Patent ID: 11884414
Assignee: ROLLS-ROYCE PLC
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC B  F | IPC B  F

Claim 0:
1. A turbofan engine for providing propulsive thrust to a supersonic aircraft, the engine having:
an engine core comprising in flow series a compressor, a combustor and a turbine;
a fan located upstream of the engine core;
a supersonic intake for slowing down incoming air to subsonic velocities at an inlet to the fan formed by the intake;
a bypass duct surrounding the engine core, wherein the fan generates a core airflow to the engine core and a bypass airflow through the bypass duct;
a mixer for mixing an exhaust gas flow exiting the engine core and the bypass airflow exiting the bypass duct;
a thrust nozzle rearwards of the mixer for discharging the mixed flows; and
a controller configured to control the thrust produced by the engine over a range of flight operations including a transonic push operation during which the aircraft transitions from subsonic to supersonic flight and a supersonic cruise operation;
wherein, to change the level of engine thrust between the transonic push operation and the supersonic cruise operation, the controller varies an area of a variable area throat of the thrust nozzle or adjusts one or more components which vary the relative areas available for the hot exhaust gas flow and the cold bypass airflow at the mixer while holding the fan inlet non-dimensional mass flow w√{square root over (T)}/P substantially constant, where w is the mass flow of the incoming air at the fan inlet, T is stagnation temperature of the incoming air at the fan inlet and P is stagnation pressure of the incoming air at the fan inlet.