发明名称 |
Method and apparatus for reducing turbine blade tip temperatures |
摘要 |
<p>A rotor blade (40) for a gas turbine engine including a tip region (60) that facilitates reducing operating temperatures of the rotor blade is described. The tip region includes a first tip wall (62) and a second tip wall (64) extending radially outward from a tip plate (54) of an airfoil (42). The tip walls extend from adjacent a leading edge (48) of the airfoil to connect at a trailing edge (50) of the airfoil. A notch (80) is defined between the first and second tip walls at the airfoil leading edge. At least a portion of the second tip wall is recessed to define a tip shelf (90). <IMAGE></p> |
申请公布号 |
EP1221537(A2) |
申请公布日期 |
2002.07.10 |
申请号 |
EP20020250143 |
申请日期 |
2002.01.09 |
申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
LEE, CHING-PAN;SHELTON, MONTY LEE;PRAKASH, CHANDER;STARKWEATHER, JOHN HOWARD;SINGH, HARDEV;RINCK, GERARD ANTHONY |
分类号 |
F01D5/18;F01D5/20;(IPC1-7):F01D5/20 |
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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