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公开(公告)号：US10302042B2
公开(公告)日：2019-05-28
申请号：US15177657
申请日：2016-06-09
Applicant: United Technologies Corporation
Inventor： Oliver V. Atassi , Oleg Petrenko
Abstract: A gas turbine engine includes a core engine that has at least a compressor section, a combustor section and a turbine section disposed along a central axis. A fan is coupled to be driven by the turbine section. A fan nozzle is aft of the fan and defines an exit area. The fan nozzle has a body that defines an airfoil cross-section geometry. The body includes a wall that has a controlled mechanical property distribution that varies by location on the wall in accordance with a desired flutter characteristic at the location.
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2.发明申请公开(公告)号：US20140321970A1
公开(公告)日：2014-10-30
申请号：US14325583
申请日：2014-07-08
Applicant: United Technologies Corporation
Inventor： Steven H. Zysman , Wesley K. Lord , Robert M. Miller , Oliver V. Atassi
IPC: F02C9/18
CPC classification number: F02C7/04 , B64D33/02 , B64D2033/0226 , F02C7/045 , F05D2250/324 , F05D2250/71 , F05D2270/17 , Y10T137/0536
Abstract: 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.
Abstract translation: 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。
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公开(公告)号：US11181074B2
公开(公告)日：2021-11-23
申请号：US16422181
申请日：2019-05-24
Applicant: United Technologies Corporation
Inventor： Oliver V. Atassi , Oleg Petrenko
Abstract: A gas turbine engine includes a core engine that has at least a compressor section, a combustor section and a turbine section disposed along a central axis. A fan is coupled to be driven by the turbine section. A fan nozzle is aft of the fan and defines an exit area. The fan nozzle has a body with an airfoil cross-section geometry. The body includes a wall that has a controlled mechanical property distribution that varies in material macro- or micro-structure by location on the wall in accordance with a desired flutter characteristic at the location.
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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：US09745918B2
公开(公告)日：2017-08-29
申请号：US14609800
申请日：2015-01-30
Applicant: United Technologies Corporation
Inventor： Jonathan Gilson , Dennis Cicon , Oliver V. Atassi
CPC classification number: F02K1/09 , F02K1/002 , F02K1/827 , F05D2260/96
Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a core nacelle defined about an engine centerline axis. A fan nacelle is mounted at least partially around the core nacelle to define a fan bypass flow path. A variable area fan nozzle is 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. The second fan nacelle section is axially movable relative to the first fan nacelle section to define an auxiliary port at a non-closed position to vary a fan nozzle exit area and adjust fan bypass airflow. The second fan nacelle section includes an acoustic system that has an acoustic impedance located on a radially outer surface.
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Patent Agency Ranking
公开(公告)号：US20170058827A1
公开(公告)日：2017-03-02
申请号：US15177657
申请日：2016-06-09
Applicant: United Technologies Corporation
Inventor： Oliver V. Atassi , Oleg Petrenko
CPC classification number: F02K1/15 , F02C3/04 , F02C7/36 , F02K1/06 , F02K1/82 , F02K3/06 , F05D2220/323 , F05D2240/35 , F05D2260/81 , F05D2300/173 , F05D2300/6033 , Y02T50/672
Abstract: A gas turbine engine includes a core engine that has at least a compressor section, a combustor section and a turbine section disposed along a central axis. A fan is coupled to be driven by the turbine section. A fan nozzle is aft of the fan and defines an exit area. The fan nozzle has a body that defines an airfoil cross-section geometry. The body includes a wall that has a controlled mechanical property distribution that varies by location on the wall in accordance with a desired flutter characteristic at the location.
Abstract translation: 燃气涡轮发动机包括至少具有压缩机部分，燃烧器部分和沿中心轴线布置的涡轮部分的核心发动机。 风扇被联接以由涡轮部分驱动。 风扇喷嘴位于风扇后部并限定出口区域。 风扇喷嘴具有限定翼型横截面几何形状的主体。 主体包括具有受控的机械属性分布的壁，其根据位置处的期望的颤动特性随墙壁上的位置而变化。
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公开(公告)号：US09644535B2
公开(公告)日：2017-05-09
申请号：US14325583
申请日：2014-07-08
Applicant: United Technologies Corporation
Inventor： Steven H. Zysman , Wesley K. Lord , Robert M. Miller , Oliver V. Atassi
CPC classification number: F02C7/04 , B64D33/02 , B64D2033/0226 , F02C7/045 , F05D2250/324 , F05D2250/71 , F05D2270/17 , Y10T137/0536
Abstract: 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.
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公开(公告)号：US20160327064A1
公开(公告)日：2016-11-10
申请号：US14706259
申请日：2015-05-07
Applicant: United Technologies Corporation
Inventor： Michaela M. Logue , Oliver V. Atassi
CPC classification number: F04D29/668 , F01D25/04 , F01D25/162 , F02C7/045 , F02K1/08 , F02K1/827 , F02K3/06 , F04D29/526 , F04D29/541 , F05D2220/36 , F05D2240/12 , F05D2250/283 , F05D2260/96 , F05D2260/963
Abstract: A gas turbine engine is provided having a fan case and a translating sleeve positioned downstream from the fan case. A flow channel extends between the fan case and the translating sleeve. The flow channel includes an inner diameter and an outer diameter. A structural guide vane is positioned within the flow channel and extends from the inner diameter to the outer diameter. A liner is positioned between an aft end of the fan case and an aft end of the translating sleeve to reduce vibratory stress on the structural guide vane.
Abstract translation: 提供一种燃气涡轮发动机，其具有风扇壳体和位于风扇壳体下游的平移套筒。 流动通道在风扇壳体和平移套筒之间延伸。 流动通道包括内径和外径。 结构导叶定位在流动通道内并从内径延伸到外径。 衬套位于风扇壳体的后端和平移套筒的后端之间，以减小结构导叶上的振动应力。
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公开(公告)号：US09394852B2
公开(公告)日：2016-07-19
申请号：US13834123
申请日：2013-03-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Oliver V. Atassi , Oleg Petrenko
CPC classification number: F02K1/15 , F02C3/04 , F02C7/36 , F02K1/06 , F02K1/82 , F02K3/06 , F05D2220/323 , F05D2240/35 , F05D2260/81 , F05D2300/173 , F05D2300/6033 , Y02T50/672
Abstract: A gas turbine engine includes a core engine that has at least a compressor section, a combustor section and a turbine section disposed along a central axis. A fan is coupled to be driven by the turbine section. A fan nacelle is arranged around the fan, and a bypass passage extends between the fan nacelle and the core engine. A variable area fan nozzle (VAFN) extends at least partially around the central axis and defines an exit area of the bypass passage. The VAFN is selectively movable to vary the exit area. The VAFN includes a body that defines an airfoil cross-section shape. The VAFN includes a wall that has a mechanical property distribution in accordance with a computer-simulated vibration profile of a flutter characteristic of the VAFN.
Abstract translation: 燃气涡轮发动机包括至少具有压缩机部分，燃烧器部分和沿中心轴线布置的涡轮部分的核心发动机。 风扇被联接以由涡轮部分驱动。 风扇周围布置有风扇机舱，并且旁通通道在风扇机舱和核心发动机之间延伸。 可变区域风扇喷嘴（VAFN）至少部分地围绕中心轴延伸并且限定旁路通道的出口区域。 VAFN选择性地可移动以改变出口区域。 VAFN包括限定翼型横截面形状的主体。 VAFN包括具有根据VAFN的颤振特性的计算机模拟振动分布的机械特性分布的壁。
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公开(公告)号：US20200032739A1
公开(公告)日：2020-01-30
申请号：US16422181
申请日：2019-05-24
Applicant: United Technologies Corporation
Inventor： Oliver V. Atassi , Oleg Petrenko
Abstract: A gas turbine engine includes a core engine that has at least a compressor section, a combustor section and a turbine section disposed along a central axis. A fan is coupled to be driven by the turbine section. A fan nozzle is aft of the fan and defines an exit area. The fan nozzle has a body with an airfoil cross-section geometry. The body includes a wall that has a controlled mechanical property distribution that varies in material macro- or micro-structure by location on the wall in accordance with a desired flutter characteristic at the location.
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