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    Exhaust duct
    11.
    发明授权
    Exhaust duct 有权

    公开(公告)号：US10514003B2

    公开(公告)日：2019-12-24

    申请号：US14972195

    申请日：2015-12-17

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Eray Akcayoz ,  Francois Doyon ,  Julie Demers

    IPC: F02K1/40 ,  F01D25/30 ,  F02K1/78 ,  F02C6/20

    Abstract: An exhaust duct for a gas turbine engine has an annular inlet conduit having an inlet axis. At least two outlet conduits branch off from the inlet conduit along respective outlet centerlines that are distinct from one another. The outlet centerlines when projected onto a projection plane perpendicular to the inlet axis are spaced apart from the inlet axis so as not to intersect the inlet axis.

    Inlet guard screen for an inlet of an aircraft engine
    12.
    发明授权
    Inlet guard screen for an inlet of an aircraft engine 有权

    公开(公告)号：US12241412B1

    公开(公告)日：2025-03-04

    申请号：US18481705

    申请日：2023-10-05

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Roberto Marrano ,  Mark Cunningham ,  Eray Akcayoz ,  Corentin Brette

    IPC: F02C7/055 ,  B64D33/02

    Abstract: A system for an aircraft includes an aircraft engine having a central axis with a flowpath projecting into the aircraft engine from an airflow inlet. An inlet plenum at the airflow inlet extends between a front wall and a rear wall along the central axis. An inlet guard is arranged at the airflow inlet and extends across the flowpath. The inlet guard includes a first screen extending circumferentially about the central axis. The first screen has a first screen axial width L1 extending from the front wall to the rear wall. The inlet guard further includes a second screen extending at least partially circumferentially about the central axis. The second screen is disposed radially outward of the first screen and axially overlaps the first screen. The second screen has a second screen axial width L2 less than the first screen axial width L1.

    Gas turbine engine nozzle loft for thrust reverser
    14.
    发明授权
    Gas turbine engine nozzle loft for thrust reverser 有权

    公开(公告)号：US12000358B1

    公开(公告)日：2024-06-04

    申请号：US18109428

    申请日：2023-02-14

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Mark Cunningham ,  Eray Akcayoz

    IPC: F02K1/62 ,  F02K1/58

    CPC classification number: F02K1/62 ,  F02K1/58 ,  F05D2220/323

    Abstract: An engine nacelle assembly includes a nacelle that defines a flow path between an intake end and an exhaust end, and a nozzle that is disposed at the exhaust end of the nacelle about a central axis. The nozzle includes opposing thrust reverser openings and thrust reverser doors. A cross-sectional area transverse to the central axis proximate a forward side of each of the opposing thrust reverser openings is oval shaped with an offset radius within offset arc segments that are aligned with the opposing thrust reverser openings and a first radius outside of the offset arc segment. The first radius is less than the offset radius.

    Systems and methods for controlling an intake inlet shape of a propulsion system air intake
    15.
    发明授权
    Systems and methods for controlling an intake inlet shape of a propulsion system air intake 有权

    公开(公告)号：US11994064B2

    公开(公告)日：2024-05-28

    申请号：US17977722

    申请日：2022-10-31

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Mark Cunningham ,  Eray Akcayoz ,  Raja Ramamurthy ,  Roberto Marrano

    IPC: F02C7/042

    CPC classification number: F02C7/042 ,  F05D2220/323 ,  F05D2270/60

    Abstract: An air intake for an aircraft propulsion system includes an air inlet duct and a flow control device. The air inlet duct includes an interior surface and an intake inlet. The interior surface extends from the intake inlet. The interior surface forms and surrounds an inlet flow passage through the air inlet duct. The intake inlet includes a top side, a bottom side, a first lateral side, and a second lateral side. Each of the first lateral side and the second lateral side extend between and to the top side and the bottom side. The flow control device is disposed inside the air inlet duct at the first lateral side. The flow control device is configured to form an asymmetrical shape of the intake inlet at the first lateral side relative to the second lateral side.

    SYSTEMS AND METHODS FOR CONTROLLING STRUT POSITIONS FOR AN AIRCRAFT PROPULSION SYSTEM STRUT ASSEMBLY
    16.
    发明公开
    SYSTEMS AND METHODS FOR CONTROLLING STRUT POSITIONS FOR AN AIRCRAFT PROPULSION SYSTEM STRUT ASSEMBLY 审中-公开

    公开(公告)号：US20240159185A1

    公开(公告)日：2024-05-16

    申请号：US17986594

    申请日：2022-11-14

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Eray Akcayoz ,  Raja Ramamurthy

    IPC: F02C7/057 ,  B64D27/10 ,  F01D25/24

    CPC classification number: F02C7/057 ,  B64D27/10 ,  F01D25/24

    Abstract: A strut assembly for an aircraft propulsion system includes an outer case, an inner case, a plurality of struts, and a plurality of pressure sensors. Each strut extends between and to the outer case and the inner case. A first strut of the plurality of struts includes a leading strut portion and a trailing strut portion. One or both of the leading strut portion and the trailing strut portion is rotatable. The leading strut portion extends between a first axial end and a second axial end. The first axial end forms a leading edge of the first strut. The leading strut portion includes a first side surface and a second side surface. The plurality of pressure sensors includes a first pressure sensor and a second pressure sensor. The first pressure sensor is disposed at the first side surface and the second pressure sensor is disposed at the second side surface.

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