发明名称 |
Gas turbine engine with modulated flow turbine nozzle |
摘要 |
<p>A gas turbine engine includes a compressor powered by a turbine (24). The turbine (24) includes a nozzle (34) having vanes (42) extending between outer and inner bands (44,46). Each vane (42) includes an internal cooling plenum (48) and a bypass tube (50) extending through the bands (44,46). First and second manifolds (52,54) surround the outer band (44) and are disposed in flow communication with the plenums (48) and bypass tubes (50), respectively. A bleed circuit (56) joins the compressor (18) to the manifolds for providing pressurized air thereto. A control valve (58) modulates airflow to the first manifold (52) and in turn through the cooling plenums (48) of the vanes.
</p> |
申请公布号 |
EP1621734(A8) |
申请公布日期 |
2006.07.05 |
申请号 |
EP20050254173 |
申请日期 |
2005.07.04 |
申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
ORLANDO, ROBERT JOSEPH;BRAUER, JOHN CHRISTOPHER;KRAMMER, ERICH ALOIS;FREDERICK, ROBERT ALAN;MONIZ, THOMAS ORY;PRENTICE, IAN FRANCIS;DOLAN, JAMES PATRICK |
分类号 |
F01D9/06;F02C6/08 |
主分类号 |
F01D9/06 |
代理机构 |
|
代理人 |
|
主权项 |
|
地址 |
|