| 发明名称 |
LOW NOISE COMPRESSOR AND TURBINE FOR GEARED TURBOFAN ENGINE |
| 摘要 |
A gas turbine engine according to an example of the present disclosure includes, among other things, a fan, a turbine section having a fan drive turbine rotor, and a compressor rotor. A gear reduction is configured to effect a reduction in a speed of the fan relative to an input speed from the fan drive turbine rotor. Each of the compressor rotor and the fan drive turbine rotor includes a number of blades in each of a plurality of blade rows. The number of blades are configured to operate at least some of the time at a rotational speed. |
| 申请公布号 |
US2016195021(A1) |
申请公布日期 |
2016.07.07 |
| 申请号 |
US201615014363 |
申请日期 |
2016.02.03 |
| 申请人 |
United Technologies Corporation |
发明人 |
Topol David A.;Morin Bruce L. |
| 分类号 |
F02C7/36;F02K3/06;F02C3/10 |
主分类号 |
F02C7/36 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine comprising:
a fan, a turbine section having a fan drive turbine rotor, and a compressor rotor; a gear reduction configured to effect a reduction in a speed of the fan relative to an input speed from the fan drive turbine rotor; and wherein each of the compressor rotor and the fan drive turbine rotor includes a number of blades in each of a plurality of blade rows, the number of blades configured to operate at least some of the time at a rotational speed, and the number of blades and the rotational speed being such that the following formula holds true for all of the blade rows of the fan drive turbine rotor, but does not hold true for any of the blade rows of the compressor rotor: (number of blades×rotational speed)/60 sec≧about 5500 Hz, and the rotational speed being an approach speed in revolutions per minute. |
| 地址 |
Farmington CT US |
