公开(公告)号：US20200307779A1

公开(公告)日：2020-10-01

申请号：US16365583

申请日：2019-03-26

Applicant: Bell Textron Inc.

Inventor： Brent Chadwick Ross ,  Alan Carl Ewing ,  Steven Ray Ivans

IPC: B64C27/26 ,  B64C27/06 ,  B64C27/82 ,  B64C3/10 ,  B64C5/02 ,  B64D27/14 ,  B64D27/02

Abstract: A fully compounding rotorcraft includes a fuselage having first and second wings extending therefrom and configured to provide lift compounding responsive to forward airspeed. A twin boom includes first and second tail boom members that extend aftward from the first and second wings. An empennage is coupled between the aft ends of the tail boom members. An anti-torque system includes a tail rotor that is rotatably coupled to the empennage. An engine is disposed within the fuselage and is configured to provide torque to a main rotor assembly via an output shaft and a main rotor gearbox. An auxiliary propulsive system is coupled to the fuselage and is configured to generate a propulsive thrust to offload at least a portion of a thrust requirement from the main rotor during forward flight, thereby providing propulsion compounding to increase the forward airspeed of the rotorcraft.

公开(公告)号：US20200309066A1

公开(公告)日：2020-10-01

申请号：US16365573

申请日：2019-03-26

Applicant: Bell Textron Inc.

Inventor： Brent Chadwick Ross ,  Steven Ray Ivans ,  Alan Carl Ewing

IPC: F02K3/06 ,  B64C27/26 ,  B64D27/10 ,  B64D33/02 ,  B64D33/04 ,  F02C3/06

Abstract: A hybrid propulsion engine for a rotorcraft includes a core turboshaft engine having a gas path and an output shaft that provides torque to a main rotor. A fan module is disposed relative to the core turboshaft engine and is coupled to the output shaft. The fan module has a bypass air path that is independent of the gas path. A thrust nozzle is configured to mix exhaust gases from the core turboshaft engine with bypass air from the fan module and to discharge the mixture to provide propulsive thrust. In a turboshaft configuration, the fan module is closed to prevent the flow of bypass air therethrough such that the thrust nozzle does not provide propulsive thrust. In a turboshaft and turbofan configuration, the fan module is open allowing the flow of bypass air therethrough such that the thrust nozzle provides propulsive thrust, thereby supplying propulsion compounding for the rotorcraft.