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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。
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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。
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