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1. 发明申请

US20180202297A1 TIP LEAKAGE FLOW DIRECTIONALITY CONTROL 审中-公开
公开(公告)号：US20180202297A1
公开(公告)日：2018-07-19
申请号：US15918190
申请日：2018-03-12
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Mark F. Zelesky , Andrew S. Aggarwala
IPC分类号： F01D5/18 , F01D11/10 , F01D5/14 , F01D5/20
CPC分类号： F01D5/187 , F01D5/146 , F01D5/18 , F01D5/186 , F01D5/20 , F01D11/10 , F05D2240/307 , Y02T50/673 , Y02T50/676
摘要： An airfoil according to an example includes, among other things, a suction sidewall and a pressure sidewall. A tip wall extends from a leading edge to a trailing edge and joins respective outer ends of the suction and pressure sidewalls. A tip rib extends along a pressure side of the tip wall. A tip leakage control channel is provided at the tip wall and has a floor that extends between a first control channel vane sidewall and a second control channel vane sidewall established by a corresponding tip leakage control vane. Each of the tip leakage control vanes is contiguous with and extending from a suction side surface of the tip rib. The tip leakage channel extends toward the trailing edge while extending toward the suction sidewall. One or more of an internal cavity, a channel cooling aperture, and a sidewall microcircuit may be provided.

2. 发明授权

US09915149B2 System and method for a fluidic barrier on the low pressure side of a fan blade 有权
公开(公告)号：US09915149B2
公开(公告)日：2018-03-13
申请号：US14837942
申请日：2015-08-27
申请人： Rolls Royce North American Technologies Inc
发明人： Edward C. Rice
IPC分类号： F01D5/14 , F02K3/06 , F01D5/18 , F01D11/10 , F01D25/24 , F01D11/04 , F02K3/075
CPC分类号： F01D5/145 , F01D5/18 , F01D11/04 , F01D11/10 , F01D25/24 , F02C3/064 , F02K1/28 , F02K1/386 , F02K3/06 , F02K3/075 , F05D2220/36 , F05D2240/12 , F05D2240/127 , Y02T50/673
摘要： A turbofan engine has a fan portion in fluid communication with a core stream and a bypass stream of air separated by splitters disposed both upstream and downstream of the fan portion. A fluid passage is defined between the splitters. The turbofan engine has a plurality of high pressure fluid jets originating from the low pressure side of the fan blades, the jets restricting the migration of the core stream into the bypass stream through the fluid passage.

3. 发明申请

US20170276000A1 APPARATUS AND METHOD FOR FORMING APPARATUS 审中-公开
公开(公告)号：US20170276000A1
公开(公告)日：2017-09-28
申请号：US15079346
申请日：2016-03-24
申请人： GENERAL ELECTRIC COMPANY
发明人： Zachary John SNIDER , John McConnell DELVAUX , Glenn Curtis TAXACHER
IPC分类号： F01D9/02 , F01D11/00
CPC分类号： F01D9/02 , F01D11/005 , F01D11/10 , F01D25/246 , F05D2230/60 , F05D2240/11 , F05D2240/128 , F05D2240/30 , F05D2240/55 , F05D2300/6033 , F05D2300/614
摘要： An apparatus is disclosed including a first article, a second article, and a third article disposed adjacent to one another, with the first article and the second article disposed between the third article and a gas path. The first article includes at least one first ceramic matrix composite ply defining a first cooperating feature. The second article includes at least one second ceramic matrix composite ply defining a second cooperating feature. The first cooperating feature and the second cooperating feature define a restricted flow path from the gas path to the third article, which includes a reduced volumetric flow rate of a gas from the gas path to the third article relative to a non-restricted flow path of a non-cooperating interface. A method for forming the apparatus includes forming and aligning the first cooperating feature and the second cooperating feature.

4. 发明授权

US09719365B2 Clearance control 有权
公开(公告)号：US09719365B2
公开(公告)日：2017-08-01
申请号：US14031695
申请日：2013-09-19
申请人： ROLLS-ROYCE PLC
发明人： Marko Bacic , Timothy John Scanlon , Ronald William Daniel
IPC分类号： F01D11/10 , F01D11/24 , F01D11/06 , F01D11/20
CPC分类号： F01D11/10 , F01D11/06 , F01D11/20 , F01D11/24 , F05D2260/16 , F05D2270/172 , F05D2270/62
摘要： A clearance control device including a segment having a passage to deliver fluid towards a component rotating past the segment. Also a fluid flow device having a first fluid path coupled to the passage and a second fluid path that is decoupled from the passage. A first plasma generator is located in the fluid flow device that directs fluid towards the first fluid path; a second plasma generator is located in the fluid flow device that directs fluid towards the second fluid path; and a control arrangement is configured to alternately energize the first and second plasma generators at an energizing frequency to deliver fluid to the passage at a frequency coincident with the passing frequency of the component.

5. 发明申请

US20170074116A1 METHOD OF CREATING HEAT TRANSFER FEATURES IN HIGH TEMPERATURE ALLOYS 审中-公开
标题翻译：在高温合金中形成热传递特征的方法
公开(公告)号：US20170074116A1
公开(公告)日：2017-03-16
申请号：US14794861
申请日：2015-07-09
申请人： United Technologies Corporation
发明人： Brandon W. Spangler , Douglas M. Berczik
IPC分类号： F01D25/12 , F01D25/28 , F23R3/00 , F01D11/10 , F01D5/18 , F01D25/00 , F01D9/06
CPC分类号： F01D25/12 , B23P15/04 , F01D5/147 , F01D5/186 , F01D9/04 , F01D9/041 , F01D9/065 , F01D11/10 , F01D25/005 , F01D25/28 , F05D2220/32 , F05D2230/236 , F05D2230/60 , F05D2260/202 , F05D2260/221 , F05D2300/131 , F23R3/002 , Y02T50/672 , Y02T50/676
摘要： A method for forming a gas turbine engine component comprises the steps of forming a first portion from a high temperature alloy material, and forming a second portion from the high temperature alloy material, the first and second portions each defining an external surface and an internal surface. At least one heat transfer feature is formed directly on the internal surface of at least one of the first and second portions. The first and second portions are attached together to form a component. A component for a gas turbine engine is also disclosed.
摘要翻译：一种形成燃气涡轮发动机部件的方法包括以下步骤：从高温合金材料形成第一部分，并从高温合金材料形成第二部分，第一和第二部分各自限定外表面和内表面。至少一个传热特征直接形成在第一和第二部分中的至少一个的内表面上。第一和第二部分附接在一起以形成部件。还公开了一种用于燃气涡轮发动机的部件。

6. 发明授权

US09327368B2 Full ring inner air-seal with locking nut 有权
标题翻译：全环内密封带锁紧螺母
公开(公告)号：US09327368B2
公开(公告)日：2016-05-03
申请号：US13628298
申请日：2012-09-27
申请人： United Technologies Corporation
发明人： Benjamin F. Hagan
IPC分类号： F01D11/00 , F01D11/02 , B23P15/04 , F02C7/28 , F01D11/04 , F01D11/10 , F01D9/06
CPC分类号： B23P15/04 , F01D9/065 , F01D11/001 , F01D11/005 , F01D11/04 , F01D11/10 , F02C7/28 , F05D2240/11 , F05D2250/191 , F05D2260/30 , Y10T29/49336
摘要： A vane assembly has a vane including an inner platform with a mount rail extending radially inwardly toward an engine center axis. An air seal is attached to the inner platform. The air seal has a single-piece ring extending circumferentially about the engine center axis. A ring nut secures the air seal to the inner platform. A biasing member cooperates with the ring nut and air seal to seal fore and aft locations on the vane.
摘要翻译：叶片组件具有叶片，叶片包括具有径向向内朝向发动机中心轴线延伸的安装轨道的内平台。空气密封件附接到内平台。空气密封件具有围绕发动机中心轴线周向延伸的单件环。环形螺母将空气密封件固定到内部平台。偏置构件与环形螺母和空气密封件协作以密封叶片上的前后位置。

7. 发明申请

US20150198063A1 COOLED STATOR HEAT SHIELD 审中-公开
标题翻译：冷却式定温器
公开(公告)号：US20150198063A1
公开(公告)日：2015-07-16
申请号：US14592127
申请日：2015-01-08
申请人： ALSTOM Technology Ltd
发明人： Petr Vitalievich LALETIN , Andrey Anatolievich Sedlov , Anton Titov , Maxim Plodistyy
IPC分类号： F01D25/12 , F01D9/02
CPC分类号： F01D25/12 , F01D9/04 , F01D11/10 , F05D2240/11 , F05D2240/15 , F05D2250/15 , F05D2260/201 , F05D2260/202 , F05D2260/22141
摘要： The present invention provides a stator heat shield for a gas turbine. The gas turbine includes a rotor defining an axis of rotation. The stator heat shield includes a plurality of cooling units disposed in array along the axis of rotation. Each of the cooling units includes an outside part facing hot gas path of the gas turbine, and an inside plate positioned on the outside part and exposed to cooling air, wherein the inside plate comprises a plurality of inlet openings formed through the inside plate to introduce the cooling air into the outside part and thereby impingement cooling of the hot gas washed wall of the outside part. The outside part includes a cooling air channel formed therein with a first central portion to receive the cooling air, and a second spiral portion around the first central portion to convey the cooling air outward to a cooling air outlet of the second spiral portion. Initial investigation of the proposed cooling scheme in the present invention shows that the cooling air saving of 40% is expected compared to the common design.
摘要翻译：本发明提供一种用于燃气轮机的定子隔热罩。燃气涡轮机包括限定旋转轴线的转子。定子隔热罩包括沿着旋转轴设置成阵列的多个冷却单元。每个冷却单元包括面对燃气轮机的热气路的外部部分和位于外部部分并暴露于冷却空气的内侧板，其中内侧板包括通过内侧板形成的多个入口，以引入冷却空气进入外部部分，从而冲击外部部分的热气体洗涤壁的冷却。外部部分包括形成有第一中心部分以接收冷却空气的冷却空气通道，以及围绕第一中心部分的第二螺旋部分，以将冷却空气向外输送到第二螺旋部分的冷却空气出口。本发明所提出的冷却方案的初步调查表明，与普通设计相比，预计节约了40％的冷却空气。

8. 发明授权

US08979482B2 Gas turbine of the axial flow type 有权
标题翻译：燃气轮机的轴流式
公开(公告)号：US08979482B2
公开(公告)日：2015-03-17
申请号：US13306025
申请日：2011-11-29
申请人： Alexander Anatolievich Khanin , Valery Kostege
发明人： Alexander Anatolievich Khanin , Valery Kostege
IPC分类号： F01D11/10
CPC分类号： F01D11/10 , F05D2240/11 , F05D2240/81 , F05D2260/201 , F05D2260/205
摘要： In an axial flow gas turbine (30), a reduction in cooling air mass flow and leakage in combination with an improved cooling and effective thermal protection of critical parts within the turbine stages of the turbine is achieved by providing, within a turbine stage (TS), devices (43-48) to direct cooling air that has already been used to cool, especially the airfoils of the vanes (31) of the turbine stage (TS), into a first cavity (41) located between the outer blade platforms (34) and the opposed stator heat shields (36) for protecting the stator heat shields (36) against the hot gas and for cooling the outer blade platforms (34).
摘要翻译：在轴流式燃气涡轮机（30）中，通过在涡轮机级（TS）中提供冷却空气质量流量和泄漏的减少以及对涡轮机涡轮级内的关键部件的改进的冷却和有效的热保护），用于引导已经用于冷却的冷却空气的装置（43-48），特别是涡轮级（TS）的叶片（31）的翼型进入位于外刀片平台（34）和相对的定子隔热罩（36），用于保护定子隔热罩（36）抵靠热气体并用于冷却外刀片平台（34）。

9. 发明申请

US20150050125A1 FLUID SEAL ARRANGEMENT AND METHOD FOR CONSTRICTING A LEAKAGE FLOW THROUGH A LEAKAGE GAP 审中-公开
标题翻译：流体密封装置和通过泄漏漏气约束泄漏流量的方法
公开(公告)号：US20150050125A1
公开(公告)日：2015-02-19
申请号：US14341264
申请日：2014-07-25
申请人： ALSTOM Technology Ltd
发明人： Carlos SIMON-DELGADO , Vasileios STEFANIS , Sergey SHCHUKIN , Joerg KRUECKELS
IPC分类号： F01D11/10 , F16J15/40
CPC分类号： F01D11/10 , F16J15/162 , F16J15/40 , F16J15/444 , F16J15/4472
摘要： The invention refers to a fluid seal arrangement for constricting a leakage flow directed through a leakage gap bordered by a rotational and a stationary component including at least one nozzle opening in the rotating and/or stationary component facing towards the rotating or stationary component of an opposite side of the leakage gap respectively in order for injecting a liquid or gaseous fluid flow through the nozzle opening into the leakage gap. The at least one nozzle opening is fluidly connected to a cooling channel inside said rotating and/or stationary component, so that said fluid flow emanating at the nozzle opening consists of a cooling fluid of the rotating and/or stationary component exclusively.
摘要翻译：本发明涉及一种流体密封装置，用于限制通过由旋转和静止部件界定的泄漏间隙的泄漏流动，所述泄漏间隙包括旋转和/或固定部件中的至少一个喷嘴开口，所述喷嘴开口面向相对的旋转部件或固定部件以便将液体或气体流体流经喷嘴开口注入到泄漏间隙中。至少一个喷嘴开口流体地连接到所述旋转和/或固定部件内的冷却通道，使得在喷嘴开口处发出的所述流体流由仅旋转和/或静止部件的冷却流体组成。

10. 发明授权

US08888444B2 Steam seal system 有权
标题翻译：蒸汽密封系统
公开(公告)号：US08888444B2
公开(公告)日：2014-11-18
申请号：US13108272
申请日：2011-05-16
申请人： Nestor Hernandez Sanchez , Kamlesh Mundra
发明人： Nestor Hernandez Sanchez , Kamlesh Mundra
IPC分类号： F04D29/08 , F01D11/06 , F01D11/10
CPC分类号： F01D11/10 , F01D11/06 , F05B2240/40
摘要： A steam seal system is disclosed. In one embodiment, the steam seal system includes: a low pressure steam turbine positioned on a shaft; a pair of end packings surrounding the shaft, each of the pair of end packings located proximate an axial end of the low pressure steam turbine along the shaft; and an pair of extraction conduits fluidly connected to the low pressure steam turbine and the shaft, the pair of extraction conduits connected to the shaft at a location axially outward of the pair of end packings and the low pressure steam turbine.
摘要翻译：公开了蒸汽密封系统。在一个实施例中，蒸汽密封系统包括：位于轴上的低压蒸汽轮机; 围绕所述轴的一对端部密封件，所述一对端部密封件中的每一个端部密封件沿着所述轴邻近所述低压蒸汽轮机的轴向端部; 以及一对流体连接到低压蒸汽轮机和轴的提取管道，一对提取管道在一对端部密封件和低压蒸汽轮机的轴向外部的位置处连接到轴。

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