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公开(公告)号：US10145302B2
公开(公告)日：2018-12-04
申请号：US14768232
申请日：2014-02-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge
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.
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公开(公告)号：US10119475B2
公开(公告)日：2018-11-06
申请号：US14767050
申请日：2014-01-24
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
Abstract: A gas turbine engine assembly according to an exemplary aspect of the present disclosure includes, among other things, a geared architecture configured to rotatably couple a turbine and a compressor of an engine to rotate the compressor at a different speed than the turbine and a fan.
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公开(公告)号：US20180179638A1
公开(公告)日：2018-06-28
申请号：US15388223
申请日：2016-12-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge , William J. Brindley
CPC classification number: C23C24/04 , B22F3/02 , B22F3/24 , B22F5/009 , B22F5/04 , B22F7/08 , B22F2003/244 , B22F2003/247 , B22F2005/005 , B22F2998/10 , B33Y80/00 , F01D25/005 , F05D2230/31
Abstract: A method for forming a metallic structure having a secondary component includes positioning the secondary component on a main formation surface of a main tool, the main formation surface corresponding to a desired shape of a first layer of material. The method also includes depositing a layer of material on the secondary component and the main formation surface using a cold-spray technique such that the layer of material bonds to the secondary component. The method also includes removing the layer of material and the secondary component to form the metallic structure.
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公开(公告)号：US20180178331A1
公开(公告)日：2018-06-28
申请号：US15388567
申请日：2016-12-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge , William J. Brindley
CPC classification number: B23P6/045 , B22F3/02 , B22F5/009 , B22F9/04 , B22F2998/10 , C22C1/05 , C22C1/1084 , C23C24/04 , F01D25/005 , F05D2220/32 , F05D2230/31 , F05D2300/10
Abstract: A method for forming a reinforced metallic structure includes depositing a mixture of metallic particles and reinforcing particles on a formation surface of a tool by cold-spraying the metallic particles to form a layer of mixed material, the formation surface corresponding to a desired shape of the reinforced metallic structure. The method also includes removing the layer of mixed material from the formation surface to create the reinforced metallic structure
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公开(公告)号：US09945325B2
公开(公告)日：2018-04-17
申请号：US14646990
申请日：2013-11-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge
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.
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Patent Agency Ranking
公开(公告)号：US20180051703A1
公开(公告)日：2018-02-22
申请号：US15242701
申请日：2016-08-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge
Abstract: A gas turbine engine has a compressor section with a low pressure compressor and a high pressure compressor having a downstream end. A cooling air system includes a tap from a location upstream of the downstream most location. The tap passes air to a boost compressor, and the boost compressor passes the air back to a location to be cooled. The boost compressor is driven by a shaft in the engine through an epicyclic gear system. A speed control changes the relative speed between an input and an output to the epicyclic gear system.
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公开(公告)号：US20180051628A1
公开(公告)日：2018-02-22
申请号：US15242674
申请日：2016-08-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge
Abstract: A gas turbine engine has a compressor section with a low pressure compressor and a high pressure compressor. The high pressure compressor has a downstream most location. A cooling air system includes a tap from a location upstream of the downstream most location. The tap passes air to a boost compressor and a heat exchanger, which passes the air back to a location to be cooled. The boost compressor is driven by a shaft which drives the lower pressure compressor.
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公开(公告)号：US20170292183A1
公开(公告)日：2017-10-12
申请号：US15096685
申请日：2016-04-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge
Abstract: A method of making a light weight component is provided. The method including the steps of: forming a metallic foam core into a desired configuration; and applying an external metallic shell to an exterior surface of the metallic foam core after it has been formed into the desired configuration.
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公开(公告)号：US20170291388A1
公开(公告)日：2017-10-12
申请号：US15096653
申请日：2016-04-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge
IPC: B32B5/18
CPC classification number: B32B5/18 , B22F3/1055 , B22F3/26 , B22F7/08 , B22F2998/10 , B23K26/361 , B23K26/40 , B23K2103/02 , B23K2103/08 , B32B5/00 , B32B15/00 , B32B15/01 , B32B15/012 , B32B15/013 , B32B15/04 , B32B15/043 , B32B15/046 , B32B15/18 , B32B2266/045 , C23C4/129 , C23C4/134 , C23C4/18 , C23C24/04 , Y02P10/295 , B22F7/006
Abstract: A method of making a light weight component is provided. The method including the steps of: forming a first metallic foam core into a desired configuration; applying an external metallic shell to a discrete exterior surface of the first metallic foam core after it has been formed into the desired configuration; arranging the first metallic form core to be adjacent to a second metallic foam core also formed into a desired configuration to form a desired pre-form shape, wherein an applied external metallic shell located on a discrete surface of the second metallic foam core is adjacent to the external metallic shell applied to the discrete exterior surface of the first metallic foam core; and applying an external metallic shell to an exterior surface of the desired pre-form shape.
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公开(公告)号：US20170284220A1
公开(公告)日：2017-10-05
申请号：US15089835
申请日：2016-04-04
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
Abstract: A gas turbine engine includes a compressor having a first compressor section and a second compressor section, a combustor fluidly connected to the compressor, and a turbine fluidly connected to the combustor. The turbine has a first turbine section and a second turbine section. A first shaft connects the first compressor section and the first turbine section. A second shaft connects the second compressor section and the second turbine section. A fan is connected to the first shaft via a geared architecture. A low speed accessory gearbox is interfaced with the first shaft via a mechanical interface. The low speed accessory gearbox includes a mechanical brake.
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