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公开(公告)号：US20170226891A1
公开(公告)日：2017-08-10
申请号：US15017127
申请日：2016-02-05
Applicant: United Technologies Corporation
Inventor： Wendell V. Twelves, JR. , Evan Butcher , Lexia Kironn , Joe Ott , Gary D. Roberge
CPC classification number: F01D25/005 , B32B3/02 , B32B3/08 , B32B9/005 , B32B9/041 , B32B15/00 , B32B15/01 , B32B15/011 , B32B15/012 , B32B15/013 , B32B15/015 , B32B15/016 , B32B15/017 , B32B15/043 , B32B15/088 , B32B15/14 , B32B15/18 , B32B15/20 , B32B27/34 , B32B2250/04 , B32B2262/0269 , B32B2307/56 , B32B2571/02 , F01D21/045 , F01D21/10 , F01D25/24 , F41H5/04 , F41H5/0442 , Y02T50/672
Abstract: An apparatus includes first, second, and third layers. The first layer includes a plurality of flanges. The second layer includes a deformable membrane. The second layer is connected to the first layer along a first major surface of the deformable membrane. The third layer is connected to the second layer along a second major surface of the deformable membrane opposite the first major surface. The third layer includes a first series of internal structures.
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公开(公告)号：US20160290226A1
公开(公告)日：2016-10-06
申请号：US15104100
申请日：2014-09-09
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
IPC: F02C3/04
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: 一种反向核心涡轮风扇发动机，其包括具有风扇的推进部分和风扇顶端涡轮机，其构造成将空气输送到芯管，包括设置在推进部分后面的第一部分，并将空气直接引向空气的入口 反向气体发生器和第二部分，其构造成从气体发生器的出口接收空气，并将空气向前推进到推进器的径向外侧，朝向推进器中的风扇顶端涡轮机，从而驱动推进器。
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公开(公告)号：US20150377040A1
公开(公告)日：2015-12-31
申请号：US14761029
申请日：2014-02-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge , George J. Kramer
CPC classification number: F01D5/288 , B64D15/00 , B64D2045/009 , F01D5/02 , F01D9/041 , F01D17/14 , F01D25/005 , F01D25/02 , F01D25/24 , F02C3/04 , F05D2220/32 , F05D2220/36 , F05D2230/70 , F05D2230/80 , F05D2230/90 , F05D2300/512 , Y02T50/673
Abstract: A fan section to be incorporated into a gas turbine engine has a rotor and a plurality of fan blades. The fan blades deliver air into a bypass duct defined inwardly of the nacelle and into a core engine. There are static vanes inward of the nacelle. A surface of the fan section is provided with a removable film material. A gas turbine engine and a method of refurbishing a surface are also disclosed.
Abstract translation: 并入燃气轮机的风扇部分具有转子和多个风扇叶片。 风扇叶片将空气输送到定位在机舱内部并进入核心发动机的旁路管道中。 机舱内有静叶片。 风扇部分的表面设置有可移除的膜材料。 还公开了一种燃气涡轮发动机和一种翻新表面的方法。
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公开(公告)号：US20150361888A1
公开(公告)日：2015-12-17
申请号：US14768232
申请日：2014-02-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge
IPC: F02C7/06
CPC classification number: F02C7/06 , F01D25/18 , F02C3/107 , F02C7/36 , F02K3/06 , F05D2260/40311 , F05D2260/98
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, a shaft including at least one bearing, a speed change device in communication with the shaft, a first lubrication system in communication with the at least one bearing and a second lubrication system in communication with the speed change device.
Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机包括：轴，包括至少一个轴承，与轴连通的变速装置，与所述至少一个轴承连通的第一润滑系统和第二润滑系统 与变速装置通信。
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公开(公告)号：US20140241856A1
公开(公告)日：2014-08-28
申请号：US13777723
申请日：2013-02-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge , Gabriel L. Suciu
IPC: F02C3/067
CPC classification number: F02C3/067 , F02C3/107 , F02K3/072 , F02K3/077 , 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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Patent Agency Ranking
公开(公告)号：US11156090B2
公开(公告)日：2021-10-26
申请号：US14761348
申请日：2013-12-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge
IPC: F01D5/02 , F01D5/28 , F01D5/34 , F01D5/22 , F04D29/02 , F04D29/32 , F02K3/06 , F01D5/30 , F04D29/34 , F01D5/14 , F02C3/04
Abstract: A fan section for a gas turbine engine is disclosed herein. The fan may include a rotor disk and a plurality of airfoils fixedly attached to and supported by the rotor disk as a single unitary piece. The airfoils may extend radially outward from the rotor disk with respect to an engine axis. The rotor disk may be made of metal and the airfoils may each be made at least partially of an organic matrix composite.
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公开(公告)号：US20210247152A1
公开(公告)日：2021-08-12
申请号：US16784630
申请日：2020-02-07
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
Abstract: A heat exchanger duct includes a wall having ends spaced along a central axis. An inlet manifold is positioned within a downstream portion of the duct at a radially outward location. An outlet manifold is positioned within an upstream portion of the duct at a radially outward location. At least one of the inlet and outlet manifolds extend at least 10 degrees around the circumference of the duct. A central manifold is disposed between the inlet and outlet manifolds, and radially inwardly of the inlet and outlet manifolds. Heat exchanger entrance elements extend radially inward from the inlet manifold to the central manifold, and heat exchanger exit elements extend radially outward from the central manifold to the outlet manifold. A gas turbine engine is also disclosed.
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公开(公告)号：US20210207564A1
公开(公告)日：2021-07-08
申请号：US16736342
申请日：2020-01-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Curtis C. Cowan , Rebecca R. Dunnigan , Gary D. Roberge
IPC: F02M35/10
Abstract: A cooling system for a gas turbine engine may comprise a plenum extending circumferentially around an outer engine case structure. The plenum may comprise a supply conduit and a return conduit. The supply conduit and the return conduit may be in fluid communication with a heat exchanger. The heat exchanger may be disposed between the outer engine case structure and an inner engine case structure. The plenum may be configured to provide enhance heat transfer for the cooling system.
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公开(公告)号：US20210207540A1
公开(公告)日：2021-07-08
申请号：US16732774
申请日：2020-01-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge
Abstract: A cryogenic fuel auxiliary power system for an engine may include a cryogenic fuel supply, a first valve in fluid communication with the cryogenic fuel supply and configured to control a fuel flow, a first heat exchanger, configured to receive the fuel flow, in fluid communication with the first valve and a combustion chamber of the engine, and a fuel cell in fluid communication between the first valve and the first heat exchanger.
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公开(公告)号：US11041439B2
公开(公告)日：2021-06-22
申请号：US16131716
申请日：2018-09-14
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
Abstract: A gas turbine engine system includes a gas turbine engine and a turbo-generator. The gas turbine engine includes a heat exchange system configured to transfer thermal energy from an air flow (i.e., inlet air flow or exhaust gas flow) to a fuel to produce a gaseous fuel. The turbo-generator includes a fuel turbine fluidly coupled to the heat exchange system and a combustor of the gas turbine engine, a fuel pump configured to be driven by the fuel turbine and fluidly coupled to the heat exchange system, and a motor/generator configured to be driven by the fuel turbine. The fuel turbine is configured to extract energy from expansion of the gaseous fuel to produce a gaseous fuel for combustion in the combustor. The motor/generator includes a cooling jacket, which is fluidly coupled to the fuel pump.
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