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1. 发明授权

US06257831B1 Cast airfoil structure with openings which do not require plugging 有权
标题翻译：具有不需要堵塞的开口的铸造翼型结构
公开(公告)号：US06257831B1
公开(公告)日：2001-07-10
申请号：US09425175
申请日：1999-10-22
申请人： Michael Papple , William Abdel-Messeh , Ian Tibbott
发明人： Michael Papple , William Abdel-Messeh , Ian Tibbott
IPC分类号： F01D518
CPC分类号： F01D5/187 , B22C9/10 , F05D2230/21 , F05D2240/126 , F05D2260/22141
摘要： A cooled gas turbine engine airfoil comprises a flow deflector arrangement adapted to re-direct a cooling fluid away from an unfilled opening left by a support member of a casting core used during the casting of the airfoil. The provision of the flow deflector arrangement advantageously allows for a larger core support, thereby facilitating the manufacture of the airfoil.
摘要翻译：冷却的燃气涡轮发动机翼型件包括导流装置，该导流装置适于将冷却流体重新引导离开由在铸造机翼期间使用的铸芯的支撑构件留下的未填充开口。提供导流装置有利地允许更大的芯支撑，从而有利于翼型件的制造。

2. 发明授权

US06406260B1 Heat transfer promotion structure for internally convectively cooled airfoils 有权
标题翻译：内部对流冷却翼型传热促进结构
公开(公告)号：US06406260B1
公开(公告)日：2002-06-18
申请号：US09425173
申请日：1999-10-22
申请人： Ricardo Trindade , Michael Papple , William Abdel-Messeh , Ian Tibbott
发明人： Ricardo Trindade , Michael Papple , William Abdel-Messeh , Ian Tibbott
IPC分类号： F01D518
CPC分类号： F01D5/187 , F05D2240/127 , F05D2260/2212 , F05D2260/22141 , F28F3/04
摘要： A cooled airfoil has an internal cooling passage in which a plurality of trip strips are arranged to effect variable coolant flow and heat transfer coefficient distribution so as to advantageously minimize the amount of coolant flow required to adequately cool the airfoil structure. In one embodiment, this is accomplished by varying the dimensions of the trip strips along a transversal axis relative to the cooling passage.
摘要翻译：冷却的翼型件具有内部冷却通道，其中布置多个跳闸带以实现可变的冷却剂流动和传热系数分布，以有利地最小化充分冷却翼型结构所需的冷却剂流量。在一个实施例中，这是通过沿相对于冷却通道的横向轴线改变跳闸带的尺寸来实现的。

3. 发明授权

US5711650A Gas turbine airfoil cooling 失效
标题翻译：燃气轮机翼型冷却
公开(公告)号：US5711650A
公开(公告)日：1998-01-27
申请号：US725990
申请日：1996-10-04
申请人： Ian Tibbott , William Abdel-Messeh , Michael Papple
发明人： Ian Tibbott , William Abdel-Messeh , Michael Papple
IPC分类号： F01D5/18 , F01D9/02 , F02C7/18 , F01D9/04
CPC分类号： F01D5/189 , F01D5/186 , F02C7/185 , F05D2240/81
摘要： A cooling system for airfoil vanes in a turbine of a gas turbine engine wherein the airfoil platforms have openings downstream of the insert tube for passing spent platform impingement coolant air into the airfoil cavity downstream of the insert tube to increase the pressure in the aft zone of the airfoil to improve the temperature gradient across the span of the airfoil.
摘要翻译：一种用于燃气涡轮发动机的涡轮机中的翼型叶片的冷却系统，其中所述翼型平台在所述插入管的下游具有开口，用于将废弃的平台冲击所述冷却剂空气冲入所述插入管下游的所述翼型腔中，以增加所述后部区域中的压力翼型件可改善跨越翼型的跨度的温度梯度。

4. 发明授权

US5779437A Cooling passages for airfoil leading edge 失效
标题翻译：翼型前缘的冷却通道
公开(公告)号：US5779437A
公开(公告)日：1998-07-14
申请号：US742258
申请日：1996-10-31
申请人： William Abdel-Messeh , Ian Tibbott , Subhash Arora
发明人： William Abdel-Messeh , Ian Tibbott , Subhash Arora
IPC分类号： F01D9/02 , F01D5/18 , F04D29/38
CPC分类号： F01D5/186 , F05D2260/202
摘要： A cooling structure for the leading edge area of an airfoil having a plurality of passages wherein each passage has a radial component and a downstream component relative to the leading edge axis, and the outlet of each passage has a diffuser area formed by conical machining, wherein the diffuser area is recessed in the wall portion downstream of the passage.
摘要翻译：一种用于具有多个通道的翼型件的前缘区域的冷却结构，其中每个通道相对于前缘轴线具有径向部件和下游部件，并且每个通道的出口具有通过锥形加工形成的扩散器区域，其中扩散器区域凹陷在通道下游的壁部分中。

5. 发明授权

US06508620B2 Inner platform impingement cooling by supply air from outside 有权
标题翻译：内平台冲击由外部供气冷却
公开(公告)号：US06508620B2
公开(公告)日：2003-01-21
申请号：US09858474
申请日：2001-05-17
申请人： Sri Sreekanth , Jeffrey William Quick , William Abdel-Messeh , Michael Papple
发明人： Sri Sreekanth , Jeffrey William Quick , William Abdel-Messeh , Michael Papple
IPC分类号： F01D906
CPC分类号： F01D5/187 , F05D2240/81
摘要： A stator blade assembly for a gas turbine engine has a leading edge portion with a passage communicating between a plenum and an air supply port of the outer shroud and an internal blade cooling channel communicating between passages and apertures adjacent the trailing edge of the blade. The plenum includes an impingement plate disposed a distance from the inner surface of blade platform to define an impingement cooling chamber within the plenum, and the plate includes impingement cooling apertures to direct cooling jets of air at the inner blade platform. An air flow restriction plate covers the inner end of the passage and controls the pressure and quantity of air delivered to the plenum via a compressed air metering aperture.
摘要翻译：用于燃气涡轮发动机的定子叶片组件具有前缘部分，其具有在外护罩的气室和空气供应口之间连通的通道，以及在与叶片的后缘相邻的通道和孔之间连通的内部叶片冷却通道。气室包括设置在叶片平台的内表面一定距离处的冲击板，以在气室内限定冲击冷却室，并且该板包括冲击冷却孔，以引导内刀片平台处的空气喷射。气流限制板覆盖通道的内端，并通过压缩空气计量孔控制输送到集气室的空气的压力和数量。

6. 发明授权

US08807945B2 Cooling system for turbine airfoil including ice-cream-cone-shaped pedestals 有权
标题翻译：包括冰淇淋锥形基座的涡轮机翼型冷却系统
公开(公告)号：US08807945B2
公开(公告)日：2014-08-19
申请号：US13166369
申请日：2011-06-22
申请人： Brandon W. Spangler , William Abdel-Messeh
发明人： Brandon W. Spangler , William Abdel-Messeh
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/126 , F05D2240/127
摘要： A turbine airfoil comprises a wall portion, a cooling channel, a plurality of trip strips and a plurality of pedestals. The wall portion comprises a leading edge, a trailing edge, a pressure side and a suction side. The cooling channel is for receiving cooling air and extends radially through an interior of the wall portion between the pressure side and the suction side. The plurality of trip strips line the wall portion inside the cooling channel along the pressure side and the suction side. Each of the pedestals is an elongate, tapered pedestal having a curved leading edge. The plurality of pedestals is interposed within the trip strips and connects the pressure side with the suction side.
摘要翻译：涡轮机翼片包括壁部分，冷却通道，多个跳闸条和多个基座。壁部分包括前缘，后缘，压力侧和吸力侧。冷却通道用于接收冷却空气并径向延伸穿过压力侧和吸力侧之间的壁部分的内部。多个跳闸带沿着压力侧和吸力侧排列在冷却通道内部的壁部分。每个基座是具有弯曲前缘的细长的锥形基座。多个基座插入跳闸带内，并将压力侧与吸力侧连接。

7. 发明申请

US20100150733A1 AIRFOIL WITH WRAPPED LEADING EDGE COOLING PASSAGE 有权
标题翻译： AIRFSIL带有封面的领先风扇冷却通道
公开(公告)号：US20100150733A1
公开(公告)日：2010-06-17
申请号：US12334665
申请日：2008-12-15
申请人： William Abdel-Messeh , Justin D. Piggush
发明人： William Abdel-Messeh , Justin D. Piggush
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/14
摘要： A turbine engine airfoil includes an airfoil structure having an exterior surface providing a leading edge. A radially extending first cooling passage is arranged near the leading edge and includes first and second portions. The first portion extends to the exterior surface and forms a radially extending trench in the leading edge. The second portion is in fluid communication with a second cooling passage. In one example, the second cooling passage extends radially, and the first cooling passage wraps around a portion of the second cooling passage from a pressure side to a suction side between the second cooling passage and the exterior surface. In the example, the first portion is arranged between the pressure and suction sides. In one example, the first cooling passage is formed by arranging a core in an airfoil mold. The trench is formed by the core in one example.
摘要翻译：涡轮发动机翼型件包括具有提供前缘的外表面的翼型结构。径向延伸的第一冷却通道布置在前缘附近并包括第一和第二部分。第一部分延伸到外表面并且在前缘中形成径向延伸的沟槽。第二部分与第二冷却通道流体连通。在一个示例中，第二冷却通道径向延伸，并且第一冷却通道围绕第二冷却通道的一部分从第二冷却通道和外表面之间的压力侧卷绕到吸入侧。在该示例中，第一部分布置在压力侧和吸力侧之间。在一个示例中，第一冷却通道是通过在翼型模具中布置芯而形成的。在一个示例中，沟槽由芯构成。

8. 发明申请

US20090180861A1 COOLING ARRANGEMENT FOR TURBINE COMPONENTS 有权
标题翻译：涡轮组件冷却装置
公开(公告)号：US20090180861A1
公开(公告)日：2009-07-16
申请号：US11971932
申请日：2008-01-10
申请人： Ricardo Trindade , Bryan P. Dube , William Abdel-Messeh
发明人： Ricardo Trindade , Bryan P. Dube , William Abdel-Messeh
IPC分类号： F02C7/12
CPC分类号： F01D5/186 , F01D5/187 , F05D2250/185 , Y02T50/676
摘要： A turbine component includes an aft cooling circuit that extends between a turbine midsection and a turbine trailing end. The aft cooling circuit includes a trailing end section proximate the trailing end, a first interior section proximate the turbine midsection, and a first intermediate section fluidly connected between the trailing end section and the first interior section. A forward cooling circuit of the turbine component extends between the turbine midsection and a turbine leading end. The forward cooling circuit includes a leading end section proximate the leading end, a second interior section proximate the turbine midsection, and a plurality of second intermediate sections fluidly connected between the leading end section and the second interior section. The leading end section, the second intermediate section, the first intermediate section, and the trailing end section each include a plurality of coolant discharge openings for facilitating cooling of the turbine component.
摘要翻译：涡轮机部件包括在涡轮机中部和涡轮机尾端之间延伸的后冷却回路。后冷却回路包括靠近后端的后端部分，靠近涡轮机中部的第一内部部分和流体连接在后端部分和第一内部部分之间的第一中间部分。涡轮机部件的向前冷却回路在涡轮机中部和涡轮机前端之间延伸。前向冷却回路包括靠近前端的前端部分，靠近涡轮机中部的第二内部部分和流体连接在前端部分和第二内部部分之间的多个第二中间部分。前端部分，第二中间部分，第一中间部分和后端部分均包括多个用于促进涡轮部件冷却的冷却剂排放口。

9. 发明申请

US20090028692A1 Systems and Methods for Providing Vane Platform Cooling 有权
标题翻译：提供叶片平台冷却的系统和方法
公开(公告)号：US20090028692A1
公开(公告)日：2009-01-29
申请号：US11782001
申请日：2007-07-24
申请人： Raymond Surace , Eleanor D. Kaufman , Andrew D. Milliken , William Abdel-Messeh
发明人： Raymond Surace , Eleanor D. Kaufman , Andrew D. Milliken , William Abdel-Messeh
IPC分类号： F01D1/02
CPC分类号： F01D5/187 , F05D2240/81
摘要： Systems and methods for cooling vane platforms are provided. In this regard, a representative method for cooling a vane platform includes: providing a cooling channel on a platform from which a vane airfoil extends, the cooling channel being defined by a cooling surface and a channel cover, the channel wall being spaced from the cooling surface and located such that the cooling surface is positioned between a gas flow path of the vane and the channel cover; and directing a flow of cooling air through the cooling channel such that heat is extracted from the cooling surface of the platform by the flow of cooling air.
摘要翻译：提供了冷却叶片平台的系统和方法。在这方面，用于冷却叶片平台的代表性方法包括：在叶片翼片延伸的平台上提供冷却通道，冷却通道由冷却表面和通道盖限定，通道壁与冷却表面并且定位成使得冷却表面位于叶片的气体流动路径和通道盖之间; 并且通过冷却通道引导冷却空气流，使得通过冷却空气流从平台的冷却表面提取热量。

10. 发明申请

US20070297917A1 Leading edge cooling using chevron trip strips 有权
标题翻译：使用人字纹旅行带的前沿冷却
公开(公告)号：US20070297917A1
公开(公告)日：2007-12-27
申请号：US11473894
申请日：2006-06-22
申请人： Jeffrey R. Levine , William Abdel-Messeh , Eleanor Kaufman
发明人： Jeffrey R. Levine , William Abdel-Messeh , Eleanor Kaufman
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/12 , F05D2240/121 , F05D2240/303 , F05D2250/70 , F05D2260/2212 , F05D2260/22141
摘要： A turbine engine component has an airfoil portion having a leading edge, a suction side, and a pressure side and a radial flow leading edge cavity through which a cooling fluid flows for cooling the leading edge. The turbine engine component further has a first set of trip strips and a second set of trip strips which meet at the leading edge nose portion of the leading edge cavity to form a plurality of chevron shaped trip strips and for generating a vortex in the leading edge cavity which impinges on the nose portion of the leading edge cavity and enhances convective heat transfer.
摘要翻译：涡轮发动机部件具有翼型部分，其具有前缘，吸力侧以及冷却流体流过的用于冷却前缘的压力侧和径向流前缘腔。涡轮发动机部件还具有第一组跳闸带和第二组跳闸条，其在前缘腔的前缘鼻部处相交，以形成多个人字形的跳闸带，并且用于在前缘中产生涡流撞击在前缘腔的鼻部上并增强对流热传递的空腔。

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