A propulsion system for an aircraft including a gas generating core engine (70) that generates an exhaust gas flow (52) that is expanded through a turbine section (32). A power turbine (38) engine is forward of the core engine (70). A propulsor (22) is cou...

A gas turbine engine assembly includes a core engine that includes a core flow path (C) where a core airflow (25) is compressed in a compressor section (24), communicated to a combustor section (26), mixed with fuel and ignited to generate a high energy co...

A method of operating a propulsion system (14) includes powering an auxiliary fan (18) with a gas turbine engine (20), where the auxiliary fan (18) is along an auxiliary axis (F) and the gas turbine engine (20) is along an engine axis (F), the auxiliary ax...

Provided are a combustor control method and a combustor controller capable of calculating the combustion air flow and the fuel flow in multi-shafts gas turbine with high precision and without the need of performing complicated calculations and thereby calc...

An engine arrangement has a first propeller assembly (21a), and a first hydraulic actuator (23a) for angular displacement of propellers (22a) of the first propeller assembly, the first hydraulic actuator rotating with the first propeller assembly. The engi...

The subject invention is directed to a new and useful method of detecting in-range engine sensor faults for a gas turbine engine associated with a helicopter. The method includes the steps of computing engine shaft horsepower for a plurality of engine sens...