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    METHODS FOR REDUCING ACOUSTIC NOISE ON TOTAL AIR TEMPERATURE SENSORS USING ADDITIVE MANUFACTURING
    2.
    发明公开
    METHODS FOR REDUCING ACOUSTIC NOISE ON TOTAL AIR TEMPERATURE SENSORS USING ADDITIVE MANUFACTURING 审中-公开

    公开(公告)号：EP4279887A1

    公开(公告)日：2023-11-22

    申请号：EP23173475.7

    申请日：2023-05-15

    Applicant: ROSEMOUNT AEROSPACE INC.

    Inventor： SABLE, Robert E. ,  PITERA, Rudy

    IPC: G01K1/08 ,  G01K13/02

    Abstract: In one embodiment, a cover (12) for an aircraft sensor includes a leading edge (28), the leading edge extending along a longitudinal axis. A first side panel (24) extending from the leading edge in a positive x direction transverse to the longitudinal axis and a second side panel (26) extending from the leading edge in the positive x direction. A first trailing edge (30) on the first side panel, the first trailing edge opposite the leading edge. A second trailing edge (32) on the second side panel, the second trailing edge opposite the leading edge. A first plurality of ridges (34) on an outer surface of the first side panel.

    PRESSURE AND TEMPERATURE SENSORS AND RELATED METHODS
    3.
    发明公开
    PRESSURE AND TEMPERATURE SENSORS AND RELATED METHODS 审中-公开

    公开(公告)号：EP3872468A1

    公开(公告)日：2021-09-01

    申请号：EP21159756.2

    申请日：2021-02-26

    Applicant: ROSEMOUNT AEROSPACE INC.

    Inventor： HOLL, Andy ,  WIGEN, Scott ,  SABLE, Robert E. ,  ISEBRAND, Scott D. ,  BOYD, Brian

    IPC: G01K13/02 ,  G01L19/00 ,  G01L19/06 ,  G01L19/14

    Abstract: A sensor includes an airfoil body (104), a heater element (134), and a temperature probe (158). The airfoil body (104) defines a sensor axis, an insulating cavity (172), and extends between a leading edge and a trailing edge of the airfoil body. The heater element (134)extends axially within the airfoil body and is positioned between the leading edge and the trailing edge of the airfoil body. The temperature probe extends axially within the airfoil body, is positioned between the heater element and the trailing edge of the airfoil body, and is separated from the heater element by the insulating cavity to limit thermal communication between the temperature probe and the heater element. Gas turbine engines, methods of making sensors, and methods of thermally separating temperature probes and heater elements in sensors are also described.

    TEMPERATURE SENSOR
    4.
    发明公开
    TEMPERATURE SENSOR 审中-公开

    公开(公告)号：EP3425359A1

    公开(公告)日：2019-01-09

    申请号：EP18184845.8

    申请日：2014-10-22

    Applicant: Rosemount Aerospace Inc.

    Inventor： WIGEN, Scott ,  SABLE, Robert E. ,  OTTO, John T.

    IPC: G01K13/02 ,  G01K13/00 ,  G01K1/22

    Abstract: A temperature sensor includes a sensor body (102) and a wedge extension (104). The sensor body extends from a sensor base (106) to an opposed sensor tip (108) along a longitudinal axis (A). The sensor body has a leading edge (110) and opposed trailing edge (112). The sensor body also has an interior flow passage (114) with an inlet (116) for fluid communication of fluid into the interior flow passage and an outlet (118) for exhausting fluid out from the interior flow passage. The wedge extension is on the sensor body between the sensor tip and the sensor base on the leading edge of the sensor body.

    SYSTEMS AND METHODS FOR PREVENTING ICE ACCUMULATION
    5.
    发明公开
    SYSTEMS AND METHODS FOR PREVENTING ICE ACCUMULATION 审中-公开
    系统VERFAHREN ZUR VERHINDERUNG VON EISANSAMMLUNG

    公开(公告)号：EP3112832A1

    公开(公告)日：2017-01-04

    申请号：EP16176499.8

    申请日：2016-06-27

    Applicant: Rosemount Aerospace Inc.

    Inventor： GMACH, Matthew J. T. ,  SABLE, Robert E. ,  WIGEN, Scott ,  KUNKEL, Matthew J.

    IPC: G01K13/02

    CPC classification number: B64D15/04 ,  G01K13/028

    Abstract: A device (24; 124) configured to prevent ice accumulation includes at least one wall (40, 42) defining a leading edge (44) and a pneumatic passage (46) configured to receive pressurized fluid. The device also includes at least one ejection port (48) formed in at least one of the leading edge (44) and the at least one wall (40, 42), the at least one ejection port (48) fluidly coupled to the pneumatic passage (46) to receive the pressurized fluid therefrom, the at least one ejection port (48) configured to form fluid jets to divert liquid water droplets away from the leading edge (44) of the device.

    Abstract translation: 被配置为防止积冰的装置（24; 124）包括限定前缘（44）的至少一个壁（40,42）和构造成接收加压流体的气动通道（46）。 该装置还包括形成在前缘（44）和至少一个壁（40,42）中的至少一个中的至少一个喷射口（48），所述至少一个喷射口（48）流体地联接到气动 通道（46）以从其接收加压流体，所述至少一个喷射口（48）构造成形成流体射流以将液体水滴从设备的前缘（44）转移出去。

    PRESSURE AND TEMPERATURE SENSORS AND METHODS OF CONTROLLING ICE ACCRETION ON PRESSURE AND TEMPERATURE SENSORS
    7.
    发明公开
    PRESSURE AND TEMPERATURE SENSORS AND METHODS OF CONTROLLING ICE ACCRETION ON PRESSURE AND TEMPERATURE SENSORS 审中-公开

    公开(公告)号：EP3872467A1

    公开(公告)日：2021-09-01

    申请号：EP21157712.7

    申请日：2021-02-17

    Applicant: ROSEMOUNT AEROSPACE INC.

    Inventor： HOLL, Andrew ,  WIGEN, Scott ,  ISEBRAND, Scott D. ,  SABLE, Robert E. ,  BOYD, Brian

    IPC: G01K13/02 ,  G01L19/00

    Abstract: A sensor (100) includes an airfoil body (104), a heater element (134), and a temperature probe (158). The airfoil body (104) defines a sensor axis (114) and having a leading edge (116), a trailing edge (118), and an ice accretion feature (195). The heater element (134) extends axially through the airfoil body (104) between the leading edge (116) and the trailing edge (118) of the airfoil body (104). The temperature probe (158) extends axially through the airfoil body (104) between the heater element (134) and the trailing edge (118) of the airfoil body (104). The heater element (134) is axially overlapped by the ice accretion feature (195) to accrete ice chordwise forward of a tip surface aperture (170). Gas turbine engines, methods of making sensors, and methods of accreting ice on sensors are also described.

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