发明名称 |
COMPRESSOR AREA SPLITS FOR GEARED TURBOFAN |
摘要 |
A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section including a fan rotor. The fan rotor includes a fan hub defining a first diameter at a leading edge of a fan blade. The fan blade defines a tip diameter at the leading edge, with a ratio of the fan hub diameter to the fan tip diameter being less than or equal to 0.40. A compressor section includes a low pressure compressor and a high pressure compressor. A turbine section includes a fan drive turbine and a high pressure turbine. The fan drive turbine is configured to drive the fan section, and the high pressure turbine is configured to drive the high pressure compressor. |
申请公布号 |
US2016215730(A1) |
申请公布日期 |
2016.07.28 |
申请号 |
US201615062514 |
申请日期 |
2016.03.07 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
Schwarz Frederick M.;Spiesman Paul H. |
分类号 |
F02K3/06;F01D5/14;F02C3/10 |
主分类号 |
F02K3/06 |
代理机构 |
|
代理人 |
|
主权项 |
1. A gas turbine engine comprising:
a fan section including a fan rotor, the fan rotor including a fan hub defining a first diameter at a leading edge of a fan blade, the fan blade defining a tip diameter at the leading edge, with a ratio of the fan hub diameter to the fan tip diameter being less than or equal to 0.40; a compressor section including a low pressure compressor and a high pressure compressor, the high pressure compressor including eight stages; a turbine section including a fan drive turbine and a high pressure turbine, the fan drive turbine configured to drive the fan section, and the high pressure turbine configured to drive the high pressure compressor; and wherein the fan section is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct, and a bypass ratio, which is defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section, being greater than about 10. |
地址 |
Hartford CT US |