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    TURBINE BLADE WITH INTEGRAL FLOW METER
    2.
    发明申请
    TURBINE BLADE WITH INTEGRAL FLOW METER 审中-公开

    公开(公告)号：US20200291792A1

    公开(公告)日：2020-09-17

    申请号：US16855591

    申请日：2020-04-22

    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 a plurality of cooling passages each having a respective inlet in fluid communication with a source of cooling fluid to receive a cooling fluid. The turbine blade includes a plurality of flow meters, with at least a respective one of the plurality of flow meters associated with a respective one of the plurality of cooling passages at the respective inlet.

    GAS TURBINE ENGINES WITH AIRFOILS HAVING IMPROVED DUST TOLERANCE
    3.
    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 WHEELS, TURBINE ENGINES INCLUDING THE SAME, AND METHODS OF FORMING TURBINE WHEELS WITH IMPROVED SEAL PLATE SEALING
    4.
    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
    5.
    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.

    TURBINE BLADE WITH INTEGRAL FLOW METER
    6.
    发明申请
    TURBINE BLADE WITH INTEGRAL FLOW METER 审中-公开

    公开(公告)号：US20180094527A1

    公开(公告)日：2018-04-05

    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

    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.

    GAS TURBINE ENGINE COMPONENTS WITH BLADE TIP COOLING
    9.
    发明申请
    GAS TURBINE ENGINE COMPONENTS WITH BLADE TIP COOLING 有权
    燃气涡轮发动机组件与叶片冷却

    公开(公告)号：US20140083116A1

    公开(公告)日：2014-03-27

    申请号：US13629284

    申请日：2012-09-27

    Applicant: HONEYWELL INTERNATIONAL INC.

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

    IPC: F01D5/18 ,  F02C3/04

    CPC classification number: F01D5/187 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/221 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A turbine rotor blade for a turbine section of an engine is provided. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path of the turbine section. The airfoil includes a pressure side wall, a suction side wall joined to the pressure side wall at a leading edge and a trailing edge, and a tip cap extending between the suction side wall and the pressure side wall. The rotor blade further includes an internal cooling circuit having a tip cap passage configured to deliver cooling air to the tip cap and a flow accelerator positioned within the tip cap passage of the internal cooling circuit.

    Abstract translation: 提供了一种用于发动机的涡轮机部分的涡轮机转子叶片。 转子叶片包括平台和从平台延伸到涡轮部分的主流气体路径中的翼型件。 翼型件包括压力侧壁，在前缘和后缘处连接到压力侧壁的吸力侧壁和在吸力侧壁和压力侧壁之间延伸的尖端盖。 转子叶片还包括内部冷却回路，其具有构造成将冷却空气输送到顶盖的顶端通道和位于内部冷却回路的顶端通道内的流动加速器。

    TURBINE WHEELS, TURBINE ENGINES INCLUDING THE SAME, AND METHODS OF FORMING TURBINE WHEELS WITH IMPROVED SEAL PLATE SEALING
    10.
    发明申请
    TURBINE WHEELS, TURBINE ENGINES INCLUDING THE SAME, AND METHODS OF FORMING TURBINE WHEELS WITH IMPROVED SEAL PLATE SEALING 审中-公开

    公开(公告)号：US20180156054A1

    公开(公告)日：2018-06-07

    申请号：US15367735

    申请日：2016-12-02

    Applicant: HONEYWELL INTERNATIONAL INC.

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

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

    Abstract: Turbine wheels, turbine engines, and methods of forming the turbine wheels are provided herein. In an embodiment, a turbine wheel includes a rotor disk and a plurality of turbine blades. Each turbine blade is operatively connected to the rotor disk through a blade mount, which is bonded to the rotor disk. The blade mount and the rotor disk have a fore surface on a higher pressure side thereof and an aft surface on a lower pressure side thereof. The blade mount includes a blade attachment surface that extends between and connects the fore surface and the aft surface. The turbine blade extends from the blade attachment surface. A gap is defined between adjacent blade mounts. The gap separates the blade mounts and extends into the rotor disk. The gap includes a pocket that has a fore opening in the fore surface. A pocket seal is disposed in the pocket.

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