Invention Grant
- Patent Title: Turbine section of high bypass turbofan
- Patent Title (中): 高旁路涡轮风扇涡轮段
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Application No.: US13599175Application Date: 2012-08-30
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Publication No.: US09010085B2Publication Date: 2015-04-21
- Inventor: Paul R. Adams , Shankar S. Magge , Joseph B. Staubach , Wesley K. Lord , Frederick M. Schwarz , Gabriel L. Suciu
- Applicant: Paul R. Adams , Shankar S. Magge , Joseph B. Staubach , Wesley K. Lord , Frederick M. Schwarz , Gabriel L. Suciu
- Applicant Address: US CT Hartford
- Assignee: United Technologies Corporation
- Current Assignee: United Technologies Corporation
- Current Assignee Address: US CT Hartford
- Agency: Bachman & LaPointe, P.C.
- Main IPC: F02K3/02
- IPC: F02K3/02 ; F02C7/36 ; F02K3/06 ; F02C3/113 ; F02K3/075
Abstract:
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.
Public/Granted literature
- US20140102076A1 Turbine Section of High Bypass Turbofan Public/Granted day:2014-04-17
Information query
