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    COMPRESSOR PORTED SHROUD WITH PARTICLE SEPARATOR
    1.
    发明申请
    COMPRESSOR PORTED SHROUD WITH PARTICLE SEPARATOR 有权

    公开(公告)号：US20210381529A1

    公开(公告)日：2021-12-09

    申请号：US16895127

    申请日：2020-06-08

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Zedic Judd ,  Yogendra Sheoran ,  Morris Anderson ,  Tyler Crowe

    IPC: F04D29/70 ,  F04D29/40 ,  F02C7/00

    Abstract: A ported shroud for a compressor associated with a gas turbine engine includes a primary inlet configured to be in fluid communication with the compressor, and the primary inlet is defined to extend along a central axis of the ported shroud. The ported shroud includes a bellmouth that surrounds the primary inlet, and a port plenum configured to be in fluid communication with the compressor. The port plenum extends along an axis that is transverse to the central axis of the ported shroud and transverse to a direction of fluid flow. The port plenum has a port plenum inlet defined about the axis, and the port plenum inlet is defined through the bellmouth such that a tortuous path is defined to the port plenum inlet. The port plenum including a port plenum outlet downstream from the port plenum inlet configured to be in fluid communication with the compressor.

    SYSTEMS FOR THRUST REVERSER WITH TEMPERATURE AND FLUID MANAGEMENT
    2.
    发明申请
    SYSTEMS FOR THRUST REVERSER WITH TEMPERATURE AND FLUID MANAGEMENT 有权

    公开(公告)号：US20210285399A1

    公开(公告)日：2021-09-16

    申请号：US17198594

    申请日：2021-03-11

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Justin C. Mickelsen ,  Morris Anderson

    IPC: F02K1/76 ,  F02K1/60 ,  F02K1/72 ,  F01D25/12 ,  B64D29/04 ,  F01D25/32

    Abstract: A thrust reverser system includes at least one hinge coupled to the thrust reverser system so as to be adjacent to at least one opening defined in the thrust reverser system. The thrust reverser system includes at least one body coupled to the at least one hinge. The at least one body has a first body end and an opposing second body end. The body pivotally coupled to the hinge such that a portion of the body is positionable within the at least one opening and the body includes at least one counterweight at the first body end or the second body end. The body is positioned within the at least one opening based on an operating condition of the gas turbine engine.

    Compressor ported shroud with particle separator
    4.
    发明授权
    Compressor ported shroud with particle separator 有权

    公开(公告)号：US11674527B2

    公开(公告)日：2023-06-13

    申请号：US16895127

    申请日：2020-06-08

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Zedic Judd ,  Yogendra Sheoran ,  Morris Anderson ,  Tyler Crowe

    IPC: F04D29/70 ,  F02C7/00 ,  F04D29/40 ,  F04D17/10

    CPC classification number: F04D29/701 ,  F02C7/00 ,  F04D29/403 ,  F04D17/10 ,  F05D2220/32

    Abstract: A ported shroud for a compressor associated with a gas turbine engine includes a primary inlet configured to be in fluid communication with the compressor, and the primary inlet is defined to extend along a central axis of the ported shroud. The ported shroud includes a bellmouth that surrounds the primary inlet, and a port plenum configured to be in fluid communication with the compressor. The port plenum extends along an axis that is transverse to the central axis of the ported shroud and transverse to a direction of fluid flow. The port plenum has a port plenum inlet defined about the axis, and the port plenum inlet is defined through the bellmouth such that a tortuous path is defined to the port plenum inlet. The port plenum including a port plenum outlet downstream from the port plenum inlet configured to be in fluid communication with the compressor.

    Anti-icing exhaust system
    5.
    发明授权
    Anti-icing exhaust system 有权

    公开(公告)号：US10221765B2

    公开(公告)日：2019-03-05

    申请号：US15248150

    申请日：2016-08-26

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Shawn Alstad ,  Morris Anderson ,  Danis Burton Smith ,  Laurence David Noble Liston

    IPC: F02C7/04 ,  F02C7/047 ,  F02C7/045 ,  B64D15/04 ,  B64D33/02

    Abstract: An anti-icing exhaust system for an inlet of a gas turbine engine is provided. The system includes a first housing portion that at least partially defines a chamber to receive an anti-icing fluid and includes a projection. A second housing portion includes a leading edge. The system includes a support structure that couples the first housing portion to the second housing portion such that the projection of the first housing portion is spaced apart from the leading edge of the second housing portion to define a gap. The gap is in fluid communication with a manifold. The support structure defines at least one flow passage in fluid communication with the chamber and the manifold to exhaust the fluid. The system includes an insulation strip having a first end received in the gap and coupled to the leading edge; and a second end coupled to the second housing portion.

    ANTI-ICING EXHAUST SYSTEM
    6.
    发明申请
    ANTI-ICING EXHAUST SYSTEM 审中-公开

    公开(公告)号：US20180058322A1

    公开(公告)日：2018-03-01

    申请号：US15248150

    申请日：2016-08-26

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Shawn Alstad ,  Morris Anderson ,  Danis Burton Smith ,  Laurence David Noble Liston

    IPC: F02C7/047

    CPC classification number: F02C7/047 ,  B64D15/04 ,  B64D2033/0233 ,  F02C7/045 ,  F05D2220/32 ,  F05D2250/52 ,  F05D2260/30 ,  F05D2260/31 ,  F05D2260/95 ,  Y02T50/672

    Abstract: An anti-icing exhaust system for an inlet of a gas turbine engine is provided. The system includes a first housing portion that at least partially defines a chamber to receive an anti-icing fluid and includes a projection. A second housing portion includes a leading edge. The system includes a support structure that couples the first housing portion to the second housing portion such that the projection of the first housing portion is spaced apart from the leading edge of the second housing portion to define a gap. The gap is in fluid communication with a manifold. The support structure defines at least one flow passage in fluid communication with the chamber and the manifold to exhaust the fluid. The system includes an insulation strip having a first end received in the gap and coupled to the leading edge; and a second end coupled to the second housing portion.

    Air data probe with double helical coil heater cable
    7.
    发明授权
    Air data probe with double helical coil heater cable 有权

    公开(公告)号：US09856027B2

    公开(公告)日：2018-01-02

    申请号：US14878650

    申请日：2015-10-08

    Applicant: Honeywell International Inc.

    Inventor： Morris Anderson ,  Grant A. Gordon ,  Yates Wong ,  Richard Bonvouloir

    IPC: B64D15/12 ,  B64D15/14 ,  B64D43/00 ,  H05B3/56 ,  G01P5/165

    CPC classification number: B64D15/12 ,  B64D15/14 ,  B64D43/00 ,  G01P5/165 ,  H05B3/56 ,  H05B2214/02

    Abstract: An air data probe comprises an elongated body structure having a proximal end and a distal end, with the elongated body structure including an outer surface and an opposing inner surface that defines an interior channel. A probe tip is located at the distal end of the elongated body structure, with the probe tip including an outer surface and an inner surface that are contiguous with the outer an inner surfaces of the elongated body structure. The probe tip has an opening in communication with the interior channel that allows outside air to pass from the probe tip into the interior channel. An electrical heater cable is coupled to the elongated body structure and the probe tip. The electrical heater cable comprises a compact double layer helix portion coupled to the elongated body structure or the probe tip, or coupled to both the elongated body structure and the probe tip.

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