公开(公告)号：US06923616B2

公开(公告)日：2005-08-02

申请号：US10653519

申请日：2003-09-02

Applicant: Ronald Eugene McRae, Jr. ,  Sean Robert Keith ,  Gulcharan Singh Brainch

Inventor： Ronald Eugene McRae, Jr. ,  Sean Robert Keith ,  Gulcharan Singh Brainch

IPC: F01D5/18 ,  F02C7/18

CPC classification number: F01D5/187 ,  F05D2240/81 ,  Y02T50/676

Abstract: A method facilitates fabricating a rotor assembly for a gas turbine engine. The method comprises providing a plurality of rotor blades that each include an airfoil, a dovetail, a shank, and a platform, wherein the platform extends between the shank and the airfoil, and wherein the dovetail extends outwardly from the shank, and forming a cooling circuit within a portion of the shank to supply cooling air to the rotor blade for supplying cooling air to the rotor blade for impingement cooling a portion of the rotor blade and for supplying cooling air to the rotor blade for purging a cavity defined downstream from the rotor blade.

Abstract translation: 一种方法有助于制造用于燃气涡轮发动机的转子组件。 该方法包括提供多个转子叶片，每个转子叶片包括翼型件，燕尾榫，柄和平台，其中平台在柄和翼型之间延伸，并且其中燕尾榫从柄部向外延伸，并形成冷却 在所述柄部的一部分内设置电路，以向所述转子叶片供应冷却空气，以向所述转子叶片供应冷却空气，用于冲击冷却所述转子叶片的一部分并用于向所述转子叶片供应冷却空气，用于向所述转子叶片 刀。

公开(公告)号：US06514037B1

公开(公告)日：2003-02-04

申请号：US09964040

申请日：2001-09-26

Applicant: Michael Joseph Danowski ,  Gulcharan Singh Brainch

Inventor： Michael Joseph Danowski ,  Gulcharan Singh Brainch

IPC: F01D518

CPC classification number: F01D5/187 ,  F01D5/186 ,  F05D2240/81 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2270/114

Abstract: A cooled turbine element including an airfoil and a flowpath boundary member extending laterally from either an inboard end or an outboard end of the airfoil. The member has a flowpath face and an outside face which is cooler than said flowpath face creating a tendency for the member to deflect in a direction away from the flowpath face and causing a thermally induced tensile radial stress in a region of the trailing edge of the airfoil. The element has an interior cooling passage and at least one cooling hole extending from the interior cooling passage to an opening located in an area upstream from the stressed region of the trailing edge to cool the area so the airfoil thermally deflects to a shape corresponding to that of the boundary member thereby lowering the thermally induced tensile radial stress in the airfoil at the trailing edge thereof.

Abstract translation: 一种冷却的涡轮机元件，包括翼型和从翼型的内侧端部或外侧端部横向延伸的流路边界构件。 该构件具有比所述流路面更冷的流路面和外面，从而形成该构件沿远离流路面的方向偏转的趋势，并且在该流路面的后缘区域中产生热诱导的拉伸径向应力 翼型。 该元件具有内部冷却通道和至少一个从内部冷却通道延伸到位于后缘的应力区域上游区域中的开口的冷却孔，以冷却该区域，使得翼型件热偏转到与之相对应的形状 的边缘部件，从而降低翼缘在其后缘处的热致拉伸径向应力。