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    TURBINE ROTOR DISKS AND TURBINE ASSEMBLIES
    1.
    发明申请
    TURBINE ROTOR DISKS AND TURBINE ASSEMBLIES 审中-公开
    涡轮转子盘和涡轮总成

    公开(公告)号：US20120148406A1

    公开(公告)日：2012-06-14

    申请号：US12966694

    申请日：2010-12-13

    申请人： Steve Halfmann ,  Daniel Cregg Crites ,  Malak Fouad Malak ,  Mark C. Morris ,  Ardeshir Riahi ,  Brandan Wakefield

    发明人： Steve Halfmann ,  Daniel Cregg Crites ,  Malak Fouad Malak ,  Mark C. Morris ,  Ardeshir Riahi ,  Brandan Wakefield

    IPC分类号： F01D5/08

    CPC分类号： F01D5/085 ,  F01D5/088 ,  F01D5/3007 ,  F05D2240/81 ,  Y02T50/676

    摘要： A turbine rotor disk is provided. The turbine rotor disk includes a hub, a ring attached to the hub, the ring including a plurality of posts extending radially outwardly and disposed around a circumference of the ring, each post including a first radially-extending face, a second radially-extending face, and a blade attachment surface extending axially between the first and second radially-extending faces, a main cooling air feed channel formed in each post and extending from the first radially-extending face toward the second radially-extending face, and a plurality of ancillary jet openings formed in each post and extending from the main cooling air feed channel to the blade attachment surface.

    摘要翻译： 提供涡轮转子盘。 涡轮转子盘包括轮毂，附接到毂的环，环包括径向向外延伸并围绕环的圆周设置的多个柱，每个柱包括第一径向延伸面，第二径向延伸面 以及在第一和第二径向延伸面之间轴向延伸的刀片附接表面，形成在每个柱中并从第一径向延伸面朝向第二径向延伸面延伸的主冷却空气供给通道，以及多个辅助 在每个柱中形成并且从主冷却空气供给通道延伸到叶片附接表面的喷射开口。

    TURBINE BLADES, TURBINE ASSEMBLIES, AND METHODS OF MANUFACTURING TURBINE BLADES
    5.
    发明申请
    TURBINE BLADES, TURBINE ASSEMBLIES, AND METHODS OF MANUFACTURING TURBINE BLADES 有权
    涡轮叶片，涡轮组件及制造涡轮叶片的方法

    公开(公告)号：US20120070307A1

    公开(公告)日：2012-03-22

    申请号：US12888202

    申请日：2010-09-22

    申请人： Kin Poon ,  Malak Fouad Malak ,  Ardeshir Riahi ,  David Chou

    发明人： Kin Poon ,  Malak Fouad Malak ,  Ardeshir Riahi ,  David Chou

    IPC分类号： F01D5/18 ,  B22D27/02 ,  B23P15/02 ,  B22D25/02

    CPC分类号： F01D5/20 ,  F01D5/187 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/49341

    摘要： A turbine blade includes a first side wall including a first tip edge, a second side wall opposite the first side wall and including a second tip edge, a tip wall between the first and second side walls, the tip wall recessed from the first tip edge of the first side wall and the second tip edge of the second side wall forming a coolant cavity, a tip recess cavity, a first parapet wall on the first side wall, and a second parapet wall on the second side wall, the coolant cavity defined by the tip wall, and the tip recess cavity defined by the tip wall, and the first and second parapet walls, a step formed between the first tip edge and the tip wall, a cooling hole through the first parapet wall, the step, and the tip wall, the cooling hole including an open and a closed channel section.

    摘要翻译： 涡轮叶片包括第一侧壁，其包括第一末端边缘，与第一侧壁相对的第二侧壁，并且包括第二末端边缘，位于第一和第二侧壁之间的末端壁， 所述第一侧壁和所述第二侧壁的所述第二末端边缘形成冷却剂腔，所述顶部凹陷空腔，所述第一侧壁上的第一栏杆壁和所述第二侧壁上的第二护墙壁，所述冷却剂腔被限定 由尖端壁和由尖端壁限定的尖端凹部空腔以及第一和第二护墙壁，在第一顶端边缘和尖端壁之间形成的台阶，穿过第一栏杆壁的冷却孔，台阶和 尖端壁，冷却孔包括开放和封闭的通道部分。

    Turbine blades, turbine assemblies, and methods of manufacturing turbine blades
    6.
    发明授权
    Turbine blades, turbine assemblies, and methods of manufacturing turbine blades 有权
    涡轮叶片，涡轮组件以及制造涡轮叶片的方法

    公开(公告)号：US08777567B2

    公开(公告)日：2014-07-15

    申请号：US12888202

    申请日：2010-09-22

    申请人： Kin Poon ,  Malak Fouad Malak ,  Ardeshir Riahi ,  David Chou

    发明人： Kin Poon ,  Malak Fouad Malak ,  Ardeshir Riahi ,  David Chou

    IPC分类号： F01D5/20 ,  F01D5/18

    CPC分类号： F01D5/20 ,  F01D5/187 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/49341

    摘要： A turbine blade includes a first side wall including a first tip edge, a second side wall opposite the first side wall and including a second tip edge, a tip wall between the first and second side walls, the tip wall recessed from the first tip edge of the first side wall and the second tip edge of the second side wall forming a coolant cavity, a tip recess cavity, a first parapet wall on the first side wall, and a second parapet wall on the second side wall, the coolant cavity defined by the tip wall, and the tip recess cavity defined by the tip wall, and the first and second parapet walls, a step formed between the first tip edge and the tip wall, a cooling hole through the first parapet wall, the step, and the tip wall, the cooling hole including an open and a closed channel section.

    摘要翻译： 涡轮叶片包括第一侧壁，其包括第一末端边缘，与第一侧壁相对的第二侧壁，并且包括第二末端边缘，位于第一和第二侧壁之间的末端壁， 所述第一侧壁和所述第二侧壁的所述第二末端边缘形成冷却剂腔，所述顶部凹陷空腔，所述第一侧壁上的第一栏杆壁和所述第二侧壁上的第二护墙壁，所述冷却剂腔被限定 由尖端壁和由尖端壁限定的尖端凹部空腔以及第一和第二护墙壁，在第一顶端边缘和尖端壁之间形成的台阶，穿过第一栏杆壁的冷却孔，台阶和 尖端壁，冷却孔包括开放和封闭的通道部分。

    TURBINE ENGINE COMPONENTS
    7.
    发明申请
    TURBINE ENGINE COMPONENTS 有权
    涡轮发动机组件

    公开(公告)号：US20100329846A1

    公开(公告)日：2010-12-30

    申请号：US12490840

    申请日：2009-06-24

    申请人： Dhinagaran Ramachandran ,  Balamurugan Srinivasan ,  Gopal Muthiah ,  Jyothishkumar Venkataramanan ,  Jong Liu ,  Luis Tapia ,  Malak Fouad Malak

    发明人： Dhinagaran Ramachandran ,  Balamurugan Srinivasan ,  Gopal Muthiah ,  Jyothishkumar Venkataramanan ,  Jong Liu ,  Luis Tapia ,  Malak Fouad Malak

    IPC分类号： F01D5/14

    CPC分类号： F01D5/187 ,  F01D5/186 ,  F05D2250/314 ,  F05D2260/221 ,  Y02T50/676

    摘要： A turbine engine component includes a wall, a main opening, and two clusters of two or more auxiliary openings. The wall includes cool and hot air sides. The main opening extends between the cool air side and the hot air side and has an inlet and an outlet. The inlet is formed on the cool air side, and the outlet is formed on the hot air side. The first cluster of two or more auxiliary openings extends from the main opening to the hot air side. The second cluster of two or more auxiliary openings extends from the main opening to the hot air side. The main opening may be cylindrical or conical with a converging passage extending from the cool air side to the hot air side. The converging main opening may enhance flow through the auxiliary openings especially at high blowing ratios.

    摘要翻译： 涡轮发动机部件包括壁，主开口和两个或更多个辅助开口的两个簇。 墙壁包括凉爽和热的空气两侧。 主开口在冷空气侧和热空气侧之间延伸并具有入口和出口。 入口形成在冷空气侧，出口形成在热空气侧。 两个或更多个辅助开口的第一簇从主开口延伸到热空气侧。 两个或更多个辅助开口的第二组从主开口延伸到热空气侧。 主开口可以是圆柱形或圆锥形的，具有从冷空气侧延伸到热空气侧的会聚通道。 会聚主开口可以增强通过辅助开口的流动，特别是在高吹风比下。

    INTER-TURBINE DUCTS WITH VARIABLE AREA RATIOS
    9.
    发明申请
    INTER-TURBINE DUCTS WITH VARIABLE AREA RATIOS 有权
    具有可变区域的涡轮泵

    公开(公告)号：US20130294908A1

    公开(公告)日：2013-11-07

    申请号：US13462738

    申请日：2012-05-02

    申请人： Vinayender Kuchana ,  Balamurugan Srinivasan ,  Sujatha Guntu ,  Malak Fouad Malak ,  Paul Couey ,  Craig Mckeever

    发明人： Vinayender Kuchana ,  Balamurugan Srinivasan ,  Sujatha Guntu ,  Malak Fouad Malak ,  Paul Couey ,  Craig Mckeever

    IPC分类号： F01D1/04

    CPC分类号： F01D5/145 ,  F01D9/041 ,  Y02T50/671 ,  Y02T50/673

    摘要： A turbine section of a gas turbine engine is annular about a longitudinal axis. The turbine section includes a first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; and an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine. The inter-turbine duct has a first station with a first meridional area, a second station with a second meridional area, and a third station with a third meridional area. The first station is upstream of the second station and the second station is upstream of the third station, and the second meridional area is less than or equal to the first meridional area.

    摘要翻译： 燃气涡轮发动机的涡轮机部分围绕纵向轴线是环形的。 涡轮部分包括具有第一入口和第一出口的第一涡轮机; 具有第二入口和第二出口的第二涡轮机; 以及从所述第一出口延伸到所述第二入口并且构造成将空气流从所述第一涡轮引导到所述第二涡轮机的涡轮机间管道。 所述涡轮机间通道具有具有第一子午区域的第一站，具有第二子午区域的第二站和具有第三子午线区域的第三站。 第一站位于第二站的上游，第二站位于第三站的上游，第二子午区小于或等于第一子午区。