公开(公告)号：US07377742B2

公开(公告)日：2008-05-27

申请号：US11250660

申请日：2005-10-14

申请人： Jason David Shapiro ,  Daniel Demers ,  Robert Patrick Tameo ,  Tyler F. Hooper ,  Robert Alexander Nicoll ,  Douglas Patrick Probasco

发明人： Jason David Shapiro ,  Daniel Demers ,  Robert Patrick Tameo ,  Tyler F. Hooper ,  Robert Alexander Nicoll ,  Douglas Patrick Probasco

IPC分类号： F01D25/26

CPC分类号： F01D11/24 ,  F01D11/08 ,  F05D2230/90 ,  F05D2240/11 ,  F05D2300/611

摘要： A method for assembling a gas turbine engine includes coupling a rotor assembly including a plurality of rotor blades about a rotatable main shaft of the gas turbine engine. The main shaft is aligned in an axial direction of the gas turbine engine. A shroud assembly is coupled to the gas turbine engine. The shroud assembly includes a plurality of shroud segments circumferentially coupled about the rotor assembly such that a shroud spacing gap is formed in the axial direction between adjacent shroud segments. A cooling fluid source is coupled to each shroud segment such that cooling fluid is channeled through each shroud segment into a corresponding shroud spacing gap to facilitate positive purge flow through the shroud spacing gap.

摘要翻译： 一种用于组装燃气涡轮发动机的方法包括将包括多个转子叶片的转子组件围绕燃气涡轮发动机的可旋转主轴联接。 主轴沿燃气轮机的轴向对准。 护罩组件联接到燃气涡轮发动机。 护罩组件包括围绕转子组件周向耦合的多个护罩段，使得在相邻护罩段之间沿轴向方向形成护罩间隔间隙。 冷却流体源联接到每个护罩段，使得冷却流体通过每个护罩段引导成相应的护罩间隔间隙，以促进穿过护罩间隔间隙的正净化流动。

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：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。