发明名称 |
Turbine Section of High Bypass Turbofan |
摘要 |
A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170. |
申请公布号 |
US2012291449(A1) |
申请公布日期 |
2012.11.22 |
申请号 |
US201213475252 |
申请日期 |
2012.05.18 |
申请人 |
ADAMS PAUL R.;MAGGE SHANKAR S.;STAUBACH JOSEPH B.;LORD WESLEY K.;SCHWARZ FREDERICK M.;SUCIU GABRIEL L.;UNITED TECHNOLOGIES CORPORATION |
发明人 |
ADAMS PAUL R.;MAGGE SHANKAR S.;STAUBACH JOSEPH B.;LORD WESLEY K.;SCHWARZ FREDERICK M.;SUCIU GABRIEL L. |
分类号 |
F02C3/04 |
主分类号 |
F02C3/04 |
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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