An aircraft power system includes an internal combustion core engine where an inlet airflow is mixed with a fuel and ignited to generate shaft power and a primary gas flow, a boost combustor where a portion of the primary gas flow from the core engine is combined with fuel and ignited to generate a boosted gas flow, and a drive turbine that includes a drive output shaft wherein the boosted gas flow is expanded to generate shaft power.

A combustion management device for generating a thrust burst to impart a physical impulse. In operation, a combustion chamber, defined by a valve unit (33), is primed to a set pressure and fueled by fuel injectors (23). An ignitor (22) then initiates combustion. Under force of combustion, the valve unit is moved, pulling an exhaust valve (18) from an exhaust port (16), releasing combustion products as thrust. Work may be derived from the travel of the valve unit, independent of the thrust generated. After combustion, a return mechanism returns the valve unit to the start position, ready to repeat the process. Simple design, and valve operations needing little more than pressure differentials to function, make for simplified construction, and more modular applications.

A combustion management device for generating a thrust burst to impart a physical impulse. In operation, a combustion chamber, defined by a valve unit (33), is primed to a set pressure and fueled by fuel injectors (23). An ignitor (22) then initiates combustion. Under force of combustion, the valve unit is moved, pulling an exhaust valve (18) from an exhaust port (16), releasing combustion products as thrust. Work may be derived from the travel of the valve unit, independent of the thrust generated. After combustion, a return mechanism returns the valve unit to the start position, ready to repeat the process. Simple design, and valve operations needing little more than pressure differentials to function, make for simplified construction, and more modular applications.

A turbofan engine assembly including a compressor, an intermittent internal combustion engine having an inlet in fluid communication with an outlet of the compressor through at least one first passage of an intercooler, a turbine having an inlet in fluid communication with an outlet of the intermittent internal combustion engine, the turbine compounded with the intermittent internal combustion engine, a bypass duct surrounding the intermittent internal combustion engine, compressor and turbine, and a fan configured to propel air through the bypass duct and through an inlet of the compressor, wherein the intercooler is located in the bypass duct, the intercooler having at least one second passage in heat exchange relationship with the at least one first passage, the at least one second passage in fluid communication with the bypass duct.

A turbofan engine assembly including a compressor, an intermittent internal combustion engine having an inlet in fluid communication with an outlet of the compressor through at least one first passage of an intercooler, a turbine having an inlet in fluid communication with an outlet of the intermittent internal combustion engine, the turbine compounded with the intermittent internal combustion engine, a bypass duct surrounding the intermittent internal combustion engine, compressor and turbine, and a fan configured to propel air through the bypass duct and through an inlet of the compressor, wherein the intercooler is located in the bypass duct, the intercooler having at least one second passage in heat exchange relationship with the at least one first passage, the at least one second passage in fluid communication with the bypass duct.

A turbofan engine assembly including an internal combustion engine in fluid communication between a compressor and a turbine, the internal combustion engine having an engine shaft, a bypass duct surrounding the internal combustion engine, and a fan drivingly engaged to the engine shaft via a gearbox, the gearbox configured to increase an output speed of the fan relative to an input speed of the engine shaft.

A turbofan engine assembly including an internal combustion engine in fluid communication between a compressor and a turbine, the internal combustion engine having an engine shaft, a bypass duct surrounding the internal combustion engine, and a fan drivingly engaged to the engine shaft via a gearbox, the gearbox configured to increase an output speed of the fan relative to an input speed of the engine shaft.

An engine assembly having an internal combustion engine, a turbine module including a turbine casing, a support casing rigidly connecting the turbine casing to a remainder of the assembly, and an inlet scroll connected to the turbine casing without any direct rigid connection to the support casing. The inlet scroll includes an inlet pipe for each engine exhaust port. An exhaust pipe is provided for each exhaust port, connected to and providing fluid communication between the respective exhaust port and inlet pipe. The exhaust pipe is movable relative to at least one of the exhaust port and the inlet pipe at a corresponding connection therewith. One of the exhaust and inlet pipes floatingly extends through an opening defined in the support casing. The assembly may be a compound engine assembly.

An engine assembly having an internal combustion engine, a turbine module including a turbine casing, a support casing rigidly connecting the turbine casing to a remainder of the assembly, and an inlet scroll connected to the turbine casing without any direct rigid connection to the support casing. The inlet scroll includes an inlet pipe for each engine exhaust port. An exhaust pipe is provided for each exhaust port, connected to and providing fluid communication between the respective exhaust port and inlet pipe. The exhaust pipe is movable relative to at least one of the exhaust port and the inlet pipe at a corresponding connection therewith. One of the exhaust and inlet pipes floatingly extends through an opening defined in the support casing. The assembly may be a compound engine assembly.

An aircraft propulsion system for an aircraft having a nacelle that includes a pylon structure is provided. The system includes compressor and turbine sections, an IC engine, a fan, and an IC engine cooling system. The compressor section is powered by a first electric motor. The turbine section is configured to power a first electric generator configured to produce electrical power. The first fan is rotationally driven by a second electric motor. The fan has a hub and a plurality of fan blades extending radially outward from the hub. The hub is disposed in the pylon interior region and the fan blades are configured to extend outside of the pylon structure. The fan is positioned downstream of the compressor section. The IC engine cooling system has a heat exchanger and a pump configured to provide coolant communication between the IC engine and the heat exchanger.