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    TURBINE VANE WITH DUST TOLERANT COOLING SYSTEM
    2.
    发明申请
    TURBINE VANE WITH DUST TOLERANT COOLING SYSTEM 有权

    公开(公告)号：US20210172336A1

    公开(公告)日：2021-06-10

    申请号：US17180035

    申请日：2021-02-19

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Steven Whitaker ,  Daniel C. Crites ,  Mark C. Morris ,  Ardeshir Riahi

    IPC: F01D25/12 ,  F01D9/04

    Abstract: A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend between a first surface and a second surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.

    Turbine blade with dust tolerant cooling system
    3.
    发明授权
    Turbine blade with dust tolerant cooling system 有权

    公开(公告)号：US10787932B2

    公开(公告)日：2020-09-29

    申请号：US16035191

    申请日：2018-07-13

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Daniel C. Crites ,  Mark C. Morris ,  Steven Whitaker ,  David Waldman

    IPC: F01D25/32 ,  F01D5/18 ,  F01D5/20

    Abstract: A turbine blade includes an airfoil that has a tip region that extends from the leading edge toward the trailing edge, and the tip region is bounded by a wall that extends at a positive angle. The leading edge has a leading edge cooling circuit that is defined from the platform to a tip flag channel, and the leading edge cooling circuit is in fluid communication with the tip flag channel. The pressure side includes at least one tip dust hole defined through the wall proximate the pressure side, and the at least one tip dust hole has an inlet and an outlet. The airfoil has at least one rib defined on the wall that extends at a second angle, and the at least one rib merges with at least one flow scoop to direct the particles and a portion of the cooling fluid into the inlet.

    Blockage-resistant vane impingement tubes and turbine nozzles containing the same
    4.
    发明授权
    Blockage-resistant vane impingement tubes and turbine nozzles containing the same 有权

    公开(公告)号：US10577954B2

    公开(公告)日：2020-03-03

    申请号：US15470471

    申请日：2017-03-27

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Harry Lester Kington ,  Daniel C. Crites ,  Jeff Howe

    IPC: F01D5/14 ,  F01D9/04 ,  F01D9/06 ,  F01D5/18

    Abstract: Vane impingement tubes having blockage deterrent features are provided, as turbine nozzles containing blockage-resistant vane impingement tubes. In an embodiment, the turbine nozzle includes inner and outer annular endwalls, and turbine nozzle vanes arranged in an annular array between the outer and inner annular endwalls. Vane impingement tubes are inserted into the turbine nozzle vanes. The vane impingement tubes each includes a tube body, an impingement outlet formed in the tube body and configured to discharge airflow for impingement against one of the turbine nozzle vanes, a first flow-turning feature located in the tube body, and an inlet formed in the tube body and configured receive cooling airflow in a substantially radial direction. The first flow-turning feature is shaped and positioned to turn the airflow received through the inlet in a substantially axial direction, which is perpendicular to the radial direction, prior to discharge through the impingement outlet.

    GAS TURBINE ENGINES WITH AIRFOILS HAVING IMPROVED DUST TOLERANCE
    5.
    发明申请
    GAS TURBINE ENGINES WITH AIRFOILS HAVING IMPROVED DUST TOLERANCE 审中-公开

    公开(公告)号：US20190186273A1

    公开(公告)日：2019-06-20

    申请号：US15841844

    申请日：2017-12-14

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Steve Halfmann ,  Daniel C. Crites ,  Mark C. Morris ,  Ardeshir Riahi

    IPC: F01D5/18

    CPC classification number: F01D5/187 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2250/60 ,  F05D2260/20 ,  F05D2260/607

    Abstract: An airfoil for a gas turbine engine includes a first side wall; a second side wall joined to the first side wall at a leading edge and a trailing edge; and an internal cooling system arranged within the first and second side walls configured to direct cooling air through and out of the airfoil. The internal cooling system has a first cooling circuit that includes an acceleration channel generally extending in a radial outward direction. A first section of the acceleration channel decreases in cross-sectional area along the radial outward direction such that the cooling air is accelerated through the first section of the acceleration channel. The first cooling circuit further includes a trailing edge chamber fluidly coupled to receive at least a portion of the cooling air from the acceleration channel and extending generally in a chordwise aft direction from the acceleration channel to the trailing edge.

    Turbine nozzle with reduced leakage feather seals
    8.
    发明授权
    Turbine nozzle with reduced leakage feather seals 有权

    公开(公告)号：US11156116B2

    公开(公告)日：2021-10-26

    申请号：US16378030

    申请日：2019-04-08

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Benjamin Dosland Kamrath ,  Jason Smoke ,  Daniel C. Crites ,  Mark C. Morris

    IPC: F01D9/04 ,  F01D11/00

    Abstract: A turbine nozzle for a gas turbine engine includes a plurality of nozzle segments that are configured to be assembled into a full ring such that each one of the plurality of nozzle segments is adjacent to another one of the plurality of nozzle segments. Each one of the plurality of nozzle segments includes an endwall segment and a nozzle vane. The turbine nozzle includes a feather seal interface defined by endwall segments of adjacent ones of the plurality of nozzle segments. The feather seal interface is defined along an area of reduced pressure drop through a pressure field defined between adjacent nozzle vanes of the plurality of nozzle segments to reduce leakage through the plurality of nozzle segments. The turbine nozzle includes a feather seal received within the feather seal interface that cooperates with the feather seal interface to reduce leakage through the plurality of nozzle segments.

    TURBINE WHEELS, TURBINE ENGINES INCLUDING THE SAME, AND METHODS OF FORMING TURBINE WHEELS WITH IMPROVED SEAL PLATE SEALING
    9.
    发明申请
    TURBINE WHEELS, TURBINE ENGINES INCLUDING THE SAME, AND METHODS OF FORMING TURBINE WHEELS WITH IMPROVED SEAL PLATE SEALING 有权

    公开(公告)号：US20210003023A1

    公开(公告)日：2021-01-07

    申请号：US17014547

    申请日：2020-09-08

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Steve Halfmann ,  Daniel C. Crites ,  Michael Kahrs ,  Ardeshir Riahi ,  Jude Miller

    IPC: F01D11/00 ,  F01D5/08 ,  F01D5/30

    Abstract: A turbine engine includes a turbine wheel including a rotor disk and turbine blades connected to the rotor disk through blade mounts. The blade mounts and the rotor disk have fore and aft surfaces. The blade mount includes a blade attachment surface connecting the fore and aft surfaces with the turbine blade extending from the blade attachment surface. A gap is defined between and separating adjacent blade mounts and extends into the rotor disk. The gap includes a pocket having a fore opening and a rotor relief hole. The turbine wheel further includes a plug disposed in a rotor relief opening and a pocket seal disposed in the pocket. The turbine engine further includes a fore seal plate having an edge abutting the blade mounts about a circumference of the turbine wheel and a finger extending toward and contacting the plug to maintain the plug in the rotor relief opening.

    Turbine blade with integral flow meter
    10.
    发明授权
    Turbine blade with integral flow meter 有权

    公开(公告)号：US10683763B2

    公开(公告)日：2020-06-16

    申请号：US15285347

    申请日：2016-10-04

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Steve Halfmann ,  Daniel C. Crites ,  Michael Kahrs ,  Ardeshir Riahi ,  Jude Miller

    IPC: F01D5/18 ,  F01D5/08

    Abstract: A turbine blade with an integral flow meter is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade includes at least one cooling passage defined internally within the turbine blade, and the at least one cooling passage is in fluid communication with a source of cooling fluid via an inlet to receive a cooling fluid. The turbine blade also includes at least one flow meter formed within the turbine blade at the inlet that supplies the cooling fluid to the at least one cooling passage.

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