发明名称 |
TURBINE BLADE PLATFORM WITH U-CHANNEL COOLING HOLES |
摘要 |
A turbine blade for a gas turbine engine includes an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending in a radial direction. The trailing edge is arranged on an aft side of the turbine blade. A root supports a platform from which the airfoil extends and a cooling passage extends within the root in the radial direction to the airfoil. A lower wing is arranged beneath the platform on the aft side and extends in an axial direction to provide a U-shaped channel with the platform that extends in a circumferential direction. An impingement hole extends from the U-channel to the cooling passage. |
申请公布号 |
US2014000282(A1) |
申请公布日期 |
2014.01.02 |
申请号 |
US201213537258 |
申请日期 |
2012.06.29 |
申请人 |
ZELESKY MARK F.;TRINDADE RICARDO;TELLER BRET M.;LEWIS SCOTT D.;BEATTIE JEFFREY S.;JACQUES JEFFREY MICHAEL;RAPP BRANDON M. |
发明人 |
ZELESKY MARK F.;TRINDADE RICARDO;TELLER BRET M.;LEWIS SCOTT D.;BEATTIE JEFFREY S.;JACQUES JEFFREY MICHAEL;RAPP BRANDON M. |
分类号 |
F01D5/18;F02C3/04;F02C7/18 |
主分类号 |
F01D5/18 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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