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公开(公告)号:US20130034433A1
公开(公告)日:2013-02-07
申请号:US13204338
申请日:2011-08-05
申请人: Dhinagaran Ramachandran , Sujatha Guntu , Vinayender Kuchana , Balamurugan Srinivasan , Anish Gupta , Paul Couey , Craig McKeever , Malak Malak , Gopal Samy Muthiah
发明人: Dhinagaran Ramachandran , Sujatha Guntu , Vinayender Kuchana , Balamurugan Srinivasan , Anish Gupta , Paul Couey , Craig McKeever , Malak Malak , Gopal Samy Muthiah
IPC分类号: F01D1/02
CPC分类号: F01D9/042 , F01D5/145 , Y02T50/671 , Y02T50/673
摘要: A turbine section of a gas turbine engine is provided. The turbine section is annular about a longitudinal axis and includes first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine; and a first guide vane disposed within the inter-turbine duct.
摘要翻译: 提供燃气涡轮发动机的涡轮部分。 涡轮机部分围绕纵向轴线是环形的,并且包括具有第一入口和第一出口的第一涡轮机; 具有第二入口和第二出口的第二涡轮机; 涡轮机间管道,其从所述第一出口延伸到所述第二入口并且构造成将来自所述第一涡轮机的空气流引导到所述第二涡轮机; 以及设置在所述涡轮机间导管内的第一导向叶片。
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公开(公告)号:US08845286B2
公开(公告)日:2014-09-30
申请号:US13204338
申请日:2011-08-05
申请人: Dhinagaran Ramachandran , Sujatha Guntu , Vinayender Kuchana , Balamurugan Srinivasan , Anish Gupta , Paul Couey , Craig McKeever , Malak Malak , Gopal Samy Muthiah
发明人: Dhinagaran Ramachandran , Sujatha Guntu , Vinayender Kuchana , Balamurugan Srinivasan , Anish Gupta , Paul Couey , Craig McKeever , Malak Malak , Gopal Samy Muthiah
CPC分类号: F01D9/042 , F01D5/145 , Y02T50/671 , Y02T50/673
摘要: A turbine section of a gas turbine engine is provided. The turbine section is annular about a longitudinal axis and includes first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine; and a first guide vane disposed within the inter-turbine duct.
摘要翻译: 提供燃气涡轮发动机的涡轮部分。 涡轮机部分围绕纵向轴线是环形的,并且包括具有第一入口和第一出口的第一涡轮机; 具有第二入口和第二出口的第二涡轮机; 涡轮机间管道,其从所述第一出口延伸到所述第二入口并且构造成将来自所述第一涡轮机的空气流引导到所述第二涡轮机; 以及设置在所述涡轮机间导管内的第一导向叶片。
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公开(公告)号:US20060171813A1
公开(公告)日:2006-08-03
申请号:US11218074
申请日:2005-08-31
申请人: Malak Malak , Derek Raybould , Thomas Strangman
发明人: Malak Malak , Derek Raybould , Thomas Strangman
IPC分类号: F03B3/12
CPC分类号: F01D5/20 , C23C28/00 , C23C28/321 , C23C28/345 , C23C28/3455 , C23C28/347 , C23C28/42 , F01D11/125
摘要: A turbine blade tip and shroud clearance control coating system comprising a dense abrasive blade tip layer and an abradable shroud layer are provided. The dense abrasive coating may comprise cubic zirconia, hafnia or mixtures thereof and the abradable layer may be a nanolaminate thermal barrier coating that is softer than the dense abrasive layer.
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公开(公告)号:US20060065383A1
公开(公告)日:2006-03-30
申请号:US10949082
申请日:2004-09-24
申请人: Milton Ortiz , Malak Malak , Steve Halfmann
发明人: Milton Ortiz , Malak Malak , Steve Halfmann
摘要: Methods for rapid prototype casting metal components, wherein the metal components are cast in a secondary ceramic mold, the secondary ceramic mold is cast in a primary mold, and the primary mold is formed by rapid prototyping or rapid manufacturing. The secondary ceramic mold may comprise a one-piece integral shell and core(s), and the metal components may have at least one hollow portion or void therein, such as a hollow airfoil for a gas turbine engine.
摘要翻译: 用于快速成型铸造金属部件的方法,其中金属部件在二次陶瓷模具中铸造,二次陶瓷模具铸造在初级模具中,并且初级模具通过快速成型或快速制造形成。 二次陶瓷模具可以包括一体式的整体壳体和芯部,并且金属部件可以在其中具有至少一个中空部分或空隙,例如用于燃气涡轮发动机的中空翼型件。
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公开(公告)号:US20060246319A1
公开(公告)日:2006-11-02
申请号:US11119657
申请日:2005-05-02
申请人: Richard Bye , Malak Malak , Thomas Strangman , Derek Raybould
发明人: Richard Bye , Malak Malak , Thomas Strangman , Derek Raybould
IPC分类号: B05D1/08
CPC分类号: C23C28/04 , C04B41/009 , C04B41/52 , C04B41/89 , F01D5/286 , F01D5/288 , F05D2260/95 , F05D2300/2118 , F05D2300/2283 , Y02T50/67 , Y02T50/6765 , C04B41/5027 , C04B41/4582 , C04B41/5042 , C04B35/584
摘要: A component for a turbine engine component includes a ceramic substrate having a surface, an environmental barrier layer bonded to the substrate surface, and an impact-resistance layer bonded to the environmental barrier layer, the impact-resistance layer having a melting point higher than about 2700° F., and further having a between about 10 and about 30% porosity. The impact-resistance layer, environmental barrier layer, and interfaces at which the environmental layer is bound to the substrate surface and the impact-resistance layer are more readily shearable than the substrate. A method for protecting a turbine engine component from environmental and particle impact-related damage includes the steps of coating a substrate surface with the environmental barrier layer, and coating the environmental barrier layer with the impact-resistance layer.
摘要翻译: 涡轮发动机部件的部件包括具有表面的陶瓷基板,与基板表面接合的环境阻挡层,以及结合到环境阻挡层的耐冲击层,耐冲击层的熔点高于约 2700°F,并且进一步具有约10至约30%的孔隙率。 耐冲击层,环境阻挡层和环境层与基材表面和耐冲击层结合的界面比基材更容易剪切。 一种用于保护涡轮发动机部件免受环境和颗粒撞击相关损伤的方法包括以下步骤:用环境阻挡层涂覆基底表面,并用耐冲击层涂覆环境阻挡层。
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