公开(公告)号：US06558121B2

公开(公告)日：2003-05-06

申请号：US09942299

申请日：2001-08-29

申请人： Gaoqiu Zhu ,  Mark Douglas Gledhill ,  Douglas Bryan Ballantyne

发明人： Gaoqiu Zhu ,  Mark Douglas Gledhill ,  Douglas Bryan Ballantyne

IPC分类号： F01D514

CPC分类号： F01D5/143 ,  Y10T29/49336

摘要： A turbine blade assembly for a gas turbine engine that includes a turbine platform including contoured edges. The turbine blade assembly includes a platform, a turbine airfoil extending radially outward from the platform, a shank that extends radially inward from the platform, and a dovetail extending from the shank. The platform includes a leading edge and a trailing edge separated by a pressure edge and an opposite suction edge, the pressure edge including a plurality of arcs extending between the leading edge and the trailing edge, the suction edge including a plurality of arcs extending between the leading and trailing edges.

摘要翻译： 一种用于燃气涡轮发动机的涡轮机叶片组件，其包括具有轮廓边缘的涡轮平台。 涡轮叶片组件包括平台，从平台径向向外延伸的涡轮机翼型件，从该平台径向向内延伸的柄部以及从该柄部延伸的燕尾榫。 平台包括由压力边缘和相对的吸力边缘分开的前缘和后缘，压力边缘包括在前缘和后缘之间延伸的多个弧，吸力边缘包括在 前缘和后缘。

公开(公告)号：US20070140851A1

公开(公告)日：2007-06-21

申请号：US11314756

申请日：2005-12-21

申请人： Tyler Hooper ,  Bhanu Reddy ,  Gaoqiu Zhu ,  Robert Manning

发明人： Tyler Hooper ,  Bhanu Reddy ,  Gaoqiu Zhu ,  Robert Manning

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F01D5/20 ,  F05D2250/185 ,  F05D2250/314 ,  F05D2260/202

摘要： Methods and apparatus for cooling gas turbine rotor blades is provided. The rotor blades include an airfoil having a pressure sidewall and a second suction sidewall connected together at a leading edge and a trailing edge, such that an internal three pass serpentine cooling circuit is formed therebetween. The cooling circuit includes radially extending first, second, and third serpentine cooling cavities partially separated by, in axially aft succession, a first radially extending internal rib and a second internal rib. The second rib includes a radially inner first portion and a radially outer portion wherein the radially outer portion is angled obliquely with respect to the first portion.

摘要翻译： 提供了用于冷却燃气轮机转子叶片的方法和装置。 转子叶片包括具有压力侧壁的翼型和在前缘和后缘连接在一起的第二吸力侧壁，使得在它们之间形成内部三通蛇形冷却回路。 冷却回路包括径向延伸的第一，第二和第三蛇形冷却空腔，其部分地沿轴向后隔开间隔开第一径向延伸的内肋和第二内肋。 第二肋包括径向内部第一部分和径向外部部分，其中径向外部部分相对于第一部分倾斜成角度。

公开(公告)号：US07431561B2

公开(公告)日：2008-10-07

申请号：US11356388

申请日：2006-02-16

申请人： Tyler F. Hooper ,  Bhanu Reddy ,  Gaoqiu Zhu ,  Richard William Albrecht, Jr.

发明人： Tyler F. Hooper ,  Bhanu Reddy ,  Gaoqiu Zhu ,  Richard William Albrecht, Jr.

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F05D2230/21 ,  F05D2240/126 ,  F05D2250/185

摘要： Methods and apparatus for cooling gas turbine rotor blades is provided. The blade includes an airfoil having an internal three pass serpentine cooling circuit having radially extending first, second, and third serpentine cooling cavities partially separated by, in axially aft succession, a first radially extending internal rib and a second radially extending internal rib. The serpentine cooling circuit includes a first inlet in flow communication with the first cavity and a second inlet in flow communication with at least one of the second and third cavities wherein the first and second inlets are formed during casting of the airfoil.

摘要翻译： 提供了用于冷却燃气轮机转子叶片的方法和装置。 叶片包括具有内部三通蛇形冷却回路的翼型件，其具有径向延伸的第一，第二和第三蛇形冷却空腔，所述径向延伸的第一，第二和第三蛇形冷却腔沿轴向向后连续地分开第一径向延伸的内肋和第二径向延伸的内肋。 蛇形冷却回路包括与第一腔体流动连通的第一入口和与第二和第三腔室中的至少一个流体连通的第二入口，其中在铸造翼型件期间形成第一和第二入口。

公开(公告)号：US07431562B2

公开(公告)日：2008-10-07

申请号：US11314756

申请日：2005-12-21

申请人： Tyler F. Hooper ,  Bhanu Reddy ,  Gaoqiu Zhu ,  Robert F. Manning

发明人： Tyler F. Hooper ,  Bhanu Reddy ,  Gaoqiu Zhu ,  Robert F. Manning

IPC分类号： F01D5/08

CPC分类号： F01D5/187 ,  F01D5/20 ,  F05D2250/185 ,  F05D2250/314 ,  F05D2260/202

摘要： Methods and apparatus for cooling gas turbine rotor blades is provided. The rotor blades include an airfoil having a pressure sidewall and a second suction sidewall connected together at a leading edge and a trailing edge, such that an internal three pass serpentine cooling circuit is formed therebetween. The cooling circuit includes radially extending first, second, and third serpentine cooling cavities partially separated by, in axially aft succession, a first radially extending internal rib and a second internal rib. The second rib includes a radially inner first portion and a radially outer portion wherein the radially outer portion is angled obliquely with respect to the first portion.

摘要翻译： 提供了用于冷却燃气轮机转子叶片的方法和装置。 转子叶片包括具有压力侧壁的翼型和在前缘和后缘连接在一起的第二吸力侧壁，使得在它们之间形成内部三通蛇形冷却回路。 冷却回路包括径向延伸的第一，第二和第三蛇形冷却空腔，其部分地沿轴向后隔开间隔开第一径向延伸的内肋和第二内肋。 第二肋包括径向内部第一部分和径向外部部分，其中径向外部部分相对于第一部分倾斜成角度。

公开(公告)号：US20070189898A1

公开(公告)日：2007-08-16

申请号：US11356388

申请日：2006-02-16

申请人： Tyler Hooper ,  Bhanu Reddy ,  Gaoqiu Zhu ,  Richard Albrecht

发明人： Tyler Hooper ,  Bhanu Reddy ,  Gaoqiu Zhu ,  Richard Albrecht

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F05D2230/21 ,  F05D2240/126 ,  F05D2250/185

摘要： Methods and apparatus for cooling gas turbine rotor blades is provided. The blade includes an airfoil having an internal three pass serpentine cooling circuit having radially extending first, second, and third serpentine cooling cavities partially separated by, in axially aft succession, a first radially extending internal rib and a second radially extending internal rib. The serpentine cooling circuit includes a first inlet in flow communication with the first cavity and a second inlet in flow communication with at least one of the second and third cavities wherein the first and second inlets are formed during casting of the airfoil.

摘要翻译： 提供了用于冷却燃气轮机转子叶片的方法和装置。 叶片包括具有内部三通蛇形冷却回路的翼型件，其具有径向延伸的第一，第二和第三蛇形冷却空腔，所述径向延伸的第一，第二和第三蛇形冷却腔沿轴向向后连续地分开第一径向延伸的内肋和第二径向延伸的内肋。 蛇形冷却回路包括与第一腔体流动连通的第一入口和与第二和第三腔室中的至少一个流体连通的第二入口，其中在铸造翼型件期间形成第一和第二入口。