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 is defined between an inner nacelle surrounding the core engine section and an outer nacelle and includes a secondary nozzle. The secondary nozzle 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 |
EP2900980(A4) |
申请公布日期 |
2016.05.25 |
申请号 |
EP20130867624 |
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 |
F02C9/16;F01D21/04;F02C3/04;F02C7/20;F02C7/32;F02K1/04;F02K3/06;F02K3/075 |
主分类号 |
F02C9/16 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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