公开(公告)号：US20200017229A1

公开(公告)日：2020-01-16

申请号：US16035340

申请日：2018-07-13

Applicant: Bell Helicopter Textron Inc.

Inventor： Alan Hisashi Steinert ,  Thomas Dewey Parsons ,  Troy Cyril Schank

IPC: B64D35/02 ,  B64D27/20 ,  F02C7/36 ,  F02K3/06 ,  F02K3/075 ,  F04D25/16

Abstract: Systems and methods include providing an aircraft with a fuselage and a convertible engine disposed within the fuselage. The convertible engine is operable as a turbofan engine in a thrust mode and a turboshaft engine in a shaft power mode. The convertible engine includes a housing, an engine core having a low pressure turbine shaft, and a bypass fan system. The bypass fan system includes a bypass fan having a fan clutch. The fan clutch selectively couples at least a portion of the bypass fan to the low pressure turbine shaft when the convertible engine is operated in the thrust mode and decouples at least a portion of the bypass fan from the low pressure turbine shaft when the convertible engine is operated in the shaft power mode.