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公开(公告)号：US20170276011A1
公开(公告)日：2017-09-28
申请号：US15079392
申请日：2016-03-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jesse M. Chandler , Gabriel L. Suciu , Joseph Stack
CPC classification number: F01D17/162 , F01D9/04 , F01D9/042 , F01D17/12 , F01D17/14 , F01D17/16 , F01D25/34 , F16H19/005 , F16H49/001 , Y02T50/671 , Y02T50/673
Abstract: An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.
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公开(公告)号：US20170254219A1
公开(公告)日：2017-09-07
申请号：US15062442
申请日：2016-03-07
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Brian D. Merry
Abstract: A gas turbine engine comprises an engine having a compressor section, and a turbine section. A firewall and accessory pumps are mounted on a downstream side of the firewall. The accessory pumps are driven by electric motors mounted on the firewall on an upstream side of the firewall.
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公开(公告)号：US20170167384A1
公开(公告)日：2017-06-15
申请号：US14967518
申请日：2015-12-14
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , Jesse M. Chandler , William K. Ackermann , Matthew R. Feulner , Om P. Sharma
CPC classification number: F02C7/18 , F01D5/08 , F02C3/04 , F02C7/143 , F02C7/185 , F02C9/18 , F02K3/06 , F04D27/0215 , F04D29/582 , F05D2220/32 , F05D2220/3219 , F05D2240/24 , F05D2260/205 , F05D2260/211 , F05D2260/213 , Y02T50/676
Abstract: A compressor section for use in a gas turbine engine comprises a compressor rotor having a hub and a plurality of blades extending radially outwardly from the hub and an outer housing surrounding an outer periphery of the blades. A tap taps air at a radially outer first location, passing the tapped air through a heat exchanger, and returning the tapped air to an outlet at a second location which is radially inward of the first location, to provide cooling air adjacent to the hub. A gas turbine engine is also disclosed.
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公开(公告)号：US09611048B2
公开(公告)日：2017-04-04
申请号：US14187038
申请日：2014-02-21
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
CPC classification number: B64D29/06 , F01D9/02 , F01D25/24 , F01D25/28 , F05D2220/32 , F05D2230/70 , F05D2230/72 , F05D2230/80 , F05D2240/121 , F05D2240/122 , F05D2240/128 , F05D2240/1281 , F05D2240/14 , F05D2240/55 , F05D2240/91 , F05D2250/192 , F05D2250/292 , F05D2250/294 , F05D2250/34 , F05D2250/75 , F05D2260/96 , Y10T29/49721
Abstract: A gas turbine engine nacelle includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. A rail is coupled to the fore pylon connecting portion and extends in the aft direction from the first annular portion. A second annular portion is positioned aft of the first portion and coupled to the rail. The second portion is movable along an engine core centerline between a closed position and at least one open position. The second annular portion is configured to engage with the first annular portion in the closed position, thereby providing access to the engine core. A mating axial groove and rib connection is located between the first annular portion and the second annular portion.
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公开(公告)号：US09581108B2
公开(公告)日：2017-02-28
申请号：US14184376
申请日：2014-02-19
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
CPC classification number: F02K1/763 , B23P19/04 , B64D29/00 , B64D33/04 , F02K1/60 , F02K1/605 , F02K1/62 , F02K1/64 , F02K1/72 , F05D2260/50 , Y10T29/49229
Abstract: One embodiment includes a pivot thrust reverser with a first pivot door with an upper linkage and a lower linkage and a second pivot door, spaced from the first pivot door, with an upper linkage and a lower linkage. A first actuator is located on a first side of an attachment location to drive the first pivot door. A second actuator is located on a second side of the attachment location to drive the second pivot door. A third actuator is located substantially radially opposite the attachment location to drive both the first pivot door and the second pivot door. The first pivot door is configured to be pivoted from a stowed position to a deployed position by both the first actuator and the third actuator. The second pivot door is configured to be pivoted from the stowed position to the deployed position by both the second actuator and the third actuator.
Abstract translation: 一个实施例包括枢转推力反向器，其具有带有上连杆的第一枢转门和下连杆以及与第一枢转门隔开的第二枢转门，具有上连杆和下连杆。 第一致动器位于附接位置的第一侧以驱动第一枢轴门。 第二致动器位于附接位置的第二侧以驱动第二枢转门。 第三致动器基本上位于与附接位置径向相对的位置，以驱动第一枢转门和第二枢转门。 第一枢转门构造成通过第一致动器和第三致动器由收起位置枢转到展开位置。 第二枢转门构造成通过第二致动器和第三致动器由收起位置枢转到展开位置。
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Patent Agency Ranking
公开(公告)号：US09567062B2
公开(公告)日：2017-02-14
申请号：US14440895
申请日：2013-03-14
Applicant: United Technologies Corporation
Inventor： Jesse M. Chandler , Gabriel L. Suciu
IPC: B64D27/14 , B64C39/06 , B64D33/04 , B64C3/14 , B64C39/12 , B64C39/10 , B64C5/06 , F02K1/56 , F02K1/78
CPC classification number: B64C3/14 , B64C5/06 , B64C39/068 , B64C39/10 , B64C39/12 , B64D27/14 , B64D33/04 , F02K1/56 , F02K1/78
Abstract: An aircraft including a fuselage having a forward portion and an aft portion with a propulsion system mounted within the aft portion of the fuselage. A burst zone is defined that extends outward from the propulsion system. The aircraft includes a box wing extending from the aft portion of the fuselage to a forward portion of the fuselage that is disposed outside of the burst zone.
Abstract translation: 一种飞机，包括具有前部和后部的机身，其具有安装在机身后部的推进系统。 定义了从推进系统向外延伸的爆破区域。 飞机包括从机身的后部延伸到设置在爆破区域外部的机身的前部的箱翼。
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公开(公告)号：US20170002659A1
公开(公告)日：2017-01-05
申请号：US14789295
申请日：2015-07-01
Applicant: United Technologies Corporation
Inventor： Alan H. Epstein , Gabriel L. Suciu , Jesse M. Chandler
CPC classification number: F01D5/141 , F01D5/14 , F01D5/225 , F01D5/303 , F01D11/02 , F02K3/025 , F02K3/065 , F04D29/164 , F04D29/321 , F04D29/668 , Y02T50/671 , Y02T50/673
Abstract: A gas turbine engine compressor stage includes a rotor. Compressor blades are supported by the rotor. The blades include an inner flow path surface each supporting an airfoil that has a chord that extends radially along a span to a tip. A shroud is supported at the tip and provides an outer flow path surface. The shroud provides a noncontiguous ring about the compressor stage.
Abstract translation: 燃气涡轮发动机压缩机级包括转子。 压缩机叶片由转子支撑。 叶片包括内部流动路径表面，每个支撑翼型件具有沿跨度径向延伸到尖端的翼弦。 护罩支撑在尖端处并且提供外部流动路径表面。 护罩提供围绕压缩机级的不连续的环。
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公开(公告)号：US20160312704A1
公开(公告)日：2016-10-27
申请号：US14695504
申请日：2015-04-24
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Joseph Brent Staubach , Brian D. Merry , Wesley K. Lord
IPC: F02C7/18
CPC classification number: F02C7/185 , F01D25/12 , F02C3/13 , F02C7/143 , F05D2210/44 , F05D2220/3212 , F05D2220/3218 , F05D2260/211 , F05D2260/213 , F05D2260/606 , Y02T50/676
Abstract: A gas turbine engine comprises a main compressor section having a downstream most end, 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, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses ng air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger has at least two passes, with one of the passes passing air radially outwardly, and a second of the passes returning the air radially inwardly to the compressor. 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最末端和更上游位置的主压缩机部分。 涡轮机部分具有高压涡轮机。 抽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，将抽头的空气通过热交换器，然后传递到冷却压缩机。 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中。 热交换器具有至少两个通道，其中一个通道径向向外通过空气，另一个通道使空气径向向内返回到压缩机。 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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139.发明申请THERMAL MANAGEMENT SYSTEM AND METHOD OF CIRCULATING AIR IN A GAS TURBINE ENGINE 有权气体涡轮发动机循环空气的热管理系统和方法公开(公告)号：US20160298544A1
公开(公告)日：2016-10-13
申请号：US14685392
申请日：2015-04-13
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
CPC classification number: F02C7/047 , B64C11/14 , F01D25/02 , F01D25/12 , F01D25/125 , F02C7/06 , F05D2260/213 , Y02T50/676
Abstract: A thermal management system and method of circulating air in a gas turbine engine are disclosed. The thermal management system includes a nose cone having an aperture communicating air to an interior space of the nose cone and a fan blade coupled to the nose cone and having a blade passage, wherein the nose cone rotates with the fan blade to circulate air from the aperture to the blade passage.
Abstract translation: 公开了一种在燃气涡轮发动机中循环空气的热管理系统和方法。 热管理系统包括鼻锥体，其具有将空气连通到鼻锥体的内部空间的孔口，以及联接到鼻锥体并具有叶片通道的风扇叶片，其中鼻锥体与风扇叶片一起旋转以使空气从 孔到刀片通道。
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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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