发明名称 |
INTERCOOLED COOLING AIR WITH AUXILIARY COMPRESSOR CONTROL |
摘要 |
A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passing the tapped air through a heat exchanger and then to a cooling compressor, which compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. The cooling compressor rotates at a speed proportional to a speed of at least one rotor in the turbine section. The cooling compressor is allowed to rotate at a speed that is not proportional to a speed of the at least one rotor under certain conditions. An intercooling system for a gas turbine engine is also disclosed. |
申请公布号 |
US2016237907(A1) |
申请公布日期 |
2016.08.18 |
申请号 |
US201514745550 |
申请日期 |
2015.06.22 |
申请人 |
United Technologies Corporation |
发明人 |
Merry Brian D.;Suciu Gabriel L.;Chandler Jesse M.;Staubach Joseph Brent;Roberge Gary D. |
分类号 |
F02C7/18;F02C3/04 |
主分类号 |
F02C7/18 |
代理机构 |
|
代理人 |
|
主权项 |
1. A gas turbine engine comprising;
a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations; a turbine section having a high pressure turbine; a tap tapping air from at least one of said more upstream locations in said compressor section, passing said tapped air through a heat exchanger and then to a cooling compressor, said cooling compressor compressing air downstream of said heat exchanger, and delivering air into said high pressure turbine; and said cooling compressor rotating at a speed proportional to a speed of at least one rotor in said turbine section, and said cooling compressor being allowed to rotate at a speed that is not proportional to a speed of said at least one rotor under certain conditions. |
地址 |
Hartford CT US |