发明名称 |
Method and arrangement for providing a gas turbine, and engine-braking therefore |
摘要 |
Method and arrangement for providing a gas turbine ( 1 ) having a first compressor ( 2 ), a combustion chamber ( 16 ) and a first turbine ( 11 ), the turbine being adapted to drive the compressor via a first shaft ( 10 a, 10 b). The gas turbine also has a bleed valve ( 12 ) arranged upstream of the first turbine for conducting part of a gas compressed by the compressor past it during engine braking. The invention also relates to a method for engine-braking a gas turbine.
|
申请公布号 |
US6883331(B2) |
申请公布日期 |
2005.04.26 |
申请号 |
US20030605531 |
申请日期 |
2003.10.06 |
申请人 |
VOLVO AERO CORPORATION |
发明人 |
JOENSSON BERTIL;SUNDIN LARS |
分类号 |
F01D15/02;F01D21/00;F02C3/10;F02C6/00;F02C6/20;F02C7/08;F02C7/36;F02C9/18;F02C9/22;F02C9/28;(IPC1-7):F02C6/08 |
主分类号 |
F01D15/02 |
代理机构 |
|
代理人 |
|
主权项 |
|
地址 |
|