发明名称 |
Thrust efficient turbofan engine |
摘要 |
A turbofan engine includes a gas generator section for generating a gas stream flow with higher energy per unit mass flow than that contained in the ambient air and a power turbine that converts the gas stream flow into shaft power. The turbofan engine further includes a propulsor section including a fan driven by the power turbine through a geared architecture at a second speed lower than the first speed for generating propulsive thrust as a mass flow rate of air through a bypass flow path. An Engine Unit Thrust Parameter defined as net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, a tip diameter of the fan and the first rotational speed of the power turbine is less than about 0.15 at a take-off condition. |
申请公布号 |
US9624827(B2) |
申请公布日期 |
2017.04.18 |
申请号 |
US201313854225 |
申请日期 |
2013.04.01 |
申请人 |
United Technologies Corporation |
发明人 |
Sabnis Jayant |
分类号 |
F02C3/04;F02K1/52;F02K3/06;F02C3/08;F02C6/02;F02C7/36 |
主分类号 |
F02C3/04 |
代理机构 |
Carlson, Gaskey & Olds, P.C. |
代理人 |
Carlson, Gaskey & Olds, P.C. |
主权项 |
1. A turbofan engine comprising:
a gas generator section for generating a gas stream flow with higher energy per unit mass flow than that contained in ambient air; a power turbine converting the gas stream flow into shaft power, the power turbine rotating at a first rotational speed; a speed reduction device driven by the power turbine; and a propulsor section including a fan driven by the power turbine through the speed reduction device at a second speed lower than the first speed for generating propulsive thrust as a mass flow rate of air through a bypass flow path, wherein an Engine Unit Thrust Parameter (“EUTP”) defined as net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, a tip diameter of the fan and the first rotational speed of the power turbine is less than about 0.15 at a take-off condition. |
地址 |
Farmington CT US |