A turbine engine system utilizes one or more augmented combustion modules to produce an exhaust that is fed into the turbine portion of the engine and wherein power is produced by the augmented combustion module for use to drive the main shaft and/or for auxiliary purposes. An augmented combustion module is configured between the compressor and the turbine of the engine and receives compressed air from the compressor and ignites an air/fuel-mixture to turn a shaft that can be used to produce power. The shaft may be coupled with an electrical power generator, a pump, a hydraulic or pneumatic power generator and/or power conversion or transmission devices and/or coupled with the main shaft of the turbine engine. The power from a power generator may be stored in a battery, hydraulic accumulator or pneumatic accumulator and may be used to power auxiliary electrical, hydraulic or pneumatic devices.

A micro-auxiliary power unit for supplying electric power to a vehicle includes a thermal resistant enclosure having an intake duct for receiving air, and a source of fuel. A fuel valve is fluidly coupled from the enclosure, and the fuel valve is movable between an opened position and a closed position. The micro-auxiliary power unit includes a Wankel engine to drive an output shaft and a starter-generator coupled to the output shaft to generate electric power. The micro-auxiliary power unit includes a system that has at least one sensor disposed within the enclosure that observes a condition of the enclosure and generates sensor signals, and a controller having a processor that receives the sensor signals, determines the presence of a thermal event within the enclosure and based on the determination, outputs one or more control signals to the fuel valve to move the fuel valve to the closed position.

A micro-auxiliary power unit for supplying electric power to a vehicle includes a thermal resistant enclosure having an intake duct for receiving air, and a source of fuel. A fuel valve is fluidly coupled from the enclosure, and the fuel valve is movable between an opened position and a closed position. The micro-auxiliary power unit includes a Wankel engine to drive an output shaft and a starter-generator coupled to the output shaft to generate electric power. The micro-auxiliary power unit includes a system that has at least one sensor disposed within the enclosure that observes a condition of the enclosure and generates sensor signals, and a controller having a processor that receives the sensor signals, determines the presence of a thermal event within the enclosure and based on the determination, outputs one or more control signals to the fuel valve to move the fuel valve to the closed position.

The present disclosure relates to an apparatus/process/cycle for production of power with heat recovery. The apparatus includes a primary engine and a secondary engine connected downstream of the primary engine to exploit waste heat from the primary engine. The primary engine is an internal combustion engine having an exhaust for exhaust fumes. The secondary engine is a closed-cycle gas turbine comprising a secondary compression device, a secondary gas turbo-expander, a closed circuit crossed by a working fluid and connecting the above-mentioned secondary compression device and the secondary gas turbo-expander. A heat exchanger is arranged downstream of the exhaust and comprises a heat exchange portion of the closed circuit. The heat exchanger is crossed by the exhaust fumes to transfer heat from the exhaust fumes to the working fluid of the closed circuit. The secondary engine also comprises a recuperator operatively disposed in the closed circuit.

A propulsion system for an aircraft having a nacelle and a fuselage is provided. The nacelle has a gas flow path and a nacelle interior region. The system includes a compressor section, an intermittent IC engine, a turbine section, a fan, and an IC cooling system. A first electric motor powers the compressor section. The compressor section produces a flow of elevated pressure compressor air. The intermittent IC engine selectively intakes the compressor air flow and produces an exhaust gas flow. The turbine section powered by exhaust gas in turn powers a first electric generator. The fan is driven by a second electric motor. The IC engine cooling system has a heat exchanger disposed within the gas flow path, coolant, coolant piping, and a pump. The heat exchanger is disposed in the nacelle.

A propulsion system for an aircraft having a nacelle and a fuselage is provided. The nacelle has a gas flow path and a nacelle interior region. The system includes a compressor section, an intermittent IC engine, a turbine section, a fan, and an IC cooling system. A first electric motor powers the compressor section. The compressor section produces a flow of elevated pressure compressor air. The intermittent IC engine selectively intakes the compressor air flow and produces an exhaust gas flow. The turbine section powered by exhaust gas in turn powers a first electric generator. The fan is driven by a second electric motor. The IC engine cooling system has a heat exchanger disposed within the gas flow path, coolant, coolant piping, and a pump. The heat exchanger is disposed in the nacelle.

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.

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.

The present invention discloses embodiments for a power augmentation system of a gas turbine engine resulting in performance improvements while also improving efficiency. The invention provides systems and methods for generating a heated air supply by way of mixing compressed air from an electrically-driven process with air drawn from the engine compressor discharge plenum.

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.