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1. 发明授权

US06652235B1 Method and apparatus for reducing turbine blade tip region temperatures 失效
标题翻译：降低涡轮叶片尖端区域温度的方法和装置
公开(公告)号：US06652235B1
公开(公告)日：2003-11-25
申请号：US10160527
申请日：2002-05-31
申请人： Sean Robert Keith , Thomas Edward DeMarche , John Robert Staker , Judd Dodge Tressler
发明人： Sean Robert Keith , Thomas Edward DeMarche , John Robert Staker , Judd Dodge Tressler
IPC分类号： F01D518
CPC分类号： F01D5/187 , F01D5/141 , F01D5/20 , F05D2260/202 , Y02T50/673 , Y02T50/676 , Y10T29/49341
摘要： A method for fabricating a rotor blade for a gas turbine engine facilitates reducing operating temperatures of a tip portion of the rotor blade. The method comprises forming an airfoil including a first sidewall and a second sidewall connected at a leading edge and a trailing edge to define a cavity therein, wherein the first and second sidewalls extend radially between a rotor blade root and a rotor blade tip plate, and forming a first tip wall extending from the rotor blade tip plate along the first sidewall, such that at least a portion of the first tip wall is at least partially recessed with respect to the rotor blade first sidewall to define a tip shelf that extends from the airfoil trailing edge towards the airfoil leading edge. A second tip wall is formed to extend from the rotor blade tip plate along the second sidewall.
摘要翻译：一种用于制造用于燃气涡轮发动机的转子叶片的方法有助于降低转子叶片的尖端部分的操作温度。该方法包括形成包括第一侧壁和第二侧壁的翼型件，第一侧壁和第二侧壁连接在前缘和后缘以在其中限定空腔，其中第一和第二侧壁在转子叶片根部和转子叶片顶板之间径向延伸，以及形成从所述转子叶片尖端板沿着所述第一侧壁延伸的第一末端壁，使得所述第一末端壁的至少一部分相对于所述转子叶片第一侧壁至少部分地凹入以限定从所述第一侧壁延伸的尖端架机翼后缘朝向翼型前缘。第二顶端壁形成为沿着第二侧壁从转子叶片顶板延伸。

2. 发明授权

US06779597B2 Multiple impingement cooled structure 有权
标题翻译：多冲击冷却结构
公开(公告)号：US06779597B2
公开(公告)日：2004-08-24
申请号：US10053534
申请日：2002-01-16
申请人： Thomas Edward DeMarche , Robert Francis Manning
发明人： Thomas Edward DeMarche , Robert Francis Manning
IPC分类号： F28F312
CPC分类号： F28F13/02 , F01D11/24 , F01D25/12 , F05D2260/201 , F28F3/022 , Y10S165/908
摘要： A multiple impingement cooled structure is provided having two or more stages of impingement cooling wherein the stages are arranged so as to have substantially constant cooling effectiveness.
摘要翻译：提供多冲击冷却结构，其具有两级或更多级的冲击冷却，其中级被布置成具有基本恒定的冷却效果。

3. 发明授权

US06746209B2 Methods and apparatus for cooling gas turbine engine nozzle assemblies 有权
标题翻译：用于冷却燃气涡轮发动机喷嘴组件的方法和装置
公开(公告)号：US06746209B2
公开(公告)日：2004-06-08
申请号：US10160548
申请日：2002-05-31
申请人： Thomas Edward DeMarche , Robert Francis Manning
发明人： Thomas Edward DeMarche , Robert Francis Manning
IPC分类号： F01D906
CPC分类号： F01D5/187 , Y02T50/676
摘要： A method for fabricating a nozzle for a gas turbine engine facilitates extending a useful life of the nozzles. The nozzle includes an airfoil. The method includes forming the airfoil to include a suction side and a pressure side connected at a leading edge and a trailing edge such that a cooling cavity and a cooling circuit are defined within the airfoil, wherein the suction side and the pressure side extend radially between a tip and a root. The method also includes forming a plurality of cooling slots within the airfoil that extend from the cooling circuit towards the airfoil trailing edge, and forming a control vane within the cooling circuit to facilitate maintaining a substantially constant cooling effectiveness within the cooling circuit.
摘要翻译：一种用于制造用于燃气涡轮发动机的喷嘴的方法有助于延长喷嘴的使用寿命。喷嘴包括翼型件。该方法包括形成翼型件，包括吸入侧和连接在前缘和后缘处的压力侧，使得在翼型件内限定冷却腔和冷却回路，其中吸入侧和压力侧之间径向延伸一个提示和根。该方法还包括在翼型件内形成从冷却回路向翼型后缘延伸的多个冷却槽，以及在冷却回路内形成控制叶片，以便于在冷却回路内保持基本恒定的冷却效果。

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