发明名称 |
METHOD AND APPARATUS FOR COOLING GAS TURBINE ROTOR BLADES |
摘要 |
<p>An airfoil for a gas turbine engine includes a first sidewall and a second sidewall coupled together at a leading edge and a trailing edge, such that a cavity is defined therebetween. A plurality of cooling circuits are defined within the cavity. Each cooling circuit channels cooling fluid through at least one cooling chamber to facilitate cooling the airfoil. More specifically, a cascade impingement circuit, a down pass circuit, a flag tip circuit, and a trailing edge circuit are provided. The cascade impingement circuit includes a central chamber and a plurality of impingement chambers.</p> |
申请公布号 |
CA2848867(A1) |
申请公布日期 |
2013.04.04 |
申请号 |
CA20122848867 |
申请日期 |
2012.09.11 |
申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
MOLTER, STEVE MARK;BRASSFIELD, STEVEN ROBERT;JENDRIX, RICHARD WILLIAM;WILLIAMS, CORY MICHAEL;WENSTRUP, RENEE SOLOMON;MARUSKO, MARK WILLARD;STEGEMILLER, MARK EDWARD |
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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