发明名称 |
GAS TURBINE ENGINE WITH GEARED ARCHITECTURE |
摘要 |
A gas turbine engine according to an exemplary aspect of the present disclosure includes a core nacelle defined about an engine centerline axis, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path for a fan bypass airflow, a fan variable area nozzle axially movable relative the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation, and a gear system driven by a core engine within the core nacelle to drive a fan within the fan nacelle, the gear system defines a gear reduction ratio of greater than or equal to about 2.3. |
申请公布号 |
CA2853694(A1) |
申请公布日期 |
2013.07.18 |
申请号 |
CA20132853694 |
申请日期 |
2013.01.03 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
SMITH, PETER G.;OCHS, STUART S.;SCHWARZ, FREDERICK M. |
分类号 |
F01D17/14 |
主分类号 |
F01D17/14 |
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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