发明名称 |
GEARED TURBOFAN PRIMARY AND SECONDARY NOZZLE INTEGRATION GEOMETRY |
摘要 |
A disclosed example geared turbofan engine includes a fan section including a plurality of fan blades rotatable about an axis and a core engine section defined about an engine axis. The core engine section includes a primary nozzle including a primary outer diameter at a primary nozzle trailing edge and a primary maximum inner diameter forward of the primary trailing edge. A bypass passage a secondary nozzle that includes an outer diameter at a secondary nozzle trailing edge and a secondary maximum inner diameter forward of the secondary trailing edge. A ratio between the maximum inner diameter of the primary nozzle and an outer diameter at the trailing edge of the primary nozzle and a ratio between the maximum inner diameter of the secondary trailing edge and the outer diameter at the trailing edge of the secondary nozzle are both less than about 0.700. |
申请公布号 |
WO2014105237(A2) |
申请公布日期 |
2014.07.03 |
申请号 |
WO2013US61927 |
申请日期 |
2013.09.26 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
KUPRATIS, DANIEL BERNARD;KOHLENBERG, GREGORY A. |
分类号 |
|
主分类号 |
|
代理机构 |
|
代理人 |
|
主权项 |
|
地址 |
|