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公开(公告)号：US20160032832A1
公开(公告)日：2016-02-04
申请号：US14766825
申请日：2014-02-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jonathan Gilson , Nigel David Sawyers-Abbott
CPC classification number: F02C7/045 , F01D5/02 , F01D25/24 , F05D2220/32 , F05D2220/36 , F05D2260/963
Abstract: A fan section for a gas turbine engine includes a fan hub and a nose cone section operatively mounted to the fan hub. The nose cone section includes a noise attenuation feature.
Abstract translation: 用于燃气涡轮发动机的风扇部分包括可操作地安装到风扇轮毂的风扇轮毂和鼻锥部分。 鼻锥部分包括噪声衰减特征。
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12.发明申请Geared Turbofan Engine Having a Reduced Number of Fan Blades and Improved Acoustics 审中-公开具有减少风扇叶片数量和改进声学的齿轮涡轮风扇发动机公开(公告)号：US20160003049A1
公开(公告)日：2016-01-07
申请号：US14769408
申请日：2014-02-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Constantine Baltas , Jonathan Gilson
IPC: F01D5/14
CPC classification number: F01D5/141 , F05D2220/36 , Y02T50/671 , Y02T50/673
Abstract: A rotor blade comprises an airfoil extending radially from a root section to a tip section and axially from a leading edge to a trailing edge, the leading and trailing edges defining a curvature therebetween. The curvature determines a relative exit angle at a relative span height between the root section and the tip section, based on an incident flow velocity at the leading edge of the airfoil and a rotational velocity at the relative span height. In operation of the rotor blade, the relative exit angle determines a substantially flat exit pressure ratio profile for relative span heights from 75% to 95%, wherein the exit pressure ratio profile is constant within a tolerance of 10% of a maximum value of the exit pressure ratio profile.
Abstract translation: 转子叶片包括从根部到尖端部分径向延伸并且从前缘到后缘的轴向延伸的翼型件，前缘和后缘在它们之间限定曲率。 基于在翼型的前缘处的入射流速和在相对跨度高度处的旋转速度，曲率确定根部和尖端部分之间相对跨度高度处的相对出射角。 在转子叶片的操作中，相对出口角度确定了从75％到95％的相对跨度高度的基本上平坦的出口压力比分布，其中出口压力比分布是恒定的，在公差范围内的最大值的10％ 出口压力比。
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公开(公告)号：US11492967B2
公开(公告)日：2022-11-08
申请号：US16503097
申请日：2019-07-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： David L. Lincoln , Wayde R. Schmidt , Michael J. Birnkrant , Michael T. Gorski , Jonathan Gilson , Xuemei Wang , Coy Bruce Wood
Abstract: A multi-angle multi-wave array may comprise a first set of sensing elements, a second set of sensing elements, and a third set of sensing elements wherein the first set of sensing elements, the second set of sensing elements, and the third set of sensing elements are collectively configured to detect and discriminate between categories of foreign object debris including solid objects and particulates including silicate sand, water vapor, dust, volcanic ash, and smoke.
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14.发明授权公开(公告)号：US11286811B2
公开(公告)日：2022-03-29
申请号：US16391476
申请日：2019-04-23
Applicant: United Technologies Corporation
Inventor： Wesley K. Lord , Robert E. Malecki , Yuan J. Qiu , Becky E. Rose , Jonathan Gilson
Abstract: 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.
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15.发明申请公开(公告)号：US20200063603A1
公开(公告)日：2020-02-27
申请号：US16658674
申请日：2019-10-21
Applicant: United Technologies Corporation
Inventor： Wesley K. Lord , Robert E. Malecki , Yuan J. Qiu , Becky E. Rose , Jonathan Gilson
Abstract: 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.
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Patent Agency Ranking
16.发明授权公开(公告)号：US09932933B2
公开(公告)日：2018-04-03
申请号：US14091862
申请日：2013-11-27
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Wesley K. Lord , Robert E. Malecki , Yuan J. Qiu , Becky E. Rose , Jonathan Gilson
CPC classification number: F02K3/068 , F01D25/24 , F02C7/04 , F05D2220/36 , F05D2240/303 , F05D2260/40311 , F05D2260/96 , Y02T50/671
Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan that has a plurality of fan blades. A diameter of the fan has a dimension D that is based on a dimension of the fan blades. Each fan blade has a leading edge. An inlet portion is situated 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.
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公开(公告)号：US20210003075A1
公开(公告)日：2021-01-07
申请号：US16503097
申请日：2019-07-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： David L Lincoln , Wayde R. Schmidt , Michael J. Birnkrant , Michael T. Gorski , Jonathan Gilson , Xuemei Wang , Coy Bruce Wood
Abstract: A multi-angle multi-wave array may comprise a first set of sensing elements, a second set of sensing elements, and a third set of sensing elements wherein the first set of sensing elements, the second set of sensing elements, and the third set of sensing elements are collectively configured to detect and discriminate between categories of foreign object debris including solid objects and particulates including silicate sand, water vapor, dust, volcanic ash, and smoke.
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公开(公告)号：US10826547B1
公开(公告)日：2020-11-03
申请号：US16692125
申请日：2019-11-22
Applicant: United Technologies Corporation
Inventor： Jonathan Gilson , Joseph V. Mantese , Goran Djuknic , Gurkan Gok , Brenda J. Lisitano , Coy Bruce Wood , Sanjay Bajekal
Abstract: A system of a machine includes a network of a plurality of nodes distributed throughout the machine. Each of the nodes is operable to communicate through a plurality of electromagnetic signals. A controller is operable to communicate with the network of nodes through the electromagnetic signals. A plurality of waveguides is configured to confine transmission of the electromagnetic signals between the controller and one or more of the nodes. A radio frequency antenna is coupled to a first end of a first waveguide of the plurality of waveguides. A radio frequency transceiver is coupled between the controller and the radio frequency antenna. A capacitively coupled membrane at a second end of the first waveguide is configured to establish communication between the first waveguide and at least one node of the plurality of nodes.
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公开(公告)号：US10808648B2
公开(公告)日：2020-10-20
申请号：US14472849
申请日：2014-08-29
Applicant: United Technologies Corporation
Inventor： Jonathan Gilson , Andre M. Hall , Oliver V. Atassi , Ramons A. Reba
Abstract: A nacelle assembly according to an exemplary aspect of the present disclosure includes, among other things, a core nacelle defined at least partially about a core engine, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path, and a variable area fan nozzle in communication with the fan bypass flow path. The variable area fan nozzle has a first fan nacelle section and a second fan nacelle section downstream of the first fan nacelle section. The first fan nacelle section and the second fan nacelle section are axially movable relative to one another to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow. The auxiliary port is defined between the first fan nacelle section and the second fan nacelle section. The first fan nacelle section comprises a first acoustic system which provides an acoustic impedance configured to attenuate a noise characterized by a leading edge of the second fan nacelle section. The first acoustic system is defined at least in part within a trailing edge region of the first fan nacelle section. A method of reducing a total effective perceived noise level of a gas turbine engine with a variable area fan nozzle is also disclosed.
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公开(公告)号：US20190024581A1
公开(公告)日：2019-01-24
申请号：US16143662
申请日：2018-09-27
Applicant: United Technologies Corporation
Inventor： Jonathan Gilson , Bruce L. Morin , Ramons A. Reba , David A. Topol , Wesley K. Lord
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.
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