发明名称 |
GAS TURBINE ENGINE AIRFOIL HAVING BUILT-UP SURFACE WITH EMBEDDED COOLING PASSAGE |
摘要 |
A component in a gas turbine engine includes an airfoil extending radially outwardly from a platform associated with the airfoil. The airfoil includes opposed pressure and suction sidewalls, which converge at a first location defined at a leading edge of the airfoil and at a second location defined at a trailing edge of the airfoil opposed from the leading edge. The component includes a built-up surface adjacent to the leading edge at an intersection between the pressure sidewall and the platform, and at least one cooling passage at least partially within the built-up surface at the intersection between the pressure sidewall and the platform. The at least one cooling passage is in fluid communication with a main cooling channel within the airfoil and has an outlet at the platform for providing cooling fluid directly from the main cooling channel to the platform. |
申请公布号 |
EP2547487(A1) |
申请公布日期 |
2013.01.23 |
申请号 |
EP20110708130 |
申请日期 |
2011.02.23 |
申请人 |
SIEMENS ENERGY, INC. |
发明人 |
LEE, CHING-PANG;MUNSHI, MRINAL;AZAD, GM, S.;UM, JAE, Y. |
分类号 |
B23P6/00;F01D5/00;F01D5/14;F01D5/18 |
主分类号 |
B23P6/00 |
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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