-
公开(公告)号：US07377746B2
公开(公告)日：2008-05-27
申请号：US11062001
申请日：2005-02-21
申请人： Steven Robert Brassfield , Ching-Pang Lee , Roger Lee Doughty , Richard William Jendrix , Cory Michael Williams
发明人： Steven Robert Brassfield , Ching-Pang Lee , Roger Lee Doughty , Richard William Jendrix , Cory Michael Williams
IPC分类号： F03D11/02
CPC分类号： F01D5/18 , B22C9/043 , F05D2230/21 , Y02T50/676 , Y10T29/49243 , Y10T29/49245
摘要： An airfoil is disclosed having at least first and second cast, axially-stacked internal airflow cooling circuits. Each circuit defines multiple air flow passages positioned laterally between a pressure sidewall side and a suction sidewall side of respective ones of the circuits. Each of the circuits is formed by a separate casting core. Methods of forming a axially-stacked core and an airfoil are also disclosed.
摘要翻译： 公开了一种具有至少第一和第二铸造，轴向堆叠的内部气流冷却回路的翼型件。 每个回路限定了多个气流通道，其横向位于各个电路的压力侧壁侧和吸力侧壁侧之间。 每个电路由单独的铸造芯形成。 还公开了形成轴向堆叠的芯和翼型的方法。
-
公开(公告)号：US20080080979A1
公开(公告)日：2008-04-03
申请号：US11062001
申请日：2005-02-21
申请人： Steven Robert Brassfield , Ching-Pang Lee , Roger Lee Doughty , Richard William Jendrix , Cory Michael Williams
发明人： Steven Robert Brassfield , Ching-Pang Lee , Roger Lee Doughty , Richard William Jendrix , Cory Michael Williams
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , B22C9/043 , F05D2230/21 , Y02T50/676 , Y10T29/49243 , Y10T29/49245
摘要： An airfoil is disclosed having at least first and second cast, axially-stacked internal airflow cooling circuits. Each circuit defines multiple air flow passages positioned laterally between a pressure sidewall side and a suction sidewall side of respective ones of the circuits. Each of the circuits is formed by a separate casting core. Methods of forming a axially-stacked core and an airfoil are also disclosed.
摘要翻译： 公开了一种具有至少第一和第二铸造，轴向堆叠的内部气流冷却回路的翼型件。 每个回路限定了多个气流通道，其横向位于各个电路的压力侧壁侧和吸力侧壁侧之间。 每个电路由单独的铸造芯形成。 还公开了形成轴向堆叠的芯和翼型的方法。
-
公开(公告)号：US09033652B2
公开(公告)日：2015-05-19
申请号：US13250345
申请日：2011-09-30
申请人： Steve Mark Molter , Steven Robert Brassfield , Richard William Jendrix , Cory Michael Williams , Renee Solomon Wenstrup , Mark Willard Marusko , Mark Edward Stegemiller
发明人： Steve Mark Molter , Steven Robert Brassfield , Richard William Jendrix , Cory Michael Williams , Renee Solomon Wenstrup , Mark Willard Marusko , Mark Edward Stegemiller
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/201 , F05D2260/202 , Y02T50/676 , Y10T29/49341
摘要： An airfoil for a gas turbine engine includes a first sidewall and a second sidewall coupled together at a leading edge and a trailing edge, such that a cavity is defined therebetween. A plurality of cooling circuits are defined within the cavity. Each cooling circuit channels cooling fluid through at least one cooling chamber to facilitate cooling the airfoil. More specifically, a cascade impingement circuit, a down pass circuit, a flag tip circuit, and a trailing edge circuit are provided. The cascade impingement circuit includes a central chamber and a plurality of impingement chambers.
摘要翻译： 用于燃气涡轮发动机的翼型件包括在前缘和后缘处联接在一起的第一侧壁和第二侧壁，使得在其间限定空腔。 多个冷却回路被限定在空腔内。 每个冷却回路使冷却流体通过至少一个冷却室，以便冷却翼型件。 更具体地，提供了级联冲击电路，降压电路，标记尖端电路和后沿电路。 级联冲击电路包括中央室和多个冲击室。
-
公开(公告)号：US20130081408A1
公开(公告)日：2013-04-04
申请号：US13250345
申请日：2011-09-30
申请人： Steve Mark Molter , Steven Robert Brassfield , Richard William Jendrix , Cory Michael Williams , Renee Solomon Wenstrup , Mark Willard Marusko , Mark Edward Stegemiller
发明人： Steve Mark Molter , Steven Robert Brassfield , Richard William Jendrix , Cory Michael Williams , Renee Solomon Wenstrup , Mark Willard Marusko , Mark Edward Stegemiller
CPC分类号： F01D5/187 , F05D2260/201 , F05D2260/202 , Y02T50/676 , Y10T29/49341
摘要： An airfoil for a gas turbine engine includes a first sidewall and a second sidewall coupled together at a leading edge and a trailing edge, such that a cavity is defined therebetween. A plurality of cooling circuits are defined within the cavity. Each cooling circuit channels cooling fluid through at least one cooling chamber to facilitate cooling the airfoil. More specifically, a cascade impingement circuit, a down pass circuit, a flag tip circuit, and a trailing edge circuit are provided. The cascade impingement circuit includes a central chamber and a plurality of impingement chambers.
摘要翻译： 用于燃气涡轮发动机的翼型件包括在前缘和后缘处联接在一起的第一侧壁和第二侧壁，使得在其间限定空腔。 多个冷却回路被限定在空腔内。 每个冷却回路使冷却流体通过至少一个冷却室，以便冷却翼型件。 更具体地，提供了级联冲击电路，降压电路，标记尖端电路和后沿电路。 级联冲击电路包括中央室和多个冲击室。
-
公开(公告)号：US07322797B2
公开(公告)日：2008-01-29
申请号：US11296910
申请日：2005-12-08
IPC分类号： F01D5/26
CPC分类号： F01D5/22 , F01D11/006 , F05D2240/81 , F05D2250/292 , F05D2250/314 , Y02T50/671 , Y02T50/676 , Y10S416/50
摘要： A turbine blade includes an airfoil, platform, shank, and dovetail integrally joined together. A cooling chamber is located under the platform and has a portal exposed outwardly from the shank. A damper seat surrounds the portal and is recessed under the platform for receiving a vibration damper to sealingly close the chamber across the portal.
摘要翻译： 涡轮机叶片包括整体连接在一起的翼型件，平台，柄和燕尾榫。 冷却室位于平台下方并具有从柄部向外露出的入口。 阻尼器座圈围绕入口并且凹陷在平台下方，用于接收振动阻尼器以密封地封闭穿过入口的腔室。
-
公开(公告)号：US06984103B2
公开(公告)日：2006-01-10
申请号：US10718465
申请日：2003-11-20
IPC分类号： F03D11/00
CPC分类号： F01D5/187 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes an airfoil having pressure and suction sidewalls extending between leading and trailing edges, and from root to tip. A dovetail is joined to the airfoil root at a platform. Three internal cooling circuits extend in span inside the airfoil, and each circuit includes a respective inlet channel commencing in axially adjacent alignment in the dovetail. The inlet channels twist together from the dovetail, through the platform, and into the airfoil behind the leading edge in transverse adjacent alignment across the sidewalls.
摘要翻译： 涡轮叶片包括具有在前缘和后缘之间延伸的压力和吸力侧壁以及从根部到尖端的翼型件。 燕尾榫在平台上连接到翼型根部。 三个内部冷却回路在翼型内部的跨度上延伸，并且每个回路包括相应的入口通道，其从燕尾榫开始轴向相邻对准。 入口通道从燕尾榫通过平台扭转在一起，并且横跨相邻的侧壁横向相邻对齐，并进入前缘的后翼。
-
公开(公告)号：US07674093B2
公开(公告)日：2010-03-09
申请号：US11641286
申请日：2006-12-19
CPC分类号： B22C9/103 , F01D5/187 , F05D2230/211 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A casting core for a turbine blade includes a plurality of rods extending above a shank. The rods define internal cooling channels in the airfoil of the blade, and the shank defines an inlet channel in the dovetail of the blade. A plurality of stubs are clustered together at a bulb joined to the shank and radiate outwardly to integrally join different ones of the rods for increasing strength of the core.
摘要翻译： 用于涡轮叶片的铸芯包括在柄上方延伸的多个杆。 杆在叶片的翼型中限定内部冷却通道，并且杆在叶片的燕尾形中限定入口通道。 多个短棒在连接到柄的灯泡上聚集在一起并向外辐射以一体地连接不同的杆，以增加芯的强度。
-
公开(公告)号：US07328580B2
公开(公告)日：2008-02-12
申请号：US10874900
申请日：2004-06-23
IPC分类号： F23R3/42
CPC分类号： B23K26/384
摘要： A wall in a gas turbine engine includes inner and outer surfaces having a row of compound chevron film cooling holes extending therethrough. The chevron holes diverge both longitudinally and laterally between an inlet at the wall inner surface and a chevron outlet at the wall outer surface.
摘要翻译： 燃气涡轮发动机中的壁包括内表面和外表面，其具有穿过其延伸的一排复合人字形薄膜冷却孔。 人字形孔在壁内表面的入口和壁外表面的人字形出口之间纵向和横向分开。
-
公开(公告)号：US07217092B2
公开(公告)日：2007-05-15
申请号：US10824283
申请日：2004-04-14
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , Y02T50/676
摘要： An airfoil for a gas turbine engine includes a first sidewall and a second sidewall coupled together at a leading edge and a trailing edge, such that a cavity is defined therebetween. A plurality of rib walls extend at least partially between the first and second sidewalls, wherein the plurality of rib walls define at least one cooling circuit having at least three cooling chambers. At least one row of openings extend through at least one of the rib walls, wherein a first of the cooling chambers supplies cooling fluid to the cavity, and the remaining cooling chambers are coupled in flow communication with the first cooling chamber via the openings.
摘要翻译： 用于燃气涡轮发动机的翼型件包括在前缘和后缘处联接在一起的第一侧壁和第二侧壁，使得在其间限定空腔。 多个肋壁至少部分地在第一和第二侧壁之间延伸，其中多个肋壁限定至少一个具有至少三个冷却室的冷却回路。 至少一排开口延伸穿过所述肋壁中的至少一个，其中第一冷却室将冷却流体供应到空腔，并且剩余的冷却室经由所述开口与第一冷却室流体连通地联接。
-
公开(公告)号：US07503749B2
公开(公告)日：2009-03-17
申请号：US11097474
申请日：2005-04-01
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2250/13 , F05D2250/184 , F05D2250/292 , F05D2260/221 , Y02T50/673 , Y02T50/676
摘要： An airfoil for a gas turbine engine has opposed pressure and suction sidewalls extending between a leading edge and a trailing edge. The airfoil includes an array of radially-spaced apart longitudinally-extending lands which define a plurality of trailing edge slots therebetween. Each of the trailing edge slots has an inlet in fluid communication with an interior of the airfoil and an exit in fluid communication with the trailing edge. At least one of the lands is tapered such that a width of the land measured in a radial direction decreases from the suction sidewall to the pressure sidewall.
摘要翻译： 用于燃气涡轮发动机的翼型件具有在前缘和后缘之间延伸的相对的压力和吸力侧壁。 翼型件包括在其间限定多个后缘槽的径向间隔开的纵向延伸的平台的阵列。 每个后缘槽具有与翼型件的内部流体连通的入口和与后缘流体连通的出口。 至少一个焊盘是锥形的，使得沿径向测量的焊盘的宽度从抽吸侧壁减小到压力侧壁。
-
-
-
-
-
-
-
-
-
搜索结果
22 条记录 (耗时 0.029 秒)