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    Turbine blade with dust tolerant cooling system
    1.
    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.

    COUNTER-FLOW HEAT EXCHANGE SYSTEMS
    2.
    发明申请
    COUNTER-FLOW HEAT EXCHANGE SYSTEMS 有权
    逆流热交换系统

    公开(公告)号：US20150114611A1

    公开(公告)日：2015-04-30

    申请号：US14064748

    申请日：2013-10-28

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Mark C. Morris ,  Donald G. Godfrey ,  David Waldman

    IPC: F02C7/18 ,  B23P15/26

    CPC classification number: B23P15/26 ,  F02C7/10 ,  F02C7/141 ,  F05D2260/213 ,  F28D7/10 ,  F28D7/106 ,  F28D2021/0021 ,  F28D2021/0026 ,  F28F1/20 ,  F28F2265/26 ,  Y02T50/675 ,  Y10T29/49361

    Abstract: A heat exchange system includes a tubular fan air inlet portion and a tubular cooled air outlet portion connected to a first end of a tubular mid portion. The heat exchange system further includes a tubular hot air inlet portion and a tubular recycled fan air outlet portion connected a second end of the mid portion. Still further, the heat exchange system includes an integrally-formed, compliant heat exchanger tube extending between the hot air inlet portion and the cooled air outlet portion within the mid portion to define a heat exchanger first flow passage within the heat exchanger tube and a second flow passage outside of the heat exchanger tube but within the tubular mid portion. Methods for fabricating such heat exchange systems are also provided.

    Abstract translation: 热交换系统包括管状风扇空气入口部分和连接到管状中间部分的第一端的管状冷却空气出口部分。 热交换系统还包括连接在中间部分的第二端的管状热空气入口部分和管状再循环风扇空气出口部分。 另外，热交换系统包括整体形成的顺从性热交换器管，其在中间部分内的热空气入口部分和冷却空气出口部分之间延伸，以限定热交换器管内的热交换器第一流动通道， 流动通道在热交换器管外面但在管状中间部分内。 还提供了制造这种热交换系统的方法。

    TURBINE BLADE WITH DUST TOLERANT COOLING SYSTEM
    3.
    发明申请
    TURBINE BLADE WITH DUST TOLERANT COOLING SYSTEM 审中-公开

    公开(公告)号：US20200018190A1

    公开(公告)日：2020-01-16

    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 ,  F01D5/20 ,  F01D5/18

    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.

    Finger-foil seals and gas turbine engines employing the same
    6.
    发明授权
    Finger-foil seals and gas turbine engines employing the same 有权
    指箔密封件和采用其的燃气涡轮发动机

    公开(公告)号：US09506566B2

    公开(公告)日：2016-11-29

    申请号：US14061498

    申请日：2013-10-23

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Marshall Saville ,  Keith Alan Hurley ,  Joseph Yanof ,  Tina Hynes ,  David Waldman

    IPC: F01D11/02 ,  F04D29/10 ,  F16J15/16 ,  F16J15/32 ,  F16J15/44 ,  F16C17/02

    CPC classification number: F16J15/164 ,  F01D11/025 ,  F04D29/10 ,  F04D29/102 ,  F05D2240/57 ,  F05D2240/59 ,  F16C17/024 ,  F16C2360/23 ,  F16J15/3212 ,  F16J15/3288 ,  F16J15/445

    Abstract: Embodiments of a gas turbine engine including a finger-foil seal are provided, as are embodiments of a finger-foil seal. In one embodiment, the finger-foil seal includes an aerodynamic foil having a generally annular body through which a first opening is formed. A finger seal retention structure is disposed around the aerodynamic foil. A finger seal backing spring is coupled to the finger seal retention structure and extends radially inward therefrom to contact an outer circumference of the aerodynamic foil. A first anti-rotation pin extends radially from the finger seal retention structure and into the first opening formed in the aerodynamic foil to inhibit rotation of the aerodynamic foil during operation of the finger-foil seal.

    Abstract translation: 提供包括指箔密封件的燃气涡轮发动机的实施例，如指箔密封件的实施例。 在一个实施例中，指箔密封件包括具有大致环形主体的空气动力箔，通过该主体形成第一开口。 手指密封保持结构设置在空气动力学箔的周围。 手指密封背衬弹簧联接到手指密封保持结构并且从其径向向内延伸以接触空气动力学箔的外周。 第一防旋转销从指状密封保持结构径向延伸并且形成在空气动力学箔中形成的第一开口中，以在手指箔密封件的操作期间阻止气动箔的旋转。

    TURBINE ROTOR BLADES WITH TIP PORTION PARAPET WALL CAVITIES
    7.
    发明申请
    TURBINE ROTOR BLADES WITH TIP PORTION PARAPET WALL CAVITIES 有权
    涡轮转子叶片与提示部分PARAPET墙壁CAVITIES

    公开(公告)号：US20150104327A1

    公开(公告)日：2015-04-16

    申请号：US14055568

    申请日：2013-10-16

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Malak Fouad Malak ,  Mark C. Morris ,  David Waldman

    IPC: F01D5/18

    CPC classification number: F01D11/10 ,  F01D5/187 ,  F05D2240/307 ,  Y02T50/673 ,  Y02T50/676

    Abstract: In accordance with an exemplary embodiment, a turbine rotor blade is provided for a turbine section of an engine. The turbine 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 first side wall; a second side wall joined to the first side wall at a leading edge and a trailing edge; a tip cap extending between the first side wall and the second side wall; a first parapet wall extending from the first side wall; a first parapet wall cavity formed at least partially within the first parapet wall; and a first cooling hole extending between the first parapet wall cavity and a first surface of the first parapet wall such that cooling air flows through the first parapet wall cavity, through the first cooling hole, and out of the first parapet wall.

    Abstract translation: 根据示例性实施例，为发动机的涡轮机部分提供涡轮转子叶片。 涡轮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。 翼型件包括第一侧壁; 在前缘和后缘处连接到第一侧壁的第二侧壁; 在所述第一侧壁和所述第二侧壁之间延伸的尖端盖; 从所述第一侧壁延伸的第一护墙壁; 至少部分地形成在所述第一栏杆壁内的第一护墙壁腔; 以及在所述第一栏杆壁腔和所述第一护墙壁的第一表面之间延伸的第一冷却孔，使得冷却空气通过所述第一冷却孔流过所述第一栏杆壁腔，并且从所述第一栏杆壁流出。

    TURBINE ROTOR BLADES WITH IMPROVED TIP PORTION COOLING HOLES
    8.
    发明申请
    TURBINE ROTOR BLADES WITH IMPROVED TIP PORTION COOLING HOLES 有权
    涡轮转子叶片与改进的提升部分冷却孔

    公开(公告)号：US20150104326A1

    公开(公告)日：2015-04-16

    申请号：US14055521

    申请日：2013-10-16

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： David Waldman ,  Mark C. Morris ,  Malak Fouad Malak

    IPC: F01D5/18 ,  F01D5/14

    CPC classification number: F01D5/18 ,  F01D5/147 ,  F01D5/20 ,  F05D2230/00 ,  F05D2260/20 ,  Y02T50/673 ,  Y10T29/49341

    Abstract: A turbine rotor blade is provided for a turbine section of an engine. The turbine 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 first side wall; a second side wall joined to the first side wall at a leading edge and a trailing edge; a tip cap extending between the first side wall and the second side wall; a first parapet wall extending from the first side wall; and a first cooling hole through the tip cap and the first parapet wall configured to deliver cooling air. The first cooling hole has a closed channel section and an open channel section. The open channel section forms a slot.

    Abstract translation: 为发动机的涡轮机部分提供涡轮转子叶片。 涡轮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。 翼型件包括第一侧壁; 在前缘和后缘处连接到第一侧壁的第二侧壁; 在所述第一侧壁和所述第二侧壁之间延伸的尖端盖; 从所述第一侧壁延伸的第一护墙壁; 以及通过所述顶盖和所述第一护板壁的第一冷却孔，其构造成输送冷却空气。 第一冷却孔具有闭合通道部分和开放通道部分。 开放通道部分形成一个插槽。

    Turbine blade with dust tolerant cooling system
    9.
    发明授权
    Turbine blade with dust tolerant cooling system 有权

    公开(公告)号：US11333042B2

    公开(公告)日：2022-05-17

    申请号：US16998523

    申请日：2020-08-20

    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 an 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 to direct the particles and a portion of the cooling fluid into the inlet.

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