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1.发明申请
公开(公告)号：WO2014130103A3
公开(公告)日：2014-10-16
申请号：PCT/US2013068717
申请日：2013-11-06
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERGE GARY D
CPC classification number: F02K3/115 , F01D9/065 , F02C7/06 , F02C7/14 , F02C7/18 , F02K3/06 , F02K3/105 , F05D2210/12 , F05D2240/123 , F05D2240/124 , F05D2250/182 , F05D2250/60 , F05D2260/20 , F05D2260/213 , F05D2260/4031 , F05D2260/98 , Y02T50/676
Abstract: An oil cooling system and method are provided for use with respect to a lubricated mechanical system within a bypass configured gas turbine engine. A surface cooler is fluidly linked to the lubricated mechanical system to receive oil from the lubricated mechanical system for cooling and reuse. In an embodiment, the surface cooler is mounted on an existing surface within the bypass airflow path of the bypass configured gas turbine engine to provide effective cooling while avoiding the introduction of additional aerodynamic disturbances in the bypass path. In an embodiment, the surface cooler is mounted on the fan casing or on a fan exit guide vane.
Abstract translation: 提供了一种用于在旁路配置的燃气涡轮发动机内的润滑的机械系统的油冷却系统和方法。 表面冷却器与润滑的机械系统流体连接，以从润滑的机械系统接收油，用于冷却和再利用。 在一个实施例中，表面冷却器安装在旁路构造的燃气涡轮发动机的旁路气流路径内的现有表面上，以提供有效的冷却，同时避免在旁路路径中引入额外的空气动力学干扰。 在一个实施例中，表面冷却器安装在风扇壳体或风扇出口导叶上。
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公开(公告)号：WO2015088606A3
公开(公告)日：2015-07-30
申请号：PCT/US2014054733
申请日：2014-09-09
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERGE GARY D
CPC classification number: F02C3/04 , F01D13/006 , F02C3/073 , F02K3/06 , F02K3/068 , F02K3/072 , F05D2220/32 , F05D2220/323 , Y02T50/672
Abstract: A reverse-core turbofan engine including a propulsor section including a fan and a fan-tip turbine configured to deliver air to a core duct, including a first portion, disposed aft of the propulsor section, and direct air aft, toward an inlet of a reverse-core gas generator, and a second portion, configured to receive air from an exit of the gas generator and direct the air forward and radially outward of the propulsor, toward the fan-tip turbine in the propulsor, thereby driving the propulsor.
Abstract translation: 一种反向堆芯涡轮风扇发动机，其包括推进器部分，所述推进器部分包括风扇和风扇叶顶涡轮，所述推进器部分构造成将空气输送到芯管，所述芯管包括设置在推进器部分的后部的第一部分以及将空气引导向尾部朝向 以及第二部分，所述第二部分构造成从所述气体发生器的出口接收空气，并将所述空气朝向所述推进器的所述风扇尖端涡轮机推进，从而驱动所述推进器。
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公开(公告)号：WO2006110125A3
公开(公告)日：2007-02-22
申请号：PCT/US2004040206
申请日：2004-12-01
Applicant: UNITED TECHNOLOGIES CORP , SUCIU GABRIEL L , ROBERGE GARY D , MERRY BRIAN
Inventor： SUCIU GABRIEL L , ROBERGE GARY D , MERRY BRIAN
CPC classification number: F02K3/068 , F01D5/025 , F01D5/34 , F02C3/067 , F02C3/073 , Y02T50/671 , Y10T29/49321
Abstract: Improved annular components and improved methods for assembling annular components into a turbine engine are described with respect to an axial compressor having a plurality of annular compressor rotor airfoil assemblies (120) as an example. Each compressor rotor airfoil assembly comprises an annular rotor portion (122), a spacer portion (124) extending axially therefrom and a plurality of airfoils (52) extending radially thereform. The plurality of airfoils may be integrally formed with the annular portion. The compressor rotor airfoil assemblies are stacked sequentially on a center-tie (134) or outer circumferential tie. The spacer portion of one compressor rotor airfoil assembly (120a) abuts the annular rotor portion of the adjacent compressor rotor airfoil assembly (120b) to retain one another on the center-tied outer circumferential tie. By stacking the compressor rotor airfoil assemblies sequentially and then retaining them, the typical split cases, flanges and rotor bolts may be eliminated.
Abstract translation: 作为示例，关于具有多个环形压缩机转子翼型组件（120）的轴向压缩机来描述改进的环形部件和用于将环形部件组装到涡轮发动机中的改进方法。 每个压缩机转子翼型组件包括环形转子部分（122），从其轴向延伸的间隔部分（124）和沿径向延伸的多个翼型件（52）。 多个翼型件可以与环形部分一体地形成。 压缩机转子翼型件组件依次堆叠在中心连接件（134）或外圆环上。 一个压缩机转子翼型组件（120a）的间隔部分邻接邻近的压缩机转子翼型组件（120b）的环形转子部分，以将它们彼此保持在中心连接的外圆环上。 通过依次堆叠压缩机转子叶片组件然后保持它们，可以消除典型的分体式壳体，凸缘和转子螺栓。
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公开(公告)号：WO2015108592A3
公开(公告)日：2015-09-24
申请号：PCT/US2014061916
申请日：2014-10-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERGE GARY D
CPC classification number: F01D5/282 , B23P15/04 , F01D5/147 , F01D5/18 , F01D5/284 , F01D9/041 , F01D25/005 , F01D25/12 , F04D29/321 , F05D2220/32 , F05D2240/303 , F05D2260/36 , F05D2300/5023 , F05D2300/522 , Y02T50/672
Abstract: A turbine component comprises a platform and an airfoil extending radially away from the platform and extending from a leading edge to a trailing edge. A leading edge portion defines the leading edge of the airfoil and a trailing edge portion including the trailing edge. One of the leading and trailing edge portions also includes the platform. The leading edge portion is formed of a first material distinct from a second material forming the trailing edge portion. The first material has an operating temperature capability at least 100F higher than that of the second material. A gas turbine engine is also disclosed.
Abstract translation: 涡轮机部件包括平台和从平台径向延伸并且从前缘延伸到后缘的翼型件。 前缘部分限定翼型的前缘和包括后缘的后缘部分。 前缘和后缘部分之一还包括平台。 前缘部分由与形成后缘部分的第二材料不同的第一材料形成。 第一种材料的工作温度至少比第二种材料高100°F。 燃气涡轮发动机也被公开。
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公开(公告)号：WO2015130386A2
公开(公告)日：2015-09-03
申请号：PCT/US2014070089
申请日：2014-12-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERGE GARY D
CPC classification number: F02C3/067 , F02C3/107 , F02K3/072 , F05D2260/40311 , Y02T50/671
Abstract: The present disclosure relates generally to turbomachinery in which a rotating component is disposed adjacent a counter-rotating component in order to achieve a relative rotational velocity that is higher than would be achieved with a rotating component disposed adjacent to a stationary component.
Abstract translation: 本公开总体上涉及涡轮机械，其中旋转部件邻近反向旋转部件设置，以实现比使用邻近静止部件布置的旋转部件所实现的更高的相对旋转速度。
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Patent Agency Ranking
公开(公告)号：DE602004031470D1
公开(公告)日：2011-03-31
申请号：DE602004031470
申请日：2004-12-01
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERGE GARY D
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公开(公告)号：DE602004023769D1
公开(公告)日：2009-12-03
申请号：DE602004023769
申请日：2004-12-01
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , ROBERGE GARY D , MERRY BRIAN
Abstract: Improved annular components and improved methods for assembling annular components into a turbine engine are described with respect to an axial compressor having a plurality of annular compressor rotor airfoil assemblies (120) as an example. Each compressor rotor airfoil assembly comprises an annular rotor portion (122), a spacer portion (124) extending axially therefrom and a plurality of airfoils (52) extending radially therefrom. The plurality of airfoils may be integrally formed with the annular portion. The compressor rotor airfoil assemblies are stacked sequentially on a center-tie (134) or outer circumferential tie. The spacer portion of one compressor rotor airfoil assembly (120a) abuts the annular rotor portion of the adjacent compressor rotor airfoil assembly (120b) to retain one another on the center-tied outer circumferential tie. By stacking the compressor rotor airfoil assemblies sequentially and then retaining them, the typical split cases, flanges and rotor bolts may be eliminated.
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公开(公告)号：CA2618116C
公开(公告)日：2012-03-27
申请号：CA2618116
申请日：2008-01-22
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERGE GARY D , WATSON CHARLES R , LEJAMBRE CHARLES R
Abstract: A variable area fan nozzle for use with a gas turbine engine system includes a nozzle section that is movable between a plurality of positions to change an effective area associated with a bypass airflow through a fan bypass passage of a gas turbine engine. A protective coating is disposed on the nozzle section and resists change in the effective area of the nozzle section caused by environmental conditions.
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公开(公告)号：WO2013172899A3
公开(公告)日：2014-01-16
申请号：PCT/US2013026903
申请日：2013-02-20
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROBERGE GARY D , SUCIU GABRIEL L
CPC classification number: F02K3/077 , F02C7/36 , F02K3/072 , F05D2260/40311
Abstract: Gas turbine engine systems involving tip fans are provided. In this regard, a representative gas turbine engine system includes: a multi-stage fan having a first rotatable set of blades and a second counter-rotatable set of blades, the second rotatable set of blades defining an inner fan and a tip fan and being located downstream of the first set of rotatable blades; and an epicyclic differential gear assembly operative to receive a torque input and differentially apply the torque input to the first set of blades and the second set of blades.
Abstract translation: 提供了涉及尖端风扇的燃气涡轮发动机系统。 在这方面，代表性的燃气涡轮发动机系统包括：多级风扇，具有第一可转动的叶片组和第二可反向旋转的叶片组，第二可旋转叶片限定内部风扇和顶端风扇， 位于第一组可旋转叶片的下游; 以及行星差速齿轮组件，其操作以接收扭矩输入并且差分地施加到第一组叶片和第二组叶片的扭矩输入。
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公开(公告)号：WO2006110124A3
公开(公告)日：2006-11-23
申请号：PCT/US2004040097
申请日：2004-12-01
Applicant: UNITED TECHNOLOGIES CORP , SUCIU GABRIEL L , ROBERGE GARY D
Inventor： SUCIU GABRIEL L , ROBERGE GARY D
CPC classification number: F02C3/045 , F01D5/022 , F01D25/12 , F01D25/14 , F02C3/073 , F02C7/18 , F02K3/068 , Y02T50/675
Abstract: A tip turbine engine (10) includes a combustor (30) radially outward of a fan. In order to reduce the heat transfer from the combustor and the high-energy gas stream generated by the combustor, a cold air ejector (38) radially outward of the combustor extends from a forward end of the nacelle (12) to a point rearward of the combustor and an exhaust mixer (110). The cold air ejector includes an annular inlet (17) at the forward end of the nacelle. The cold air ejector draws air over the outer engine case (39) to provide a boundary between the nacelle and the hot outer engine case. The layer of air being pulled past the engine case ejects the heat, thereby preventing the heat from escaping into the nacelle or engine bay.
Abstract translation: 顶端涡轮发动机（10）包括在风扇的径向外侧的燃烧器（30）。 为了减少来自燃烧器的热传递和由燃烧器产生的高能气流，从燃烧器径向向外的冷空气喷射器（38）从机舱（12）的前端延伸到 燃烧器和排气混合器（110）。 冷空气喷射器包括在机舱前端的环形入口（17）。 冷空气喷射器将空气吸引到外部发动机壳体（39）上，以提供机舱和热外部发动机壳体之间的边界。 被拉动通过发动机舱的空气层排出热量，从而防止热量逸出到机舱或发动机舱中。
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