| 发明名称 |
GAS TURBINE ENGINE WITH DISTRIBUTED FANS DRIVEN ON ANGLED DRIVE SHAFT |
| 摘要 |
A gas turbine engine includes a gas generator that has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of the at least one gas generator turbine rotor. The fan drive turbine drives a driveshaft and the driveshaft engages gears to drive at least three fan rotors. The driveshaft extends away from the gas generator such that at least one of the fan rotors that is positioned remotely from the fan drive turbine on the driveshaft is spaced to be either more forward or more rearward of the fan drive turbine relative to at least one of the fan rotors positioned closer to the fan drive turbine. An aircraft is also disclosed. |
| 申请公布号 |
US2015360787(A1) |
申请公布日期 |
2015.12.17 |
| 申请号 |
US201514600235 |
申请日期 |
2015.01.20 |
| 申请人 |
United Technologies Corporation |
发明人 |
Chandler Jesse M.;Suciu Gabriel L. |
| 分类号 |
B64D27/12;B64D35/02;B64C3/00;F02C3/10;F02C7/36 |
主分类号 |
B64D27/12 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine comprising:
a gas generator with at least one compressor rotor, at least one gas generator turbine rotor and a combustion section; a fan drive turbine positioned downstream of said at least one gas generator turbine rotor, said fan drive turbine for driving a driveshaft and said driveshaft engaging gears to drive at least three fan rotors; and said driveshaft extending away from the gas generator such that at least one of said fan rotors that is positioned remotely from said fan drive turbine on said driveshaft is spaced to be either more forward or more rearward of the fan drive turbine relative to at least one of said fan rotors positioned closer to said fan drive turbine. |
| 地址 |
Hartford CT US |
