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71. 发明申请

US20160108854A1 LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE 审中-公开
标题翻译：低压风扇发动机在入口和风扇尺寸之间存在尺寸关系
公开(公告)号：US20160108854A1
公开(公告)日：2016-04-21
申请号：US14882760
申请日：2015-10-14
申请人： United Technologies Corporation
发明人： Wesley K. Lord , Robert E. Malecki , Yuan J. Qiu , Becky E. Rose , Jonathan Gilson
IPC分类号： F02K3/06 , F04D19/02 , F01D15/12 , F01D17/10 , F01D5/02 , F01D5/12
CPC分类号： F02K3/06 , F01D5/02 , F01D5/141 , F01D15/12 , F01D17/105 , F02C7/04 , F02C7/045 , F04D29/522 , F04D29/547 , F05D2220/32 , F05D2250/00 , Y02T50/671 , Y02T50/673
摘要： A gas turbine engine assembly according to an example of the present disclosure includes, among other things, a fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, a geared architecture configured to drive the fan, a turbine section configured to drive the geared architecture, a compressor section including a first compressor and a second compressor, and an inlet portion forward of the fan. A length of the inlet portion has a dimension L between a location of the leading edge of at least some of the fan blades and a forward edge on the inlet portion. A dimensional relationship of L/D is between about 0.2 and about 0.45.
摘要翻译：根据本公开的示例的燃气涡轮发动机组件包括除了别的以外的包括多个风扇叶片的风扇，具有基于风扇叶片的尺寸的尺寸D的风扇的直径，每个风扇具有前缘的叶片，配置成驱动风扇的齿轮架构，构造成驱动齿轮架构的涡轮部分，包括第一压缩机和第二压缩机的压缩机部分以及风扇前部的入口部分。入口部分的长度在至少一些风扇叶片的前缘的位置与入口部分的前边缘之间具有尺寸L。 L / D的尺寸关系为约0.2至约0.45。

72. 发明申请

US20160032731A1 THERMAL BARRIER COATING INSIDE COOLING CHANNELS 审中-公开
标题翻译：热障涂层在冷却通道内
公开(公告)号：US20160032731A1
公开(公告)日：2016-02-04
申请号：US14799994
申请日：2015-07-15
申请人： United Technologies Corporation
发明人： Gabriel L. Suciu , Brian D. Merry , James D. Hill , Wesley K. Lord
IPC分类号： F01D5/18
CPC分类号： F01D5/082 , F01D5/084 , F01D5/085 , F01D5/288 , Y02T50/672 , Y02T50/676
摘要： 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.
摘要翻译：根据本公开的示例性方面的用于燃气涡轮发动机的转子包括可绕轴线旋转的转子盘和连接到转子盘的径向外侧的气体通道壁。气体通道壁限定气体通道的径向向内部分。多个转子轮辐径向地位于转子盘和气体通道壁之间。多个转子轮辐在周向间隔开以限定转子盘和气体通道壁之间的多个冷却通道。热屏障涂层设置在多个冷却通道中的至少一个的表面上。还公开了一种冷却转子组件的方法。

73. 发明申请

US20150337762A1 TURBOFAN THRUST REVERSER SYSTEM 审中-公开
标题翻译： TURBOFAN THRUST REVERSER系统
公开(公告)号：US20150337762A1
公开(公告)日：2015-11-26
申请号：US14284893
申请日：2014-05-22
申请人： United Technologies Corporation
发明人： Allan R. Penda , Gabriel L. Suciu , William G. Sheridan , Wesley K. Lord
IPC分类号： F02K1/70 , F16H3/70 , F02C7/36
CPC分类号： F02K1/70 , F02C3/10 , F02C3/113 , F02C3/145 , F02C6/04 , F02C7/36 , F02K1/32 , F02K3/075 , F05D2260/40311 , F16H3/60 , Y02T50/671
摘要： A gas turbine engine comprises a core engine, a fan, a bypass duct and a clutch. The fan is driven by the core engine. The bypass duct is configured to receive airflow from the fan. The clutch links the core engine and the fan. The core comprises a reverse-flow, two-spool gas generator in one embodiment. In another embodiment, the fan is driven by a free turbine aerodynamically powered by the core engine. In one embodiment, the clutch includes reverse gearing to reverse rotational output of the fan. In one embodiment, the clutch and reverse gearing are implemented in an epicyclic gear system.
摘要翻译：燃气涡轮发动机包括核心发动机，风扇，旁通管道和离合器。风扇由核心发动机驱动。旁路管道被配置为从风扇接收气流。离合器连接核心发动机和风扇。核心包括在一个实施例中的逆流双阀气体发生器。在另一个实施例中，风扇由空气动力学地由核心发动机驱动的自由涡轮机驱动。在一个实施例中，离合器包括倒档以反转风扇的旋转输出。在一个实施例中，离合器和倒档传动装置实现在行星齿轮系统中。

74. 发明申请

US20150337738A1 Two Spool Gas Generator with Improved Air Porting 审中-公开
标题翻译：具有改进空气流通的两个轴流气发生器
公开(公告)号：US20150337738A1
公开(公告)日：2015-11-26
申请号：US14758277
申请日：2013-05-10
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Gabriel L. Suciu , Jesse M. Chandler , Wesley K. Lord
IPC分类号： F02C9/18 , F02K3/02 , F02C7/12
CPC分类号： F02C7/12 , F02C3/13 , F02C3/145 , F02C6/04 , F02C6/08 , F02C9/18 , F02K3/00 , F02K3/02 , F05D2220/3217 , F05D2220/3218
摘要： In a featured embodiment, a gas turbine engine has a first compressor rotor driven by a first turbine rotor, and a second compressor rotor driven by a second turbine rotor. The second compressor rotor is upstream of the first compressor rotor and the first turbine rotor is upstream of the second turbine rotor. An air mixing system taps air from a location upstream of the first compressor rotor for delivery to an environmental control system. The air mixing system receives air from a first air source and a second air source. The first air source includes air at a first pressure upstream of the first compressor rotor. The second air source includes air at a lower second pressure. At least one valve controls a mixture of air from the first and second sources to achieve a predetermined pressure for the environmental control system.
摘要翻译：在特征实施例中，燃气涡轮发动机具有由第一涡轮转子驱动的第一压缩机转子和由第二涡轮转子驱动的第二压缩机转子。第二压缩机转子在第一压缩机转子的上游，第一涡轮转子位于第二涡轮转子的上游。空气混合系统从第一压缩机转子的上游位置抽出空气，用于输送到环境控制系统。空气混合系统从第一空气源和第二空气源接收空气。第一空气源包括在第一压缩机转子的上游的第一压力下的空气。第二空气源包括较低的第二压力的空气。至少一个阀控制来自第一和第二源的空气的混合物以实现环境控制系统的预定压力。

75. 发明申请

US20140321970A1 PASSIVE BOUNDARY LAYER BLEED SYSTEM FOR NACELLE INLET AIRFLOW CONTROL 审中-公开
标题翻译：用于空气入口空气流量控制的被动边界层系统
公开(公告)号：US20140321970A1
公开(公告)日：2014-10-30
申请号：US14325583
申请日：2014-07-08
申请人： United Technologies Corporation
发明人： Steven H. Zysman , Wesley K. Lord , Robert M. Miller , Oliver V. Atassi
IPC分类号： F02C9/18
CPC分类号： F02C7/04 , B64D33/02 , B64D2033/0226 , F02C7/045 , F05D2250/324 , F05D2250/71 , F05D2270/17 , Y10T137/0536
摘要： A nacelle for a gas turbine engine system includes a housing that has a pressure side and a suction side. A passage extends between the pressure side and the suction side for permitting airflow from the pressure side to the suction side. The passage includes a first curved section that has an inlet at the pressure side. A linear section is connected with the first curved section. A second curved section is connected with the linear section and has an outlet at the suction side. The outlet has a cross sectional area smaller than a cross sectional area of the linear section.
摘要翻译：用于燃气涡轮发动机系统的机舱包括具有压力侧和吸力侧的壳体。通道在压力侧和吸力侧之间延伸，以允许从压力侧到吸力侧的气流。通道包括在压力侧具有入口的第一弯曲部分。线性部分与第一弯曲部分连接。第二弯曲部分与线性部分连接并且在吸力侧具有出口。出口的横截面积小于线性部分的横截面面积。

76. 发明授权

US11286811B2 Low pressure ratio fan engine having a dimensional relationship between inlet and fan size 有权
公开(公告)号：US11286811B2
公开(公告)日：2022-03-29
申请号：US16391476
申请日：2019-04-23
申请人： United Technologies Corporation
发明人： Wesley K. Lord , Robert E. Malecki , Yuan J. Qiu , Becky E. Rose , Jonathan Gilson
IPC分类号： F01D25/24 , F02K3/06 , F01D5/14 , F02C7/04 , F01D5/02 , F01D15/12 , F01D17/10
摘要： According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a geared architecture, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan through the geared architecture, a nacelle surrounding the fan, the nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L measured along an engine axis between the first reference plane and the second reference plane. A dimensional relationship of L/D is between 0.20 and 0.40.

77. 发明授权

US10711631B2 Turbine engine with guide vanes forward of its fan blades 有权
公开(公告)号：US10711631B2
公开(公告)日：2020-07-14
申请号：US14976876
申请日：2015-12-21
申请人： United Technologies Corporation
发明人： Gabriel L. Suciu , Wesley K. Lord , Jayant Sabnis , Jesse M. Chandler
IPC分类号： F01D1/02 , F01D17/10 , F01D7/00 , F01D5/02 , F01D9/04 , F01D25/24 , F02C3/107 , F02C3/14
摘要： A turbine engine such as a pusher fan engine is provided. This turbine engine includes a nacelle with a bypass flowpath. A fan rotor is configured to propel air out of the bypass flowpath. A plurality of guide vanes are configured to direct the air to the fan rotor.

78. 发明申请

US20200063603A1 LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE 审中-公开
公开(公告)号：US20200063603A1
公开(公告)日：2020-02-27
申请号：US16658674
申请日：2019-10-21
申请人： United Technologies Corporation
发明人： Wesley K. Lord , Robert E. Malecki , Yuan J. Qiu , Becky E. Rose , Jonathan Gilson
IPC分类号： F01D25/24 , F01D5/14 , F02K3/06 , F01D5/02 , F01D15/12 , F02C7/04 , F01D17/10
摘要： A gas turbine engine assembly includes a fan. A diameter of the fan has a dimension D. The fan has a pressure ratio of greater than 1.20 and less than 1.45. A leading edge on an inlet portion of a nacelle is within a first reference plane oriented at an oblique angle. A forward most portion on the fan blade leading edges is in a second reference plane. A length of the inlet portion has a dimension L different at a plurality of locations on the inlet portion. A geared architecture has a gear reduction ratio of greater than 2.3, a bypass ratio is greater than 10, and a low pressure turbine includes a pressure ratio greater than 5:1. A dimensional relationship of UD is between 0.25 and 0.45. The leading edge on the inlet portion is further from the second reference plane near the top of the assembly.

79. 发明授权

US10526914B2 Gas turbine engine with low fan noise 有权
公开(公告)号：US10526914B2
公开(公告)日：2020-01-07
申请号：US14761689
申请日：2014-03-11
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Bruce L. Morin , Wesley K. Lord
IPC分类号： F01D25/04 , F01D5/02 , F01D5/14 , F01D9/02 , F02K1/15 , F02K1/16 , F01D17/14
摘要： In accordance with one aspect of the disclosure, a gas turbine engine, method of using and designing such is disclosed. The gas turbine engine may comprise a fan including a plurality of blades, and a variable area fan nozzle. The fan may be configured to have a design point fan tip leading edge relative flow angle βADP, and may be further configured to have an off-design point fan tip leading edge relative flow angle β at an off-design fan operating point. The variable area fan nozzle may be configured to manipulate the amount of air flowing through the fan so that the absolute value of a difference between the design point fan tip leading edge relative flow angle βADP and the off-design point fan tip leading edge relative flow angle β is in a specified range.

80. 发明授权

US10421554B2 Double propulsor imbedded in aircraft tail with single core engine 有权
公开(公告)号：US10421554B2
公开(公告)日：2019-09-24
申请号：US14874560
申请日：2015-10-05
申请人： United Technologies Corporation
发明人： Gabriel L. Suciu , Jesse M. Chandler , Wesley K. Lord , Alan H. Epstein , Steven M. O'Flarity
IPC分类号： B64D35/06 , B64D27/20 , B64D27/14
摘要： A drive arrangement for an aircraft comprises a pair of propulsor units each having a fan and a fan shaft for driving the fan. A core engine has a turbine driving a core engine shaft. A mechanical connection connects the core engine shaft to drive the fan shafts for each of the propulsor units. An aircraft also has such an arrangement.

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