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    Geared turbofan engine having a reduced number of fan blades and improved acoustics
    21.
    发明授权
    Geared turbofan engine having a reduced number of fan blades and improved acoustics 有权

    公开(公告)号：US10184340B2

    公开(公告)日：2019-01-22

    申请号：US14769408

    申请日：2014-02-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Constantine Baltas ,  Jonathan Gilson

    IPC: F01D5/14

    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.

    Gas turbine engine with noise attenuating variable area fan nozzle
    23.
    发明授权
    Gas turbine engine with noise attenuating variable area fan nozzle 有权

    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

    IPC: F02K1/09 ,  F02K1/00 ,  F02K1/82

    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.

    Radio frequency-based repeater in a waveguide system
    24.
    发明授权
    Radio frequency-based repeater in a waveguide system 有权

    公开(公告)号：US10998958B1

    公开(公告)日：2021-05-04

    申请号：US16692119

    申请日：2019-11-22

    Applicant: United Technologies Corporation

    Inventor： Jonathan Gilson ,  Joseph V. Mantese ,  Goran Djuknic ,  Gurkan Gok ,  Brenda J. Lisitano ,  Sanjay Bajekal ,  Coy Bruce Wood

    IPC: H04B7/155 ,  F02C9/00

    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. The system also includes a plurality of waveguides configured to guide transmission of the electromagnetic signals between the controller and one or more of the nodes. A radio frequency-based repeater is coupled to at least two of the waveguides in the network between the controller and at least one of the nodes. The radio frequency-based repeater is configured to receive a portion of the electromagnetic signals in a first waveguide and boost a transmission characteristic of the portion of the electromagnetic signals in a second waveguide.

    GAS TURBINE ENGINE WITH NOISE ATTENUATING VARIABLE AREA FAN NOZZLE
    28.
    发明申请
    GAS TURBINE ENGINE WITH NOISE ATTENUATING VARIABLE AREA FAN NOZZLE 有权
    燃气涡轮发动机与噪声衰减变化范围风扇喷嘴

    公开(公告)号：US20150135678A1

    公开(公告)日：2015-05-21

    申请号：US14609800

    申请日：2015-01-30

    Applicant: United Technologies Corporation

    Inventor： Jonathan Gilson ,  Dennis Cicon ,  Oliver V. Atassi

    IPC: F02K1/09 ,  F02K1/00 ,  F02K1/82

    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.

    Abstract translation: 用于高旁路燃气涡轮发动机的机舱组件包括围绕发动机中心线轴线限定的核心机舱。 风扇机舱至少部分地安装在核心机舱周围以限定风扇旁路流动路径。 可变区域风扇喷嘴与风扇旁路流路连通。 可变区域风扇喷嘴具有第一风扇机舱部分和第二风扇机舱部分。 第二风扇机舱部分可相对于第一风扇机舱部分轴向移动，以在非闭合位置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。 第二风扇机舱部分包括具有位于径向外表面上的声阻抗的声学系统。

    CROSS REFERENCE TO RELATED APPLICATIONS
    29.
    发明申请
    CROSS REFERENCE TO RELATED APPLICATIONS 审中-公开
    相关申请的交叉引用

    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

    IPC: F02K1/09 ,  F02K3/075

    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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