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公开(公告)号：US08403632B2
公开(公告)日：2013-03-26
申请号：US12953514
申请日：2010-11-24
申请人： Raymond Surace , Andrew D. Milliken
发明人： Raymond Surace , Andrew D. Milliken
CPC分类号： F01D9/041 , F01D25/08 , F05D2240/81 , F05D2260/221
摘要： A method of cooling a gas turbine engine component includes creating a cooling channel within a platform of the component, communicating cooling air into the cooling channel to cool the platform, and recycling the cooling airflow used to cool the platform by communicating the cooling airflow from the cooling channel into the airfoil to cool the airfoil.
摘要翻译： 一种冷却燃气涡轮发动机部件的方法包括在所述部件的平台内形成冷却通道，将冷却空气与所述冷却通道连通以冷却所述平台，以及再循环用于冷却所述平台的冷却气流， 冷却通道进入翼型以冷却翼型。
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公开(公告)号：US07862291B2
公开(公告)日：2011-01-04
申请号：US11672604
申请日：2007-02-08
申请人： Raymond Surace , Andrew D. Milliken
发明人： Raymond Surace , Andrew D. Milliken
CPC分类号： F01D9/041 , F01D25/08 , F05D2240/81 , F05D2260/221
摘要： A gas turbine engine component includes a platform and an airfoil extending from the platform. The platform includes an outer surface. A cover plate is positioned adjacent to the outer surface of the platform. A cooling channel extends between the outer surface and the cover plate and receives cooling air to cool the platform and the airfoil.
摘要翻译： 燃气涡轮发动机部件包括平台和从平台延伸的翼型件。 平台包括一个外表面。 盖板邻近平台的外表面定位。 冷却通道在外表面和盖板之间延伸并接收冷却空气以冷却平台和翼型件。
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公开(公告)号：US20090028692A1
公开(公告)日：2009-01-29
申请号：US11782001
申请日：2007-07-24
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。
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公开(公告)号：US08403631B2
公开(公告)日：2013-03-26
申请号：US12953513
申请日：2010-11-24
申请人： Raymond Surace , Andrew D. Milliken
发明人： Raymond Surace , Andrew D. Milliken
CPC分类号： F01D9/041 , F01D25/08 , F05D2240/81 , F05D2260/221
摘要： A gas turbine engine includes a compressor section, a combustor section and a turbine section. The turbine section includes components having a platform and an airfoil extending from the platform. The platform includes an outer surface, a cover plate and a cooling channel extending between the outer surface and the cover plate. The cooling channel receives cooling airflow to cool the platform and the airfoil.
摘要翻译： 燃气涡轮发动机包括压缩机部分，燃烧器部分和涡轮部分。 涡轮部分包括具有平台和从平台延伸的翼型件的部件。 平台包括外表面，盖板和在外表面和盖板之间延伸的冷却通道。 冷却通道接收冷却气流以冷却平台和翼型。
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公开(公告)号：US07150601B2
公开(公告)日：2006-12-19
申请号：US11021152
申请日：2004-12-23
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/18 , F01D5/187 , F01D5/188 , F05D2230/80 , F05D2240/12
摘要： An internally cooled gas turbine engine turbine vane has an outboard shroud and an airfoil extending from an outboard end at the shroud to an inboard end. A cooling passageway has an inlet in the shroud, a first turn at least partially within the airfoil, a first leg extending from the inlet inboard through the airfoil to the first turn, and a second leg extending from the first turn. A dividing wall is in the passageway and has an upstream end in an outboard half of a span of the airfoil and has a plurality of vents. The vane may be formed as a reengineering of a baseline configuration lacking the dividing wall.
摘要翻译： 内部冷却的燃气涡轮发动机涡轮叶片具有外侧护罩和从护罩的外侧端部延伸到内侧端部的翼型件。 冷却通道在护罩中具有入口，至少部分地在翼型内的第一匝，从内侧的入口穿过翼型件延伸到第一匝的第一腿部，以及从第一匝延伸的第二腿部。 分隔壁在通道中，并且在翼型的跨度的外侧半部中具有上游端，并且具有多个通风口。 叶片可以形成为缺少分隔壁的基线构型的再造。
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公开(公告)号：US06884023B2
公开(公告)日：2005-04-26
申请号：US10260083
申请日：2002-09-27
申请人： Bryan Dube , Andrew D. Milliken , John H. Mosley , Conan Cook
发明人： Bryan Dube , Andrew D. Milliken , John H. Mosley , Conan Cook
IPC分类号： F01D9/02 , F01D5/08 , F01D9/06 , F01D11/00 , F01D11/04 , F02C7/18 , F02C7/28 , F04D29/10 , F04D29/58 , F16J15/44 , F16J15/447 , F04D31/00
CPC分类号： F01D11/001 , F01D5/08 , F01D9/065 , F05D2220/3213 , F05D2240/128 , F05D2260/20
摘要： The present invention relates to a system for delivering cooling air to a seal arrangement in a turbine stage of a gas turbine engine. The system comprises at least one vane having a passageway extending from an outer platform of the at least one vane to an inner platform of the at least one vane. A tube insert is positioned within the passageway. The tube insert has an inlet at one end for receiving cooling air from a source of cooling air and an outlet at a second end. A cover assembly is attached to the second end of the tube for receiving cooling air from the tube and delivering the cooling air to the seal arrangement. In a preferred embodiment, the cooling air is pre-swirled in the direction of rotation of a rotor stage of the turbine stage.
摘要翻译： 本发明涉及一种用于将冷却空气输送到燃气涡轮发动机的涡轮级中的密封装置的系统。 该系统包括至少一个叶片，其具有从至少一个叶片的外平台延伸到至少一个叶片的内平台的通道。 管插入件位于通道内。 管插入件在一端具有入口，用于从冷却空气源和第二端的出口接收冷却空气。 盖组件附接到管的第二端，用于从管接收冷却空气并将冷却空气输送到密封装置。 在优选实施例中，冷却空气沿着涡轮级的转子级的旋转方向被预先旋转。
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公开(公告)号：US08016546B2
公开(公告)日：2011-09-13
申请号：US11782001
申请日：2007-07-24
IPC分类号： F01D25/12
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。
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公开(公告)号：US20110070082A1
公开(公告)日：2011-03-24
申请号：US12953514
申请日：2010-11-24
申请人： Raymond Surace , Andrew D. Milliken
发明人： Raymond Surace , Andrew D. Milliken
IPC分类号： B64C27/00
CPC分类号： F01D9/041 , F01D25/08 , F05D2240/81 , F05D2260/221
摘要： A method of cooling a gas turbine engine component includes creating a cooling channel within a platform of the component, communicating cooling air into the cooling channel to cool the platform, and recycling the cooling airflow used to cool the platform by communicating the cooling airflow from the cooling channel into the airfoil to cool the airfoil.
摘要翻译： 一种冷却燃气涡轮发动机部件的方法包括在所述部件的平台内形成冷却通道，将冷却空气与所述冷却通道连通以冷却所述平台，以及再循环用于冷却所述平台的冷却气流， 冷却通道进入翼型以冷却翼型。
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公开(公告)号：US20110070097A1
公开(公告)日：2011-03-24
申请号：US12953513
申请日：2010-11-24
申请人： Raymond Surace , Andrew D. Milliken
发明人： Raymond Surace , Andrew D. Milliken
IPC分类号： F01D5/18
CPC分类号： F01D9/041 , F01D25/08 , F05D2240/81 , F05D2260/221
摘要： A gas turbine engine includes a compressor section, a combustor section and a turbine section. The turbine section includes components having a platform and an airfoil extending from the platform. The platform includes an outer surface, a cover plate and a cooling channel extending between the outer surface and the cover plate. The cooling channel receives cooling airflow to cool the platform and the airfoil.
摘要翻译： 燃气涡轮发动机包括压缩机部分，燃烧器部分和涡轮部分。 涡轮部分包括具有平台和从平台延伸的翼型件的部件。 平台包括外表面，盖板和在外表面和盖板之间延伸的冷却通道。 冷却通道接收冷却气流以冷却平台和翼型。
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公开(公告)号：US20080190114A1
公开(公告)日：2008-08-14
申请号：US11672604
申请日：2007-02-08
申请人： Raymond Surace , Andrew D. Milliken
发明人： Raymond Surace , Andrew D. Milliken
CPC分类号： F01D9/041 , F01D25/08 , F05D2240/81 , F05D2260/221
摘要： A gas turbine engine component includes a platform and an airfoil extending from the platform. The platform includes an outer surface. A cover plate is positioned adjacent to the outer surface of the platform. A cooling channel extends between the outer surface and the cover plate and receives cooling air to cool the platform and the airfoil.
摘要翻译： 燃气涡轮发动机部件包括平台和从平台延伸的翼型件。 平台包括一个外表面。 盖板邻近平台的外表面定位。 冷却通道在外表面和盖板之间延伸并接收冷却空气以冷却平台和翼型件。
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