| 发明名称 |
LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE |
| 摘要 |
A gas turbine engine assembly according to an example of the present disclosure includes, among other things, a fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, a geared architecture configured to drive the fan, a turbine section configured to drive the geared architecture, a compressor section including a first compressor and a second compressor, and an inlet portion forward of the fan. A length of the inlet portion has a dimension L between a location of the leading edge of at least some of the fan blades and a forward edge on the inlet portion. A dimensional relationship of L/D is between about 0.2 and about 0.45. |
| 申请公布号 |
US2016108854(A1) |
申请公布日期 |
2016.04.21 |
| 申请号 |
US201514882760 |
申请日期 |
2015.10.14 |
| 申请人 |
United Technologies Corporation |
发明人 |
Lord Wesley K.;Malecki Robert E.;Qiu Yuan J.;Rose Becky E.;Gilson Jonathan |
| 分类号 |
F02K3/06;F04D19/02;F01D15/12;F01D17/10;F01D5/02;F01D5/12 |
主分类号 |
F02K3/06 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine assembly, comprising:
a fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge; a geared architecture configured to drive the fan; a turbine section configured to drive the geared architecture; a compressor section including a first compressor and a second compressor, the first compressor including fewer stages than the second compressor; and an inlet portion forward of the fan, a length of the inlet portion having a dimension L between a location of the leading edge of at least some of the fan blades and a forward edge on the inlet portion, wherein a dimensional relationship of L/D is between about 0.2 and about 0.45. |
| 地址 |
Hartford CT US |
