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公开(公告)号：US10197008B2
公开(公告)日：2019-02-05
申请号：US14768714
申请日：2014-02-14
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
Abstract: A turbofan engine that includes a first flowpath, a second flowpath, a third flowpath, and a third flowpath exhaust nozzle is provided. The first flowpath is radially inboard of the second flowpath at a location upstream of a core section of the turbofan engine. The third flowpath is radially outboard of the second flowpath at the location upstream of the core section. The third flowpath exhaust nozzle defines a plurality of third flowpath exhaust exit ports through which gas traveling along the third flowpath may be discharged. An area or a geometry of each of the plurality of third flowpath exhaust exit ports is independently and selectively adjustable. A method for operating the turbofan engine includes independently and selectively adjusting an area or a geometry of at least one of the plurality of third flowpath exhaust exit ports to achieve a desired engine operation.
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162.发明授权公开(公告)号：US10024610B2
公开(公告)日：2018-07-17
申请号：US15096668
申请日：2016-04-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge
IPC: F28D15/00 , F28F21/08 , B23P15/26 , B22F3/11 , B22F7/00 , B23K37/00 , B32B5/18 , B32B5/20 , B32B15/01 , F01D25/12 , F02C7/12 , F16L59/02 , F28F13/00 , B23K26/70 , F28F7/02 , F28F13/18 , F28D1/047 , C22C1/08
Abstract: A method of making a light weight housing for an internal component is provided. The method including the steps of: forming a first metallic foam core into a desired configuration; forming a second metallic foam core into a desired configuration; inserting an internal component into the first metallic foam core; placing the second metallic foam core adjacent to the first metallic core in order to secure the internal component between the first metallic foam core and the second metallic foam core; applying an external metallic shell to an exterior surface of the first metallic foam core and the second metallic foam core; and securing an inlet fitting and an outlet fitting to the housing, wherein a thermal management fluid path for the internal component into and out of the housing is provided by the inlet fitting and the outlet fitting.
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公开(公告)号：US20180179639A1
公开(公告)日：2018-06-28
申请号：US15388286
申请日：2016-12-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge , William J. Brindley
CPC classification number: C23C24/04 , B22F3/02 , B29C64/00 , B29C64/153 , B33Y10/00 , B33Y80/00 , F01D25/005 , F05D2220/323 , F05D2230/90
Abstract: A method for forming a sheet structure includes depositing at least one layer of material on a main formation surface of a main tool using a cold-spray technique, the main tool having a plurality of tool portions that each have a formation surface such that the formation surface of each of the plurality of tool portions forms the main formation surface corresponding to a desired structure shape of the sheet structure. The method also includes removing the at least one layer of material from the main formation surface to create the sheet structure.
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公开(公告)号：US09932902B2
公开(公告)日：2018-04-03
申请号：US14797253
申请日：2015-07-13
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
CPC classification number: F02C7/20 , F01D25/16 , F01D25/162 , F02C3/04 , F02C7/06 , F05D2220/32 , F05D2230/60 , F05D2240/24 , F05D2240/50 , F05D2240/54 , F05D2240/60 , F05D2250/36 , F16C19/55 , F16C35/06
Abstract: A gas turbine engine includes a compressor portion, a combustor fluidly connected to the compressor portion via a primary flowpath, and a turbine portion fluidly connected to the combustor via the primary flowpath. The turbine section includes a first turbine portion and a second turbine portion. The second turbine portion is at a low pressure relative to the first turbine portion. A first turbine shaft is supported relative to a second turbine shaft by a first bearing, the first bearing having an inner diameter and an outer diameter, with the inner diameter of the first bearing being connected to one of the first shaft and the second shaft and the outer diameter of the first bearing being connected to the other of the first shaft and the second shaft.
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165.发明申请公开(公告)号：US20170292797A1
公开(公告)日：2017-10-12
申请号：US15096668
申请日：2016-04-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge
CPC classification number: F28F21/08 , B22F3/1125 , B22F3/162 , B22F5/006 , B22F7/002 , B22F7/006 , B23K26/703 , B23K37/003 , B23P15/26 , B32B5/18 , B32B5/20 , B32B15/01 , B32B2305/022 , C22C2001/083 , F01D25/12 , F02C7/12 , F05D2230/22 , F05D2300/612 , F16L59/02 , F28D1/0477 , F28D15/00 , F28F7/02 , F28F13/003 , F28F13/185
Abstract: A method of making a light weight housing for an internal component is provided. The method including the steps of: forming a first metallic foam core into a desired configuration; forming a second metallic foam core into a desired configuration; inserting an internal component into the first metallic foam core; placing the second metallic foam core adjacent to the first metallic core in order to secure the internal component between the first metallic foam core and the second metallic foam core; applying an external metallic shell to an exterior surface of the first metallic foam core and the second metallic foam core; and securing an inlet fitting and an outlet fitting to the housing, wherein a thermal management fluid path for the internal component into and out of the housing is provided by the inlet fitting and the outlet fitting.
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Patent Agency Ranking
公开(公告)号：US20160377026A1
公开(公告)日：2016-12-29
申请号：US14753637
申请日：2015-06-29
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
CPC classification number: F02K1/08 , F02K1/002 , F02K1/15 , F02K1/42 , F02K1/58 , F02K1/763 , F02K3/02
Abstract: An exhaust nozzle for a gas turbine engine according to an example of the present disclosure includes, among other things, a duct having a first surface and a second surface extending about a duct axis to define an exhaust flow path, and at least one effector positioned along the first surface. The at least one effector is pivotable about an effector axis to vary a throat area of the exhaust flow path. The at least one effector tapers along the effector axis. A method of exhaust control for a gas turbine engine is also disclosed.
Abstract translation: 根据本公开的示例的用于燃气涡轮发动机的排气喷嘴包括具有第一表面和第二表面的管道，管道围绕管道轴线延伸以限定排气流动路径，并且至少一个效应器定位 沿着第一个表面。 所述至少一个效应器围绕效应器轴线枢转以改变排气流动路径的喉部区域。 至少一个效应器沿着效应器轴线逐渐变细。 还公开了一种用于燃气涡轮发动机的排气控制方法。
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公开(公告)号：US20160298539A1
公开(公告)日：2016-10-13
申请号：US15103833
申请日：2014-12-12
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
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: 本公开一般涉及涡轮机械，其中旋转部件邻近反向旋转部件设置，以便实现比通过邻近固定部件设置的旋转部件实现的相对旋转速度。
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公开(公告)号：US20160237907A1
公开(公告)日：2016-08-18
申请号：US14745550
申请日：2015-06-22
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , Jesse M. Chandler , Joseph Brent Staubach , Gary D. Roberge
CPC classification number: F02C7/18 , F02C7/185 , F05D2260/213 , Y02T50/676
Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passing the tapped air through a heat exchanger and then to a cooling compressor, which compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. The cooling compressor rotates at a speed proportional to a speed of at least one rotor in the turbine section. The cooling compressor is allowed to rotate at a speed that is not proportional to a speed of the at least one rotor under certain conditions. An intercooling system for a gas turbine engine is also disclosed.
Abstract translation: 燃气涡轮发动机包括具有下游排出口的高压压缩机的主压缩机部分和更多的上游位置。 涡轮机部分具有高压涡轮机。 分接头从压缩机部分中的上游位置中的至少一个抽头抽吸空气，使抽头的空气通过热交换器，然后到达冷却压缩机，冷却压缩机压缩热交换器下游的空气，并将空气输送到高压涡轮机 。 冷却压缩机以与涡轮机部分中的至少一个转子的速度成比例的速度旋转。 允许冷却压缩机在某些条件下以与至少一个转子的速度成比例的速度旋转。 还公开了一种用于燃气涡轮发动机的中间冷却系统。
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公开(公告)号：US20160195011A1
公开(公告)日：2016-07-07
申请号：US14797250
申请日：2015-07-13
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
CPC classification number: F02C3/107 , F01D5/06 , F01D25/24 , F02C3/113 , F02C7/36 , F02K3/04 , F02K3/06 , F04D29/321 , F04D29/325 , F05D2220/32 , F05D2240/35 , F05D2240/60 , F05D2260/40 , F05D2260/40311
Abstract: A gas turbine engine includes a fan section, a compressor section aft of the fan section, a combustor fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor. The turbine section includes at least a first turbine and a second turbine. The second turbine operates at a higher pressure than the first turbine. A shaft is connected to the first turbine section such that the first turbine section is operable to drive rotation of the shaft. The shaft is a rotational input for a split gear and the split gear is connected to the fan and at least one of the multiple compressors.
Abstract translation: 燃气涡轮发动机包括风扇部分，风扇部分后部的压缩机部分，流体连接到压缩机部分的燃烧器和流体连接到燃烧器的涡轮机部分。 涡轮部分包括至少第一涡轮机和第二涡轮机。 第二涡轮机在比第一涡轮机更高的压力下运行。 轴连接到第一涡轮部分，使得第一涡轮部分可操作以驱动轴的旋转。 轴是用于分离齿轮的旋转输入，并且分离齿轮连接到风扇和多个压缩机中的至少一个。
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公开(公告)号：US20160195010A1
公开(公告)日：2016-07-07
申请号：US14797264
申请日：2015-07-13
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
CPC classification number: F02C3/04 , F01D1/20 , F01D1/26 , F01D5/142 , F01D9/06 , F01D25/162 , F02C7/06 , F02K3/072 , F05D2220/3213 , F05D2240/12 , F05D2260/40311 , Y02T50/673
Abstract: A gas turbine engine includes a compressor section, a combustor, and a turbine section. The turbine section includes a first turbine portion and a second turbine portion, with the first and second turbine portions being counter-rotating turbine portions. A transition duct transitions fluid flow from the first turbine portion to the second turbine portion. The transition duct is a vaneless transition duct.
Abstract translation: 燃气涡轮发动机包括压缩机部分，燃烧器和涡轮部分。 涡轮部分包括第一涡轮机部分和第二涡轮机部分，其中第一和第二涡轮机部分是反向旋转的涡轮机部分。 过渡管道将从第一涡轮机部分流向第二涡轮部分的流体流动。 过渡管道是无叶过渡管道。
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