发明名称 |
Method and apparatus for cooling an airfoil |
摘要 |
An improved cooling design and method for cooling airfoils within a gas turbine engine is provided includes a plenum (80) longitudinally located within the leading edge (46) of the airfoils. Within the plenum (80) are positioned a plurality of turbulence promoters (86) to provide enhanced heat transfer within the leading edge. Also, the cooling design includes a plurality of inlets (72,76) to receive cooling air from an internal cavity (36) of the airfoil as well as a plurality of outlets (64,66) located within a trench (52) on the exterior surface of the leading edge (46) through which the cooling air exits to film cool the leading edge. |
申请公布号 |
EP1467064(A3) |
申请公布日期 |
2007.04.11 |
申请号 |
EP20040252040 |
申请日期 |
2004.04.06 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
CUNHA, FRANK J;PALUMBO, MICHAEL A |
分类号 |
F01D5/18 |
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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