| 发明名称 |
TURBINE ENGINE ADVANCED COOLING SYSTEM |
| 摘要 |
A cooling system for a gas turbine is provided that may include a drive shaft, a shield of a combustor of the gas turbine engine, and a conduit. The drive shaft may be configured to mechanically couple a compressor of the gas turbine engine to a turbine of the gas turbine engine. The shield may be positioned between the compressor and the turbine. The combustor may be configured to drive the turbine. The conduit may be configured to supply a cooling fluid to a gap between an outer surface of the drive shaft and the shield of the combustor. |
| 申请公布号 |
US2017089263(A1) |
申请公布日期 |
2017.03.30 |
| 申请号 |
US201514871382 |
申请日期 |
2015.09.30 |
| 申请人 |
Rolls-Royce Corporation ;Rolls-Royce North American Technologies Inc. |
发明人 |
Clegg Joseph;English Craig;Kapadia Behram;Pesyna Kenneth M.;Swindle Jason Lee;Rector Jason Wayne;Vincent Christopher;Metzger Nicholas D.;Edwards Daniel G. |
| 分类号 |
F02C7/12;F02C7/24;F04D29/58;F01D25/12;F04D29/32;F02C3/04;F01D5/02 |
主分类号 |
F02C7/12 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A cooling system comprising:
a drive shaft configured to mechanically couple a compressor of a gas turbine engine to a turbine of the gas turbine engine; a shield of a combustor of the gas turbine engine, the shield positioned between the compressor and the turbine, the combustor configured to drive the turbine with a stream of gas; and a conduit configured to supply a cooling fluid to a gap between an outer surface of the drive shaft and the shield of the combustor. |
| 地址 |
Indianapolis IN US |
