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    INLET GUIDE VANE HAVING A VARIED TRAILING EDGE GEOMETRY
    21.
    发明申请
    INLET GUIDE VANE HAVING A VARIED TRAILING EDGE GEOMETRY 审中-公开

    公开(公告)号：US20190078450A1

    公开(公告)日：2019-03-14

    申请号：US15698997

    申请日：2017-09-08

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： James A. Eley ,  Eric A. Grover ,  Thomas J. Praisner

    IPC: F01D9/04 ,  F01D5/14 ,  F01D17/16

    Abstract: An inlet guide vane having varied trailing edge geometry is provided. The inlet guide vane may have an inner diameter edge opposite an outer diameter edge, and may comprise a leading edge part and a trailing edge part. The trailing edge part may comprise a trailing edge length defining a length between a forward edge and an aft edge. The trailing edge length may vary in length. The trailing edge part may be displaced from the leading edge part at a stagger angle. The stagger angle may vary in displacement.

    Variable area vane endwall treatments
    26.
    发明授权
    Variable area vane endwall treatments 有权

    公开(公告)号：US11118471B2

    公开(公告)日：2021-09-14

    申请号：US15027526

    申请日：2014-10-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： John D. Teixeira ,  Eric A. Grover ,  Raymond Surace

    IPC: F01D17/16 ,  F01D5/14

    Abstract: A gas turbine engine component includes an outer diameter endwall, an inner diameter endwall spaced radially inward of the outer diameter endwall, and at least one body supported between the outer and inner endwalls for rotation about an axis. The body includes an outer diameter surface spaced from the outer diameter endwall by a first gap and an inner diameter surface spaced from the inner diameter endwall by a second gap. The outer and inner diameter surfaces and the outer and inner diameter endwalls are configured such that the first and second gaps remain generally constant in size as the body rotates about the axis.

    GAS TURBINE ENGINE AIRFOIL
    27.
    发明申请
    GAS TURBINE ENGINE AIRFOIL 有权

    公开(公告)号：US20210115803A1

    公开(公告)日：2021-04-22

    申请号：US16654380

    申请日：2019-10-16

    Applicant: United Technologies Corporation

    Inventor： Timothy Charles Nash ,  Gary A. Zess ,  Eric A. Grover ,  Jin Hu

    IPC: F01D9/02

    Abstract: An airfoil includes pressure and suction sides that extend between a leading edge and a trailing edge. The airfoil has a camber line along an airfoil section that is equidistant between the exterior surface of the pressure and suction sides. The camber line extends from a 0% camber position at the leading edge to a 100% camber position at the trailing edge. A ratio of a maximum thickness to an axial chord length is between 0.2 and 0.5. The maximum thickness is located along the camber line between about 13% and 38% camber position.

    Hydrostatic seal with enhanced maneuver response
    28.
    发明授权
    Hydrostatic seal with enhanced maneuver response 有权

    公开(公告)号：US10961858B2

    公开(公告)日：2021-03-30

    申请号：US16239611

    申请日：2019-01-04

    Applicant: United Technologies Corporation

    Inventor： Eric A. Grover ,  Brian F. Hilbert ,  Daniel L. Gysling ,  Christopher W. Robak

    IPC: F01D11/00 ,  F01D11/08

    Abstract: A hydrostatic seal configured to be disposed between relatively rotatable components includes a base. The seal also includes a seal housing. The seal further includes a shoe operatively coupled to the base and extending axially from a forward end to an aft end. The seal yet further includes a plurality of teeth extending radially from a sealing surface of the shoe, one of the teeth being a longest tooth that extends furthest radially from the sealing surface, the axial distance from the forward end of the shoe to the longest tooth being greater than a radial distance from a radial tooth tip to the sealing surface.

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