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公开(公告)号：US20170044983A1
公开(公告)日：2017-02-16
申请号：US14826905
申请日：2015-08-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Paul W. Duesler , Frederick M. Schwarz
CPC classification number: F02C7/185 , F02C7/141 , F02C7/18 , F02C7/20 , F02K3/115 , F04D19/02 , F04D29/5826 , F05D2260/213 , F28D1/0475 , F28D7/06 , F28D2021/0026 , F28F2009/222 , F28F2245/00 , F28F2250/06 , F28F2255/00 , Y02T50/675
Abstract: A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. The HEX may comprise a central manifold comprising an inlet portion, a first outlet portion, and a second outlet portion. The HEX may further comprise a plurality of tubes coupled to the central manifold, the plurality of tubes comprising at least a first tube, a second tube, a third tube, and a fourth tube, a shroud at least partially encasing said plurality of tubes, and a cooling air flow path defined by at least one of the shroud, the plurality of tubes, and an outer surface of the central manifold, wherein the cooling air flow path is orthogonal to said plurality of tubes.
Abstract translation: 提供一种用于在燃气涡轮发动机中冷却空气的热交换器（HEX）。 HEX可以包括中央歧管，其包括入口部分，第一出口部分和第二出口部分。 HEX还可以包括耦合到中央歧管的多个管，多个管包括至少第一管，第二管，第三管和第四管，至少部分地封装所述多个管的护罩， 以及由所述护罩，所述多个管和所述中央歧管的外表面中的至少一个限定的冷却空气流动路径，其中所述冷却空气流动路径与所述多个管正交。
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公开(公告)号：US20170044982A1
公开(公告)日：2017-02-16
申请号：US14826871
申请日：2015-08-14
Applicant: United Technologies Corporation
Inventor： Paul W. Duesler , Frederick M. Schwarz
CPC classification number: F02C7/185 , F01D25/12 , F02C7/141 , F02C7/32 , F05D2220/32 , F05D2240/91 , F05D2250/42 , F05D2260/213 , F05D2260/232 , F05D2260/30 , F05D2260/941 , F28F9/002 , F28F2265/26 , Y02T50/675
Abstract: A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. The HEX may comprise an intake manifold in fluid communication with a compressor section and configured to receive air from the compressor section, an outtake manifold in fluid communication with the intake manifold via a tube, and a cooling air flow path defined by at least one of an outer surface of the tube, an outer surface of the intake manifold, and an outer surface of the outtake manifold, wherein the cooling air flow path is orthogonal to said tube. The air from the intake manifold may travel through the tube to the outtake manifold and from the outtake manifold to a portion of the gas turbine engine.
Abstract translation: 提供一种用于在燃气涡轮发动机中冷却空气的热交换器（HEX）。 HEX可以包括与压缩机部分流体连通并被配置为从压缩机部分接收空气的进气歧管，经由管与进气歧管流体连通的出口歧管和由至少一个 管的外表面，进气歧管的外表面和出口歧管的外表面，其中冷却空气流动路径与所述管正交。 来自进气歧管的空气可以通过管移动到出口歧管，并且从出口歧管移动到燃气涡轮发动机的一部分。
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公开(公告)号：US20170044980A1
公开(公告)日：2017-02-16
申请号：US15062400
申请日：2016-03-07
Applicant: United Technologies Corporation
Inventor： Paul W. Duesler , Frederick M. Schwarz
CPC classification number: F02C7/18 , F02C7/141 , F02K3/115 , F04D29/5826 , F05D2260/213 , F28D1/0475 , F28D7/06 , F28D2021/0021 , F28D2021/0026 , F28F9/0268 , F28F9/24 , Y02T50/675
Abstract: A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. An adjustable damper is provided. The adjustable damper may be for damping a movement of the HEX relative to the gas turbing engine. An adjustable damper may comprise: a first tube; a second tube located at least partially within the first tube; a housing coupled to the second tube; a moveable member, the moveable member comprising a contacting surface in contact with the second tube; an adjusting member adjustably coupled to the housing; and a spring member located between the moveable member and the adjusting member, the spring member configured to at least one of compress or decompress in response to adjusting member moving relative to the housing.
Abstract translation: 提供一种用于在燃气涡轮发动机中冷却空气的热交换器（HEX）。 提供可调节阻尼器。 可调阻尼器可以用于阻止HEX相对于气体涡流发动机的运动。 可调节阻尼器可以包括：第一管; 至少部分地位于第一管内的第二管; 联接到所述第二管的壳体; 可移动构件，所述可移动构件包括与所述第二管接触的接触表面; 可调节地联接到所述壳体的调节构件; 以及位于所述可移动构件和所述调节构件之间的弹簧构件，所述弹簧构件构造成响应于调节构件相对于所述壳体移动而被压缩或减压中的至少一个。
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公开(公告)号：US20170023012A1
公开(公告)日：2017-01-26
申请号：US14804728
申请日：2015-07-21
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz
CPC classification number: F04D29/526 , B64D33/02 , F01D25/243 , F01D25/246 , F02C7/04 , F02K3/06 , F04D19/002 , F04D29/38 , F04D29/542 , F05B2220/303 , F05B2230/80 , F05B2250/60 , F05D2240/14
Abstract: The present disclosure relates generally to a fan nacelle assembly circumferentially surrounding a fan section, the fan nacelle assembly including an inner wall including an inner wall axial length, and an outer wall an outer wall axial length, wherein the outer wall axial length is greater than the inner wall axial length.
Abstract translation: 本公开总体上涉及围绕风扇部分的风扇机舱组件，风扇机舱组件包括包括内壁轴向长度的内壁和外壁轴向长度的外壁，其中外壁轴向长度大于 内壁轴向长度。
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公开(公告)号：US20160369695A1
公开(公告)日：2016-12-22
申请号：US14740636
申请日：2015-06-16
Applicant: United Technologies Corporation
Inventor： Jeffrey F. Perlak , Joseph B. Staubach , Frederick M. Schwarz , James D. Hill
CPC classification number: F02C7/10 , F02C3/04 , F02C7/08 , F02C9/18 , F05D2220/32 , F05D2260/20 , F05D2270/112 , F05D2270/3032 , Y02T50/676
Abstract: A recuperated gas turbine engine includes an engine core that has a compressor section, a combustor section, and a turbine section. An exhaust duct is located downstream of the turbine section for receiving a hot turbine exhaust stream from the turbine section. The exhaust duct includes a heat exchanger and a temperature-control module upstream of the heat exchanger. A compressor bleed line leads from the compressor section into the heat exchanger and a compressor return line leads from the heat exchanger into the engine core upstream of the combustor section. The compressor bleed line is operable to selectively feed compressed air to the heat exchanger, and the temperature-control module is operable to selectively modulate at least one of temperature and flow of the hot turbine exhaust stream with respect to the heat exchanger.
Abstract translation: 复原燃气涡轮发动机包括具有压缩机部分，燃烧器部分和涡轮部分的发动机芯。 排气管道位于涡轮机部分的下游，用于从涡轮机部分接收热涡轮机废气流。 排气管道包括在热交换器上游的热交换器和温度控制模块。 压缩机排气管路从压缩机部分引入热交换器，并且压缩机返回管线从热交换器引导到燃烧器部分上游的发动机芯。 压缩机排气管线可操作以选择性地将压缩空气供给到热交换器，并且温度控制模块可操作以选择性地调节热涡轮机废气流相对于热交换器的温度和流量中的至少一个。
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Patent Agency Ranking
公开(公告)号：US20160348591A1
公开(公告)日：2016-12-01
申请号：US14566840
申请日：2014-12-11
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Frederick M. Schwarz
CPC classification number: F02C7/36 , F01D9/041 , F01D9/042 , F01D25/16 , F01D25/168 , F01D25/246 , F01D25/28 , F02C3/04 , F02K3/06 , F04D25/045 , F04D29/321 , F04D29/325 , F05D2220/32 , F05D2240/35 , F05D2260/40311 , F05D2260/606
Abstract: A gas turbine engine turbine comprises a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis. A low pressure turbine is configured to rotate with a low pressure compressor as a low pressure spool in a second direction about the central axis. A mid-turbine frame supports the high pressure turbine. The mid-turbine frame includes a first bearing supporting the high pressure turbine, and a strut supporting the first bearing at a location between the high pressure turbine and the low pressure turbine. A plurality of vanes are associated with a first stage of the low pressure turbine. The plurality of vanes are positioned within the mid-turbine frame.
Abstract translation: 燃气涡轮发动机涡轮机包括高压涡轮机，其构造成以围绕中心轴线的第一方向的高压压缩机作为高压压力机旋转。 低压涡轮机被构造成以低压压缩机作为低压阀芯在围绕中心轴线的第二方向上旋转。 中涡轮机架支撑高压涡轮机。 中间涡轮机框架包括支撑高压涡轮机的第一轴承和在高压涡轮机和低压涡轮机之间的位置处支撑第一轴承的支柱。 多个叶片与低压涡轮机的第一级相关联。 多个叶片位于中涡轮机框架内。
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公开(公告)号：US20160305443A1
公开(公告)日：2016-10-20
申请号：US15102155
申请日：2014-12-16
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Michael A. Weisse
Abstract: An airfoil for a turbine engine includes an airfoil body with a cover mounting support, a first cover, and a second cover. The airfoil body includes a solid perimeter portion surrounding a recess formed into at least one of a suction side and a pressure side of the airfoil body, while the cover mounting support extends through the recess. The first cover can be engaged with a first edge of the recess and joined to a first portion of the cover mounting support by a first stir weld. The second cover can be engaged with a second edge of the recess, and joined to a second portion of the cover mounting support by a second stir weld.
Abstract translation: 用于涡轮发动机的翼型件包括具有盖安装支撑件的机翼本体，第一盖和第二盖。 机翼本体包括围绕形成为翼型体的吸力侧和压力侧中的至少一个的凹部的固体周边部分，而盖安装支撑件延伸穿过凹部。 第一盖可以与凹部的第一边缘接合，并通过第一搅拌焊接接合到盖安装支撑件的第一部分。 第二盖可以与凹部的第二边缘接合，并且通过第二搅拌焊接接合到盖安装支架的第二部分。
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公开(公告)号：US20160245184A1
公开(公告)日：2016-08-25
申请号：US14626534
申请日：2015-02-19
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , William G. Sheridan
CPC classification number: F02C7/36 , F02C3/107 , F02K3/06 , F05D2220/36 , F05D2230/51 , F05D2230/52 , F05D2260/40311 , F05D2260/74
Abstract: A turbine engine is provided that includes a fan rotor, a first compressor rotor, a second compressor rotor, a third compressor rotor, a first turbine rotor, a second turbine rotor, a third turbine rotor and a gear train. The fan rotor and the first compressor rotor are connected to the first turbine rotor through the gear train. The second compressor rotor is connected to the second turbine rotor. The third compressor rotor is connected to the third turbine rotor.
Abstract translation: 提供一种涡轮发动机，其包括风扇转子，第一压缩机转子，第二压缩机转子，第三压缩机转子，第一涡轮机转子，第二涡轮机转子，第三涡轮转子和齿轮系。 风扇转子和第一压缩机转子通过齿轮系连接到第一涡轮转子。 第二压缩机转子连接到第二涡轮转子。 第三压缩机转子连接到第三涡轮转子。
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公开(公告)号：US20160201569A1
公开(公告)日：2016-07-14
申请号：US14875750
申请日：2015-10-06
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Robert E. Malecki
CPC classification number: F02C7/36 , B64D33/02 , B64D2033/0286 , F02C3/10 , F02C3/107 , F02K3/06 , F02K3/068 , F05D2220/36 , Y02T50/672
Abstract: A propulsion system according to an example of the present disclosure includes, among other things, a geared architecture configured to drive a fan section including a fan, and a turbine section configured to drive the geared architecture. The turbine section has an exit point, and a diameter (Dt) defined as the outer diameter of a last blade airfoil stage in the turbine section at the exit point. A nacelle surrounds a core engine housing. The fan is configured to deliver air into a bypass duct defined between the nacelle and the core engine housing. A core engine exhaust nozzle is downstream of the exit point. A downstream most point of the core engine exhaust nozzle is defined at a distance (Lc or Ln) from the exit point.
Abstract translation: 根据本公开的示例的推进系统包括构造成驱动包括风扇的风扇部分和被配置为驱动齿轮架构的涡轮机部分的齿轮架构。 涡轮部分具有出口点，并且直径（Dt）被定义为在出口处涡轮部分中的最后叶片翼型段的外径。 机舱围绕核心发动机外壳。 风扇被配置为将空气输送到限定在机舱和核心发动机壳体之间的旁路管道中。 核心发动机排气喷嘴位于出口点的下游。 核心发动机排气喷嘴的下游最点位于出口点的距离（Lc或Ln）处。
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150.发明申请公开(公告)号：US20160153310A1
公开(公告)日：2016-06-02
申请号：US14905994
申请日：2014-07-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frederick M. Schwarz , Bruce L. Morin
CPC classification number: F01D25/04 , F01D5/06 , F01D5/142 , F01D9/06 , F01D15/12 , F01D17/105 , F02C3/107 , F02K3/06 , F04D29/321 , F04D29/325 , F05D2220/32 , F05D2220/36 , F05D2240/24 , F05D2260/40311 , F05D2260/96 , F05D2270/02 , F05D2270/333 , Y02T50/673
Abstract: A turbine section including a high pressure turbine, an intermediate pressure turbine and a fan drive turbine, the fan drive turbine driving a gear reduction to in turn drive a fan, and effecting a reduction in the speed of the fan relative to an input speed from the fan drive turbine and said high pressure turbine driving a high pressure compressor, and the intermediate pressure turbine driving a low pressure compressor, with the intermediate pressure turbine having a number of turbine blades in at least one row, and the turbine blades operating at least some of the time at a rotational speed, and the number of turbine blades in the at least one row, and the rotational speed being such that the following formula holds true for the at least one row of the intermediate pressure turbine: (number of blades×speed)/60?5500 Hz.
Abstract translation: 包括高压涡轮机，中压涡轮机和风扇驱动涡轮机的涡轮机部分，风扇驱动涡轮驱动齿轮减速，从而驱动风扇，并且相对于输入速度降低风扇的速度， 所述风扇驱动涡轮机和所述高压涡轮机驱动高压压缩机，并且所述中压涡轮机驱动低压压缩机，所述中压涡轮机具有至少一排中的多个涡轮叶片，并且所述涡轮叶片至少工作 一些转速的时间，以及至少一行中的涡轮叶片的数量，并且转速使得下列公式对于至少一排中压涡轮机成立：（叶片数量 ×速度）/ 60〜5500Hz。
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