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公开(公告)号：US09869183B2
公开(公告)日：2018-01-16
申请号：US14799994
申请日：2015-07-15
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill , Wesley K. Lord
CPC classification number: F01D5/082 , F01D5/084 , F01D5/085 , F01D5/288 , Y02T50/672 , Y02T50/676
Abstract: A rotor for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a rotor disk rotatable about an axis and a gas path wall coupled to and radially outward of the rotor disk. The gas path wall bounds a radially inward portion of a gas path. A plurality of rotor spokes are radially intermediate the rotor disk and the gas path wall. The plurality of rotor spokes is circumferentially spaced to define a plurality of cooling channels intermediate the rotor disk and the gas path wall. A thermal barrier coating is disposed on a surface of at least one of the plurality of cooling channels. A method of cooling a rotor assembly is also disclosed.
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公开(公告)号：US09850819B2
公开(公告)日：2017-12-26
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
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.
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公开(公告)号：US20170298954A1
公开(公告)日：2017-10-19
申请号：US15378371
申请日：2016-12-14
Applicant: United Technologies Corporation
Inventor： Yuan J. Qiu , Robert E. Malecki , Wesley K. Lord
Abstract: A fan assembly for a gas turbine engine includes a fan including a plurality of fan blades. Each fan blade extends radially outwardly from a fan hub to a blade tip. The plurality of blade tips define a fan diameter. A nacelle surrounds the fan and defines a fan inlet upstream of the fan, relative to an airflow direction into the fan. The nacelle has a forwardmost edge defining an inlet length from the forwardmost edge to a leading edge of a fan blade of the plurality of fan blades. A ratio of inlet length to fan diameter is between 0.20 and 0.45. A nacelle inner surface defines a nacelle flowpath. The nacelle flowpath has a convex throat portion and a concave diffusion portion between the throat portion and the leading edge of the fan blade at a bottommost portion of the nacelle.
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公开(公告)号：US20170267342A1
公开(公告)日：2017-09-21
申请号：US15072657
申请日：2016-03-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Wesley K. Lord
CPC classification number: B64C39/005 , B64C11/006 , B64C21/025 , B64C23/02 , B64C2230/04 , F04D17/04 , Y02T50/166
Abstract: A cross flow fan to be incorporated into an aircraft comprises a cross flow fan rotor to be positioned in an aircraft, a drive arrangement for the cross flow fan rotor, and a plurality of vanes positioned downstream of the cross flow fan rotor. An aircraft is also disclosed.
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公开(公告)号：US09752510B2
公开(公告)日：2017-09-05
申请号：US15000077
申请日：2016-01-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Alan H. Epstein , Wesley K. Lord , Michael E. McCune , Brian D. Merry
CPC classification number: F02C7/36 , F01D15/12 , F02C3/06 , F02C3/107 , F05D2220/32 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2240/40 , F05D2240/60 , F05D2260/4031 , F05D2260/40311
Abstract: A gas turbine engine includes a core engine with a compressor section, a combustor and a turbine. The turbine drives an output shaft, and the output shaft drives at least four gears. Each of the at least four gears extends through a drive shaft to drive an associated fan rotor.
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Patent Agency Ranking
公开(公告)号：US09611034B1
公开(公告)日：2017-04-04
申请号：US14930712
申请日：2015-11-03
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Wesley K. Lord
CPC classification number: B64C21/08 , B64C2230/06 , B64D27/20 , B64D33/02 , B64D2033/0226 , B64D2033/0253 , Y02T50/166
Abstract: An arrangement for reducing drag on the body of an aircraft with a relatively wide fuselage comprises a gas turbine engine. At least one duct is selectively moveable between a closed position and an open position, such that the at least one duct allows airflow to move toward a fan rotor in the gas turbine engine in the open position, but blocks airflow when in the closed position. An aircraft body is also disclosed.
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公开(公告)号：US20170044992A1
公开(公告)日：2017-02-16
申请号：US15292472
申请日：2016-10-13
Applicant: United Technologies Corporation
Inventor： Paul R. Adams , Shankar S. Magge , Joseph Brent Staubach , Wesley K. Lord , Frederick M. Schwarz , Gabriel L. Suciu
CPC classification number: F02C7/36 , F01D5/06 , F01D11/122 , F01D25/24 , F02C3/04 , F02C3/107 , F02C7/20 , F02C9/18 , F02K3/06 , F02K3/075 , F04D19/02 , F05B2250/283 , F05D2220/32 , F05D2220/323 , F05D2240/35 , F05D2240/60 , F05D2260/40311
Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.
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公开(公告)号：US20160090909A1
公开(公告)日：2016-03-31
申请号：US14964727
申请日：2015-12-10
Applicant: United Technologies Corporation
Inventor： Jonthan Gilson , Burce L. Morin , Ramons A. Reba , David A. Topol , Wesley K. Lord
CPC classification number: F02C3/107 , F01D9/041 , F01D25/162 , F02K3/06 , F04D29/542 , F04D29/544 , F04D29/664 , F04D29/667 , F05D2220/36 , F05D2250/191 , F05D2250/38 , F05D2260/40311 , F05D2260/96 , F05D2260/961 , F05D2300/603
Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.
Abstract translation: 根据本公开的示例的用于燃气涡轮发动机的风扇部分包括具有风扇叶片的风扇转子和位于风扇转子下游的多个风扇出口导向叶片。 风扇转子被构造成通过齿轮减速被驱动。 定义了多个风扇出口导向叶片与多个风扇叶片的比例。 风扇出口导向叶片具有优化的扫掠和优化的倾斜。
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公开(公告)号：US20160003145A1
公开(公告)日：2016-01-07
申请号：US14767396
申请日：2014-02-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Yuan J. Qiu , Robert M. Miller , Wesley K. Lord , Gavin Hendricks
Abstract: A gas turbine engine that includes a fan nacelle and a core nacelle that provide a bypass flow path radially between. The fan nacelle has an inlet including a throat. The inlet has an inlet forward-most point. A fan is arranged in the bypass flow path and rotatable about an axis. The fan has a leading edge recessed from the inlet forward-most point an inlet length in an axial direction. A spinner has a spinner length from a spinner forward-most point to the leading edge. A ratio of the spinner length to inlet length is equal to or greater than about 0.5.
Abstract translation: 一种燃气涡轮发动机，其包括在其之间径向提供旁通流动路径的风扇机舱和核心机舱。 风扇机舱具有包括喉部的入口。 入口具有入口最前面的点。 风扇布置在旁路流动路径中并可围绕轴线旋转。 风扇具有从入口最前端凹入的前缘，其轴向方向上的入口长度。 旋转器的旋转器长度从最远点到最前沿。 旋转器长度与入口长度的比例等于或大于约0.5。
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公开(公告)号：US20150330254A1
公开(公告)日：2015-11-19
申请号：US14611887
申请日：2015-02-02
Applicant: United Technologies Corporation
Inventor： Richard Alan Weiner , Wesley K. Lord
CPC classification number: B64D29/02 , B64D33/04 , F01D25/24 , F02C3/06 , F02K3/068 , F05D2250/70 , F05D2250/73 , Y02T50/671
Abstract: A gas turbine engine including a fan, compressor, combustor and a turbine arranged in series and surrounded by a nacelle. An engine core cowl is disposed within the nacelle. Each of these elements shares a central longitudinal axis. The nacelle length may be non-uniform around the circumference of the nacelle.
Abstract translation: 一种燃气涡轮发动机，其包括串联布置并被机舱包围的风扇，压缩机，燃烧器和涡轮机。 发动机核心罩被布置在机舱内。 这些元件中的每一个共享中心纵向轴线。 机舱长度在机舱周围可能不均匀。
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