发明授权
- 专利标题： Turbine section of high bypass turbofan
- 专利标题（中）： 高旁路涡轮风扇涡轮段
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申请号： US13599175申请日： 2012-08-30
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公开(公告)号： US09010085B2公开(公告)日： 2015-04-21
- 发明人: Paul R. Adams , Shankar S. Magge , Joseph B. Staubach , Wesley K. Lord , Frederick M. Schwarz , Gabriel L. Suciu
- 申请人： Paul R. Adams , Shankar S. Magge , Joseph B. Staubach , Wesley K. Lord , Frederick M. Schwarz , Gabriel L. Suciu
- 申请人地址： US CT Hartford
- 专利权人： United Technologies Corporation
- 当前专利权人： United Technologies Corporation
- 当前专利权人地址： US CT Hartford
- 代理机构： Bachman & LaPointe, P.C.
- 主分类号： F02K3/02
- IPC分类号： F02K3/02 ; F02C7/36 ; F02K3/06 ; F02C3/113 ; F02K3/075
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 ratio is below about 170.
公开/授权文献
- US20140102076A1 Turbine Section of High Bypass Turbofan 公开/授权日：2014-04-17
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