D2260/2214 , F05D2260/22141
摘要： A turbine airfoil including a central cavity defined by an outer wall including pressure and suction sides extending between and joined at leading and trailing edges, and a chordal axis extends generally centrally between the pressure and suction sides. Rib structures located in the central cavity define radial central channels extending across the chordal axis. Radial near wall passages are defined between the rib structures and each of the pressure and suction sides of the outer wall. The radial near wall passages are each open to an adjacent central channel along a radial extent of both the near wall passages and the adjacent central channel to define a radial flow pass associated with each central channel. The flow passes are connected in series to form a serpentine cooling path extending in the direction of the chordal axis.
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公开(公告)号：US20160230563A1
公开(公告)日：2016-08-11
申请号：US14616999
申请日：2015-02-09
CPC分类号： F01D5/187 , F01D5/08 , F01D5/18 , F01D5/186 , F01D5/188 , F01D9/065 , F05D2230/30 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , Y02T50/676
摘要： A. structure for creating a core for a gas turbine engine component comprises a body with a curved surface defining a turn passage. A plurality of protrusions are formed within a wall surface of the turn passage. A plurality of protrusions are configured to extend transversely relative to the curved surface. A gas turbine engine component is also disclosed.
摘要翻译： A.用于产生燃气涡轮发动机部件的核心的结构包括具有限定转向通道的弯曲表面的主体。 在转向通道的壁面内形成有多个突起。 多个突起构造成相对于弯曲表面横向延伸。 还公开了一种燃气轮机发动机部件。
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公开(公告)号：US20160215625A1
公开(公告)日：2016-07-28
申请号：US14603318
申请日：2015-01-22
CPC分类号： F01D5/147 , F01D5/08 , F01D5/081 , F01D5/082 , F01D5/085 , F01D5/087 , F01D5/14 , F01D11/001 , F01D11/006 , F01D11/02 , F05D2220/32 , F05D2240/30 , F05D2240/55 , F05D2240/80
摘要： Embodiments of the invention relate generally to rotary machines and, more particularly, to the control of wheel space purge air in gas turbines. In one embodiment, the invention provides a turbine bucket comprising: a platform portion; an airfoil extending radially outward from the platform portion; a shank portion extending radially inward from the platform portion; at least one angel wing extending axially from a face of the shank portion, the at least one angel wing including an angel wing rim extending radially upward toward the airfoil; and a plurality of voids disposed along the angel wing rim.
摘要翻译： 本发明的实施例一般涉及旋转机械，更具体地，涉及在燃气涡轮机中控制车轮间隙吹扫空气。 在一个实施例中，本发明提供一种涡轮机桶，包括：平台部分; 从平台部分径向向外延伸的翼型件; 从所述平台部分径向向内延伸的柄部; 至少一个天使翼从所述柄部的表面轴向延伸，所述至少一个天使翼包括朝向翼型件径向向上延伸的天使翼缘; 以及沿天使翼缘设置的多个空隙。
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公开(公告)号：US20160208712A1
公开(公告)日：2016-07-21
申请号：US14598252
申请日：2015-01-16
CPC分类号： F02C9/16 , F01D5/08 , F01D25/10 , F02C3/04 , F02C9/18 , F05D2260/232 , F05D2260/941 , F05D2270/303 , Y02T50/676
摘要： A gas turbine engine comprises a compressor rotor including blades and a disk, with a bore defined radially inwardly of the disk, and a combustor. A tap directs the products of combustion first to a valve and then into the bore of the disk. At least two temperature sensors sense a temperature of the products of combustion downstream of the valve. A control compares sensed temperatures from the at least two temperature sensors to ensure the at least two temperature sensors are functioning properly. The sensed temperatures are utilized to control the valve. A method of operating a gas turbine engine is also disclosed.
摘要翻译： 燃气涡轮发动机包括具有叶片和盘的压缩机转子，其具有径向向内定位在盘的内部的孔和燃烧器。 龙头将燃烧产物首先引导到阀门，然后进入盘孔。 至少两个温度传感器感测阀下游燃烧产物的温度。 控制器比较来自至少两个温度传感器的感测温度，以确保至少两个温度传感器正常工作。 感测到的温度用于控制阀门。 还公开了一种操作燃气涡轮发动机的方法。
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公开(公告)号：US09359898B2
公开(公告)日：2016-06-07
申请号：US13450791
申请日：2012-04-19
CPC分类号： F01D5/08 , F01D11/24 , F01D25/10 , Y02T50/676
摘要： A system includes a turbomachine. The turbomachine includes at least one rotor disk. The system also includes a rotor disk heating system configured to resistively heat at least a portion of the at least one rotor disk via an electrical current or voltage applied to the portion of the at least one rotor disk.
摘要翻译： 系统包括涡轮机。 涡轮机包括至少一个转子盘。 该系统还包括转子盘加热系统，其被配置为通过施加到至少一个转子盘的部分的电流或电压来电阻加热至少一个转子盘的至少一部分。
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公开(公告)号：US20150322795A1
公开(公告)日：2015-11-12
申请号：US14132421
申请日：2013-12-18
发明人： David J. Thomas , Ted J. Freeman
CPC分类号： F01D5/08 , F01D5/188 , F01D5/284 , F01D5/288 , F01D25/08 , F05D2230/90 , F05D2260/231 , F05D2300/6033 , F05D2300/611
摘要： A gas turbine engine component includes an insulating coating that is adhered to a surface of the component that permits the components to operate at higher temperatures with reduced thermal stress. The coating can be selectively applied to one or more portions of a part feature where, in some embodiments, the part feature may include a portion that does not include the coating. The part feature can include recognized features of a component such as an interior surface of a hollow component, a back side of a blade track, a cooling hole passage, etc.
摘要翻译： 燃气涡轮发动机部件包括粘附到部件的表面的绝缘涂层，其允许部件在较低温度下以较低的热应力运行。 涂层可以选择性地施加到零件特征的一个或多个部分，其中在一些实施例中，零件特征可以包括不包括涂层的部分。 部件特征可以包括诸如中空部件的内表面，叶片轨道的后侧，冷却孔通道等的部件的识别的特征。
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公开(公告)号：US20150226073A1
公开(公告)日：2015-08-13
申请号：US14425012
申请日：2013-08-22
发明人： Stephen Batt , Richard Bluck , David Butler
CPC分类号： F01D9/023 , F01D1/04 , F01D5/08 , F01D5/14 , F01D5/18 , F01D5/288 , F01D9/04 , F01D9/041 , Y10T29/49321
摘要： A guide vane arrangement of a gas turbine and a method of manufacturing a guide vane arrangement of a gas turbine are provided herein. The guide vane arrangement includes a first guide vane device including a first radially inner platform and a first number of first airfoils, and a second guide vane device including a second radially inner platform and a second number of second airfoils. The first guide vane device and the second guide vane device are arranged along a circumferential direction of the turbine, wherein the first number of the first airfoils differs to the second number of the second airfoils. The first guide vane device is designed with a higher heat resistance than the second guide vane device.
摘要翻译： 本发明提供一种燃气轮机的导向叶片装置及燃气轮机的导向叶片装置的制造方法。 导叶装置包括第一导叶装置，其包括第一径向内平台和第一数目的第一翼型件，以及包括第二径向内平台和第二数量第二翼型件的第二导叶装置。 第一导叶装置和第二导叶装置沿着涡轮机的周向布置，其中第一数量的第一翼型件与第二翼型件的第二数量不同。 第一导叶装置的设计具有比第二导叶装置更高的耐热性。
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公开(公告)号：US20150184529A1
公开(公告)日：2015-07-02
申请号：US14146292
申请日：2014-01-02
IPC分类号： F01D9/04
CPC分类号： F01D9/045 , F01D5/08 , F01D9/06 , F01D9/065 , F01D11/003 , F01D11/005 , F01D11/02 , F01D25/12 , F01D25/24 , F05D2240/55 , Y10T29/49316
摘要： A steam turbine is provided. The steam turbine includes a housing and a steam inlet configured to discharge a primary steam flow within the housing. A stator is coupled to the housing and a rotor is coupled to the housing and located within the stator. The rotor and the stator are configured to define a primary flow path there between and in flow communication with the primary steam flow. The steam turbine includes a seal assembly coupled to the housing. The seal assembly includes a packing head and a plurality of seals. The packing head is configured to define a cooling flow path in flow communication with the rotor and configured to discharge a cooling steam flow toward the rotor. An anti-swirl device is coupled to the seal assembly and located between the rotor and the packing head.
摘要翻译： 提供蒸汽轮机。 蒸汽轮机包括壳体和构造成排出壳体内的主蒸汽流的蒸汽入口。 定子联接到壳体并且转子联接到壳体并且定位在定子内。 转子和定子构造成在其间限定主流动路径，并与主蒸汽流动流动连通。 蒸汽轮机包括联接到壳体的密封组件。 密封组件包括密封头和多个密封件。 包装头构造成限定与转子流动连通的冷却流动路径，并且构造成朝向转子排放冷却蒸汽流。 防旋转装置联接到密封组件并且位于转子和包装头之间。
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公开(公告)号：US20150071783A1
公开(公告)日：2015-03-12
申请号：US14388458
申请日：2013-03-28
发明人： Fathi Ahmad , Hans-Thomas Bolms , Nihal Kurt
CPC分类号： F01D5/30 , F01D5/08 , F01D5/147 , F01D9/042 , F01D11/006 , F05B2240/80 , F05D2240/80
摘要： A turbine blade is provided having a blade and a modular platform which follow one another along a longitudinal axis of the turbine blade. In order to provide a modular turbine blade that has an especially plain and simple design and that ensures an especially reliable, long-lasting, durable connection of the individual components among each other, the blade has an extension and the platform has an outer platform part and an at least two-part inner platform part which is radial in relation to the longitudinal axis and which lie laterally against the extension of the blade, and the outer platform part is designed as an endless platform frame that surrounds the outer edge of the inner platform part.
摘要翻译： 涡轮叶片设置有具有叶片和模块化平台，该平台沿着涡轮机叶片的纵向轴线彼此相接。 为了提供一种具有特别简单且简单设计并且确保各个部件彼此之间特别可靠，持久耐久的连接的模块化涡轮叶片，叶片具有延伸部，并且该平台具有外平台部分 以及至少两部分的内部平台部分，其相对于纵向轴线是径向的，并且横向抵靠叶片的延伸部分，并且外部平台部分被设计为围绕内部的外部边缘的环形平台框架 平台部分。
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