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1. 发明授权

US07708525B2 Industrial gas turbine blade assembly 有权
标题翻译：工业燃气轮机叶片组件
公开(公告)号：US07708525B2
公开(公告)日：2010-05-04
申请号：US11167445
申请日：2005-06-27
申请人： Anthony Cherolis , Jesse Christophel , William Abdel-Messeh
发明人： Anthony Cherolis , Jesse Christophel , William Abdel-Messeh
IPC分类号： F01D5/08
CPC分类号： F01D5/187 , F05D2230/90 , F05D2240/81 , F05D2250/314 , F05D2260/201 , F05D2260/202
摘要： A gas turbine blade assembly includes a neck defining a neck cavity, and has a first end and a second end at an opposite side relative to the first end. A platform has first and second sides. The first side is disposed on and faces the second end of the neck. An airfoil is supported on the second side of the platform. The neck, platform and airfoil define an inner cooling passage extending through the neck, platform and into the airfoil. The neck defines at least one core channel extending between the cooling passage and the neck cavity. The platform defines at least one film cooling channel extending from the first side facing the neck cavity to the second side disposed exterior to the airfoil to permit cooling air to flow through the inner cooling passage into the neck cavity and through the platform exterior to the airfoil.
摘要翻译：燃气轮机叶片组件包括限定颈腔的颈部，并且在相对于第一端的相对侧具有第一端和第二端。一个平台有第一面和第二面。第一侧设置在颈部的第二端并面向颈部的第二端。翼片支撑在平台的第二侧上。颈部，平台和翼型件限定了延伸穿过颈部，平台并进入翼型的内部冷却通道。颈部限定在冷却通道和颈腔之间延伸的至少一个芯通道。平台限定了至少一个薄膜冷却通道，其从面向颈部空腔的第一侧延伸到设置在翼型件外部的第二侧，以允许冷却空气流过内部冷却通道进入颈部腔并且通过翼面外部平台。

2. 发明申请

US20070009359A1 Industrial gas turbine blade assembly 有权
标题翻译：工业燃气轮机叶片组件
公开(公告)号：US20070009359A1
公开(公告)日：2007-01-11
申请号：US11167445
申请日：2005-06-27
申请人： Anthony Cherolis , Jesse Christophel , William Abdel-Messeh
发明人： Anthony Cherolis , Jesse Christophel , William Abdel-Messeh
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2230/90 , F05D2240/81 , F05D2250/314 , F05D2260/201 , F05D2260/202
摘要： A gas turbine blade assembly includes a neck defining a neck cavity, and has a first end and a second end at an opposite side relative to the first end. A platform has first and second sides. The first side is disposed on and faces the second end of the neck. An airfoil is supported on the second side of the platform. The neck, platform and airfoil define an inner cooling passage extending through the neck, platform and into the airfoil. The neck defines at least one core channel extending between the cooling passage and the neck cavity. The platform defines at least one film cooling channel extending from the first side facing the neck cavity to the second side disposed exterior to the airfoil to permit cooling air to flow through the inner cooling passage into the neck cavity and through the platform exterior to the airfoil.
摘要翻译：燃气轮机叶片组件包括限定颈腔的颈部，并且在相对于第一端的相对侧具有第一端和第二端。一个平台有第一面和第二面。第一侧设置在颈部的第二端并面向颈部的第二端。翼片支撑在平台的第二侧上。颈部，平台和翼型件限定了延伸穿过颈部，平台并进入翼型的内部冷却通道。颈部限定在冷却通道和颈腔之间延伸的至少一个芯通道。平台限定了至少一个薄膜冷却通道，其从面向颈部空腔的第一侧延伸到设置在翼型件外部的第二侧，以允许冷却空气流过内部冷却通道进入颈部腔并且通过翼面外部平台。

3. 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。

4. 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。

5. 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。

6. 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。

7. 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。

8. 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。

9. 发明申请

US20120152484A1 PERIPHERAL MICROCIRCUIT SERPENTINE COOLING FOR TURBINE AIRFOILS 有权
标题翻译：用于涡轮机空气的外围微型伺服系统冷却
公开(公告)号：US20120152484A1
公开(公告)日：2012-06-21
申请号：US13267055
申请日：2011-10-06
申请人： Frank Cunha , William Abdel-Messeh
发明人： Frank Cunha , William Abdel-Messeh
IPC分类号： B22D25/02
CPC分类号： F01D5/187 , B22C9/04 , B22C9/103 , F01D5/14 , F05D2230/211 , F05D2250/185 , F28F3/022 , F28F3/12 , F28F13/06 , Y02T50/676 , Y10T29/49343
摘要： A turbine component has an airfoil portion with at least one central core element, a pressure side wall, and a suction side wall. The airfoil portion also has a serpentine cooling passageway in at least one of the walls. In a preferred embodiment, the airfoil portion has a serpentine cooling passageway in both of the pressure and suction side walls. A refractory metal core for forming the serpentine cooling passageway(s) is also described.
摘要翻译：涡轮机部件具有至少一个中心芯元件，压力侧壁和吸力侧壁的翼型部分。机翼部分还在至少一个壁中具有蛇形冷却通道。在优选实施例中，翼型部分在压力侧和吸力侧壁中都具有蛇形冷却通道。还描述了用于形成蛇形冷却通道的难熔金属芯。

10. 发明授权

US08177506B2 Microcircuit cooling with an aspect ratio of unity 有权
标题翻译：微电路冷却与长宽比统一
公开(公告)号：US08177506B2
公开(公告)日：2012-05-15
申请号：US11339921
申请日：2006-01-25
申请人： Francisco J. Cunha , William Abdel-Messeh
发明人： Francisco J. Cunha , William Abdel-Messeh
IPC分类号： F01D5/08
CPC分类号： F01D5/187 , F01D5/186 , F05D2250/185 , F05D2260/202
摘要： A turbine engine component having improved cooling is provided. The turbine engine component includes an airfoil portion having a leading edge, a trailing edge, a pressure side, a suction side, a root, and a tip, and at least one cooling circuit in a wall of the airfoil portion. The at least one cooling circuit has at least one passageway extending between the root and the tip. The at least one passageway has an aspect ratio of no greater than 2:1, and preferably substantially unity.
摘要翻译：提供了具有改进的冷却的涡轮发动机部件。涡轮发动机部件包括具有前缘，后缘，压力侧，吸力侧，根部和尖端的翼型部分，以及在翼型部分的壁中的至少一个冷却回路。至少一个冷却回路具有至少一个在根部和尖端之间延伸的通道。所述至少一个通道具有不大于2:1的纵横比，优选基本上为1。

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