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    Vane with L-shaped seal
    51.
    发明授权
    Vane with L-shaped seal 有权

    公开(公告)号：US11125093B2

    公开(公告)日：2021-09-21

    申请号：US16659737

    申请日：2019-10-22

    Applicant: United Technologies Corporation

    Inventor： Bryan P. Dube ,  Michael G. McCaffrey

    IPC: F01D11/00

    Abstract: A vane includes a ceramic vane piece that defines first and second vane platforms and a hollow airfoil section that joins the first and second vane platforms. A structural platform adjacent the first platform defines a radial seal slot. A seal has a radial leg and an axial leg. The radial leg extends in the radial seal slot and the axial leg extends in an interface between the structural platform and the first vane platform.

    CONTOURED STOP FOR VARIABLE AREA TURBINE
    53.
    发明申请
    CONTOURED STOP FOR VARIABLE AREA TURBINE 有权

    公开(公告)号：US20210215057A1

    公开(公告)日：2021-07-15

    申请号：US16740645

    申请日：2020-01-13

    Applicant: United Technologies Corporation

    Inventor： Michael G. McCaffrey

    IPC: F01D11/08 ,  F01D9/04

    Abstract: A vane ring for a gas turbine engine includes a contoured stop that extends from the static flowpath wall, the contoured stop being of an airfoil shape such that a first side of the contoured stop matches a portion of a first side of the first variable vane along a chord length when the first variable vane is pivoted about the longitudinal axis to a first position.

    Single crystal grain structure seals and method of forming
    56.
    发明授权
    Single crystal grain structure seals and method of forming 有权

    公开(公告)号：US10830357B2

    公开(公告)日：2020-11-10

    申请号：US14695981

    申请日：2015-04-24

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Michael G. McCaffrey ,  Jeffrey M. Wittman ,  Dilip M. Shah ,  Alan D. Cetel ,  Timothy M. Davis ,  Mark J. Rogers

    IPC: F16J15/08 ,  B21B1/46 ,  F01D11/00 ,  C30B33/00 ,  C30B29/52 ,  C30B11/14 ,  F16J15/02

    Abstract: The present disclosure relates to advanced materials, particularly single crystal grain structures including the formation of single crystal grain structures. Single crystal grain structures offer improved mechanical properties when used with individual components. Improving mechanical properties is favorable for components that are used in applications with high temperature, pressure, and stress. In these applications, mechanical failure is extremely undesirable. Individual components, such as seals, can be designed with a single crystal grain structure in a preferred direction. By selecting a preferred direction, and orienting the single crystal grain structure accordingly, the single crystal grain structure can improve the component's mechanical properties. Single crystal grain structure seals and the method of forming the seals, therefore, offer various improvements to individual components, specifically when the components are designed for high temperature, pressure, and stress applications.

    Coolant flow redirection component
    57.
    发明授权
    Coolant flow redirection component 有权

    公开(公告)号：US10822953B2

    公开(公告)日：2020-11-03

    申请号：US15800544

    申请日：2017-11-01

    Applicant: United Technologies Corporation

    Inventor： Michael G. McCaffrey ,  Elizabeth F. Vinson

    IPC: F01D5/08

    Abstract: A gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor and mechanically connected to the compressor section via a shaft. Multiple rotors are disposed in one of the compressor section and the turbine section. Each of the rotors includes a rotor disk portion having a radially inward bore, and is static relative to the shaft. Each rotor is axially adjacent at least one other rotor and a gap is defined between each rotor and an adjacent rotor. A cooling passage for a cooling flow is defined between the shaft and the rotors, and a cooling flow redirection component is disposed at the gap and is operable to redirect the cooling flow in the cooling passage into the gap.

    PRE-DIFFUSER FOR A GAS TURBINE ENGINE
    59.
    发明申请
    PRE-DIFFUSER FOR A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20200318833A1

    公开(公告)日：2020-10-08

    申请号：US16376451

    申请日：2019-04-05

    Applicant: United Technologies Corporation

    Inventor： Michael G. McCaffrey ,  Matthew Andrew Hough ,  Pedro Rivero

    IPC: F23R3/10 ,  F01D9/04 ,  F04D29/54

    Abstract: A hot fairing structure for a pre-diffuser includes a ring-strut-ring structure that comprises a multiple of hollow struts; and a multiple of diffusion passage ducts attached to the ring-strut-ring structure. A pre-diffuser for a gas turbine engine includes an exit guide vane ring having a multiple of exit guide vanes defined around an engine longitudinal axis; a ring-strut-ring structure adjacent to the exit guide vane ring to form a multiple of diffusion passages defined around the engine longitudinal axis, an inlet to each of the multiple of diffusion passages smaller than an exit from each of the multiple diffusion passage through the ring-strut-ring structure; a diffusion passage duct attached to the ring-strut-ring structure at the exit from each of the multiple diffusion passage.

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