公开(公告)号：US20070059182A1

公开(公告)日：2007-03-15

申请号：US11162433

申请日：2005-09-09

Applicant: Mark Stegemiller ,  Chander Prakash ,  Leslie Leeke ,  Kevin Klasing ,  Ching-Pang Lee

Inventor： Mark Stegemiller ,  Chander Prakash ,  Leslie Leeke ,  Kevin Klasing ,  Ching-Pang Lee

IPC: B64C27/46

CPC classification number: F01D5/20 ,  F05D2250/71 ,  F05D2250/712 ,  Y02T50/67

Abstract: An airfoil for a gas turbine engine includes a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls extending generally along a radial axis. The airfoil includes a tip cap extending between the pressure and suction sidewalls; and spaced-apart suction-side and pressure-side tip walls extending radially outward from the tip cap to define a tip cavity therebetween. The pressure-side tip wall includes a continuously concave curved arcuate portion, at least a section of which extends circumferentially outward from a radial axis of the airfoil.

Abstract translation: 用于燃气涡轮发动机的翼型件包括根部，尖端，前缘，后缘以及大致沿径向轴线延伸的相对的压力和吸力侧壁。 翼型件包括在压力侧和吸力侧壁之间延伸的顶盖; 并且间隔开的吸入侧和压力侧尖端壁从尖端帽径向向外延伸以在它们之间限定尖端腔。 压力侧末端壁包括连续凹入的弯曲弧形部分，其至少一部分从翼型件的径向轴向向外延伸。

公开(公告)号：US20070140850A1

公开(公告)日：2007-06-21

申请号：US11312059

申请日：2005-12-20

Applicant: Tingfan Pang ,  Ching-Pang Lee ,  Kevin Klasing ,  Steven Brassfield

Inventor： Tingfan Pang ,  Ching-Pang Lee ,  Kevin Klasing ,  Steven Brassfield

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F05D2240/122 ,  F05D2240/304 ,  Y02T50/676

Abstract: A method facilitates fabricating an airfoil for use with a turbine blade. The method comprises forming a substantially solid ceramic airfoil core, inserting the core into a die and casting the airfoil with a pressure side wall and a suction side wall connected together at a leading edge and a trailing edge, such that a plurality of first trailing edge slots and at least one second trailing edge slot extend from the trailing edge along the pressure side wall, wherein the second trailing edge slot has a length, measured between an inlet and an exit of the slot, that is longer than a corresponding length of each of the plurality of first trailing edge slots.

Abstract translation: 一种方法有助于制造与涡轮叶片一起使用的翼型件。 该方法包括形成基本上固体的陶瓷翼型芯，将芯插入模具中并且在前缘和后缘连接有压力侧壁和吸力侧壁的情况下铸造翼型件，使得多个第一后缘 槽和至少一个第二后缘槽沿着所述压力侧壁从所述后缘延伸，其中所述第二后缘槽具有在所述槽的入口和出口之间测量的长度，所述长度大于每个的相应长度 的多个第一后缘槽。

公开(公告)号：US20070128021A1

公开(公告)日：2007-06-07

申请号：US10907476

申请日：2005-04-01

Applicant: Kevin Klasing ,  Scott Carson

Inventor： Kevin Klasing ,  Scott Carson

IPC: F04D29/54

CPC classification number: F01D5/145 ,  F01D5/143 ,  F01D9/041 ,  F01D11/001 ,  Y02T50/672 ,  Y02T50/673

Abstract: A turbine nozzle for a gas turbine engine includes a nozzle segment having an airfoil-shaped vane with a root, a tip, a leading edge, a trailing edge and opposed curved pressure and suction sides. An arcuate inner band segment is attached to the root of the vane. The inner band segment includes an inner flowpath surface bounded at forward and aft ends thereof by a forward-facing surface and an aft-facing surface, respectively. A convex curved blended corner is formed between the inner flowpath surface and the aft-facing surface.

Abstract translation: 用于燃气涡轮发动机的涡轮喷嘴包括具有叶形翼片的喷嘴段，其具有根部，尖端，前缘，后缘和相对的弯曲压力和吸力侧。 弧形内带段连接到叶片的根部。 内带段包括在其前端和后端分别由前向表面和后向表面限定的内部流路表面。 内侧流路面与后方面之间形成有凸曲面的混合角。