| 发明名称 |
GEARED TURBOFAN ENGINE WITH HIGH COMPRESSOR EXIT TEMPERATURE |
| 摘要 |
A gas turbine engine comprises a fan includes a plurality of fan blades rotatable about an axis. A compressor section includes at least a first compressor section and a second compressor section, wherein components of the second compressor section are configured to operate at an average exit temperature that is between about 1000° F. and about 1500° F. A combustor is in fluid communication with the compressor section. A turbine section is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis. |
| 申请公布号 |
US2016076445(A1) |
申请公布日期 |
2016.03.17 |
| 申请号 |
US201514950393 |
申请日期 |
2015.11.24 |
| 申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
Schwarz Frederick M.;Hasel Karl L. |
| 分类号 |
F02C3/13;F02C3/06;F02C7/36;F02C3/10 |
主分类号 |
F02C3/13 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine comprising:
a fan including a plurality of fan blades rotatable about an axis; a compressor section including at least a first compressor section and a second compressor section, wherein components of the second compressor section are configured to operate at an average exit temperature that is between about 1000° F. and about 1500° F.; a combustor in fluid communication with the compressor section; a turbine section in fluid communication with the combustor; and a geared architecture driven by the turbine section for rotating the fan about the axis. |
| 地址 |
Hartford CT US |
