发明名称 |
Turbine airfoil and methods for airfoil cooling |
摘要 |
A turbine engine airfoil includes a three-pass serpentine shaped cooling cavity including a leading edge chamber, an oversized intermediate chamber, and a trailing edge chamber in flow communication. The cavity further includes a combination of a plurality of ribs and a plurality of pins, a purge air swirler, a turning vane, and a metering partition which mixes the high pressure air and provides increased air cooling and uniform flow control in the airfoil. The metering partition provides a decrease of the air pressure in the trailing edge chamber allowing for an increase in the number of trailing edge slots.
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申请公布号 |
US6132169(A) |
申请公布日期 |
2000.10.17 |
申请号 |
US19980215858 |
申请日期 |
1998.12.18 |
申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
MANNING, ROBERT F.;SOLDA, ROBERT B.;PAREKH, LALIT K.;TASLIM, MOHAMMAD E. |
分类号 |
F01D9/02;F01D5/18;(IPC1-7):F01D5/14 |
主分类号 |
F01D9/02 |
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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