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公开(公告)号：US11346282B2
公开(公告)日：2022-05-31
申请号：US16251492
申请日：2019-01-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ramons A. Reba , Bruce L. Morin , Daniel L. Gysling , Carson A. Roy Thill , Jose R. Paulino , JinQuan Xu , Stephen A. Morford
Abstract: A section for a gas turbine engine includes a rotating structure, a stationary structure, and a flow guide assembly arranged generally between the rotating structure and the stationary structure. A flow path is defined between the flow guide assembly and one of the rotating structure and the stationary structure. The flow guide assembly includes a plurality of apertures configured to disrupt acoustic waves of air in the flow path. A seal is configured to establish a sealing relationship between the rotating structure and the stationary structure, and wherein an inlet to the flow path is adjacent the seal. A gas turbine engine and a method of disrupting acoustic waves in a flow path of a gas turbine engine are also disclosed.
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公开(公告)号：US10655538B2
公开(公告)日：2020-05-19
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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公开(公告)号：US20140366554A1
公开(公告)日：2014-12-18
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
CPC classification number: F02K1/09 , F02K1/827 , F02K3/06 , F02K3/075 , Y02T50/672
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.
Abstract translation: 根据本公开的示例性方面的机舱组件尤其包括至少部分地围绕核心发动机限定的核心机舱，至少部分地围绕所述核心机舱安装的风扇机舱，以限定风扇旁路流动路径，以及 与风扇旁路流路连通的可变区域风扇喷嘴。 可变区域风扇喷嘴具有第一风扇机舱部分和第一风扇机舱部分下游的第二风扇机舱部分。 第一风扇机舱部分和第二风扇机舱部分可相对于彼此轴向移动以限定辅助端口以改变风扇喷嘴出口区域并调节风扇旁路气流。 辅助端口定义在第一风扇机舱部分和第二风扇机舱部分之间。 第一风扇机舱部分包括第一声学系统，其提供被配置为衰减由第二风扇机舱部分的前缘表征的噪声的声阻抗。 第一声学系统至少部分地限定在第一风扇机舱部分的后缘区域内。 还公开了一种用可变面积风扇喷嘴降低燃气涡轮发动机的总有效感知噪声水平的方法。
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Patent Agency Ranking
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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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：US20200232390A1
公开(公告)日：2020-07-23
申请号：US16251492
申请日：2019-01-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ramons A. Reba , Bruce L. Morin , Daniel L. Gysling , Carson A. Roy Thill , Jose R. Paulino , JinQuan Xu , Stephen A. Morford
Abstract: A section for a gas turbine engine includes a rotating structure, a stationary structure, and a flow guide assembly arranged generally between the rotating structure and the stationary structure. A flow path is defined between the flow guide assembly and one of the rotating structure and the stationary structure. The flow guide assembly includes a plurality of apertures configured to disrupt acoustic waves of air in the flow path. A seal is configured to establish a sealing relationship between the rotating structure and the stationary structure, and wherein an inlet to the flow path is adjacent the seal. A gas turbine engine and a method of disrupting acoustic waves in a flow path of a gas turbine engine are also disclosed.
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公开(公告)号：US10107191B2
公开(公告)日：2018-10-23
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
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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