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公开(公告)号：US07114339B2
公开(公告)日：2006-10-03
申请号：US10813520
申请日：2004-03-30
申请人： Ioannis Alvanos , Rajendra Agrawal , Hector M. Pinero , Jin Hu
发明人： Ioannis Alvanos , Rajendra Agrawal , Hector M. Pinero , Jin Hu
CPC分类号： F01D25/12 , F01D5/081 , F02C7/18 , F05D2240/81 , F05D2260/60 , F05D2260/6022 , Y02T50/676
摘要： A gas turbine engine having a turbine section cooling system is disclosed which is able to cool the turbine section of the gas turbine engine to an optimal operating temperature range, while at the same time not substantially degrading engine performance. The disclosure provides a number of different structures for doing so including the provision of turning foils, turning holes, and turning grooves within a secondary air flow cavity which turns or directs cooling and parasitic leakage air into the turbine section in a direction in substantial alignment with a gas flow path through the turbine section.
摘要翻译： 公开了一种具有涡轮部分冷却系统的燃气涡轮发动机，其能够将燃气涡轮发动机的涡轮部分冷却到最佳工作温度范围，同时基本上不降低发动机性能。 本公开提供了许多不同的结构，包括在二次空气流动空腔内提供转动箔，转动孔和转动槽，其将冷却和寄生的泄漏空气转向或引导到与涡轮部分基本对准的方向 通过涡轮机部分的气体流动路径。
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公开(公告)号：US20050217277A1
公开(公告)日：2005-10-06
申请号：US10813520
申请日：2004-03-30
申请人： Ioannis Alvanos , Rajendra Agrawal , Hector Pinero , Jin Hu
发明人： Ioannis Alvanos , Rajendra Agrawal , Hector Pinero , Jin Hu
CPC分类号： F01D25/12 , F01D5/081 , F02C7/18 , F05D2240/81 , F05D2260/60 , F05D2260/6022 , Y02T50/676
摘要： A gas turbine engine having a turbine section cooling system is disclosed which is able to cool the turbine section of the gas turbine engine to an optimal operating temperature range, while at the same time not substantially degrading engine performance. The disclosure provides a number of different structures for doing so including the provision of turning foils, turning holes, and turning grooves within a secondary air flow cavity which turns or directs cooling and parasitic leakage air into the turbine section in a direction in substantial alignment with a gas flow path through the turbine section.
摘要翻译： 公开了一种具有涡轮部分冷却系统的燃气涡轮发动机，其能够将燃气涡轮发动机的涡轮部分冷却到最佳工作温度范围，同时基本上不降低发动机性能。 本公开提供了许多不同的结构，包括在二次空气流动空腔内提供转动箔，转动孔和转动槽，其将冷却和寄生的泄漏空气转向或引导到与涡轮部分基本对准的方向 通过涡轮机部分的气体流动路径。
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公开(公告)号：US20070059158A1
公开(公告)日：2007-03-15
申请号：US11224613
申请日：2005-09-12
申请人： Ioannis Alvanos , Rajendra Agrawal , Hector Pinero
发明人： Ioannis Alvanos , Rajendra Agrawal , Hector Pinero
IPC分类号： F03B11/00
CPC分类号： F01D5/081 , F01D11/001 , F01D25/12 , F02C7/18 , F02C7/28
摘要： A turbine engine section has a stationary vane stage and a rotating blade stage. The blade stage is spaced from the vane stage to form an annular chamber therebetween. A manifold delivers a pressurized fluid to the chamber. An outer diameter (OD) sealing means restricts leakage of the pressurized fluid from the chamber. An inner diameter (ID) sealing means restricts leakage of the pressurized fluid from the chamber. A flow guide extends radially between the inner diameter sealing means and the manifold. The flow guide bisects the chamber to form a stationary chamber portion and a rotating chamber portion, the rotating chamber portion at least partially along a disk of the first blade stage.
摘要翻译： 涡轮发动机部分具有静止叶片台和旋转叶片台。 叶片台与叶片台间隔开以在它们之间形成环形室。 歧管将加压流体输送到腔室。 外径（OD）密封装置限制加压流体从腔室泄漏。 内径（ID）密封装置限制加压流体从腔室泄漏。 流动引导件在内径密封装置和歧管之间径向延伸。 流动导向装置将室平分成一个固定室部分和旋转室部分，旋转室部分至少部分地沿着第一叶片台的圆盘。
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公开(公告)号：US20060275106A1
公开(公告)日：2006-12-07
申请号：US11146660
申请日：2005-06-07
申请人： Ioannis Alvanos , Rajendra Agrawal
发明人： Ioannis Alvanos , Rajendra Agrawal
IPC分类号： F03B11/00
CPC分类号： F01D5/3007 , F01D5/082 , F01D11/001 , F01D11/02
摘要： Disclosed are assemblies and articles for restricting leakage of a pressurized fluid from a cavity. In accordance with an embodiment of the invention, a vane support defines a land, and a neck region of a bladed rotor assembly defines a segmented ring. The segmented ring protrudes outward from the bladed rotor assembly in the neck region, spans across the cavity and cooperates with the land to define a seal.
摘要翻译： 公开了用于限制加压流体从空腔泄漏的组件和制品。 根据本发明的实施例，叶片支撑件限定平台，并且叶片转子组件的颈部区域限定分段环。 分段环从颈部区域中的叶片式转子组件向外突出，跨越空腔并与凸台配合以限定密封。
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公开(公告)号：US20060275107A1
公开(公告)日：2006-12-07
申请号：US11146798
申请日：2005-06-07
申请人： Ioannis Alvanos , Rajendra Agrawal , John Virtue , James Hill , Hector Pinero
发明人： Ioannis Alvanos , Rajendra Agrawal , John Virtue , James Hill , Hector Pinero
IPC分类号： F03B11/00
CPC分类号： F01D5/3007 , F01D5/085 , F01D11/001 , F02C7/28
摘要： Disclosed are assemblies and articles for restricting leakage of a pressurized fluid from a cavity. In accordance with an embodiment of the invention, a vane support defines at least one land, and an interrupted rim region of a bladed rotor assembly defines at least one segmented ring. The at least one segmented ring protruding outward from the bladed rotor assembly in the interrupted rim region, spans across the cavity and cooperates with the at least one land to define a seal.
摘要翻译： 公开了用于限制加压流体从空腔泄漏的组件和制品。 根据本发明的实施例，叶片支撑件限定至少一个平台，并且叶片转子组件的中断的边缘区域限定至少一个分段环。 在中断的边缘区域中从叶片转子组件向外突出的至少一个分段环跨越空腔并与至少一个平台配合以限定密封。
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公开(公告)号：US07334983B2
公开(公告)日：2008-02-26
申请号：US11260357
申请日：2005-10-27
IPC分类号： F01D11/02
CPC分类号： F01D11/02 , F01D5/081 , F01D11/001 , F02C7/28 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： Disclosed are various embodiments of a gas turbine blade to vane interface seal for restricting leakage of cooling air and improving the apportioning of the cooling air to the seal. Accordingly, a turbine rotor contains a first and a second stage of radially extending and circumferentially distributed blades. The stages are separated axially from one another by an annular coupling located radially inboard of the blades, forming a chamber therebetween. Interposed between the blade stages is a vane stage. The vane stage contains a land, facing radially inwardly. A ring projects axially from each of the first and second blade stages towards the vane stage. A ring may also project radially from the coupling towards the vane stage. The rings radially cooperate with the land and together form the blade to vane interface seal. The coupling contains an aperture for radially introducing a cooled fluid to the chamber for use in cooling the seal.
摘要翻译： 公开了用于限制冷却空气泄漏并改善冷却空气对密封件的分配的燃气轮机叶片与叶片接口密封件的各种实施例。 因此，涡轮转子包含径向延伸和周向分布的叶片的第一和第二阶段。 阶段通过位于叶片的径向内侧的环形联接器彼此轴向分开，在它们之间形成室。 在叶片级之间插入叶片级。 叶片台包含一个面向径向内侧的平台。 环从第一和第二叶片台阶中的每一个朝向叶片台轴向突出。 环也可以从联接器径向伸向叶片台。 环与陆部径向配合，并一起形成叶片与叶片接口密封。 联接器包括用于将冷却的流体径向引入到腔室中以用于冷却密封件的孔。
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公开(公告)号：US20070098545A1
公开(公告)日：2007-05-03
申请号：US11260357
申请日：2005-10-27
IPC分类号： F04D29/08
CPC分类号： F01D11/02 , F01D5/081 , F01D11/001 , F02C7/28 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： Disclosed are various embodiments of a gas turbine blade to vane interface seal for restricting leakage of cooling air and improving the apportioning of the cooling air to the seal. Accordingly, a turbine rotor contains a first and a second stage of radially extending and circumferentially distributed blades. The stages are separated axially from one another by an annular coupling located radially inboard of the blades, forming a chamber therebetween. Interposed between the blade stages is a vane stage. The vane stage contains a land, facing radially inwardly. A ring projects axially from each of the first and second blade stages towards the vane stage. A ring may also project radially from the coupling towards the vane stage. The rings radially cooperate with the land and together form the blade to vane interface seal. The coupling contains an aperture for radially introducing a cooled fluid to the chamber for use in cooling the seal.
摘要翻译： 公开了用于限制冷却空气泄漏并改善冷却空气对密封件的分配的燃气轮机叶片与叶片接口密封件的各种实施例。 因此，涡轮转子包含径向延伸和周向分布的叶片的第一和第二阶段。 阶段通过位于叶片的径向内侧的环形联接器彼此轴向分开，在它们之间形成室。 在叶片级之间插入叶片级。 叶片台包含一个面向径向内侧的平台。 环从第一和第二叶片台阶中的每一个朝向叶片台轴向突出。 环也可以从联接器径向伸向叶片台。 环与陆部径向配合，并一起形成叶片与叶片接口密封。 联接器包括用于将冷却的流体径向引入到腔室中以用于冷却密封件的孔。
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