Aircraft power plants and associated methods are provided. A method for driving a load on an aircraft includes: transferring motive power from an internal combustion (IC) engine to the load; discharging a flow of first exhaust gas from the IC engine when transferring motive power from the IC engine to the load; receiving the flow of first exhaust gas from the IC engine into a combustor; mixing fuel with the first exhaust gas in the combustor and igniting the fuel to generate a flow of second exhaust gas; receiving the flow of second exhaust gas at a turbine and driving the turbine with the flow of second exhaust gas from the combustor; and transferring motive power from the turbine to the load.

An internal combustion engine includes two intake openings, opened and closed by intake valves; exhaust openings opened and closed by exhaust valves; a fuel injector having a plurality of nozzle holes; and mask parts having wall surfaces extending along outer edges of the intake openings toward the inside of the combustion chamber. The fuel injector arranged wherein the nozzle holes are positioned at the opposite exhaust opening sides from the intake openings, and the plurality of nozzle holes include a first nozzle hole, injecting in a direction with the smallest angle from a plane perpendicular to the axial direction of the cylinder. The wall surface formed wherein a height in a first nozzle hole ejection region positioned in a range of injection of a fuel spray from the first nozzle hole, when viewed in the axial direction, is lower than a height in the first nozzle hole ejection region.

An internal combustion engine includes two intake openings, opened and closed by intake valves; exhaust openings opened and closed by exhaust valves; a fuel injector having a plurality of nozzle holes; and mask parts having wall surfaces extending along outer edges of the intake openings toward the inside of the combustion chamber. The fuel injector arranged wherein the nozzle holes are positioned at the opposite exhaust opening sides from the intake openings, and the plurality of nozzle holes include a first nozzle hole, injecting in a direction with the smallest angle from a plane perpendicular to the axial direction of the cylinder. The wall surface formed wherein a height in a first nozzle hole ejection region positioned in a range of injection of a fuel spray from the first nozzle hole, when viewed in the axial direction, is lower than a height in the first nozzle hole ejection region.

A system for controlling the combustion behavior of an engine is provided. The engine is equipped with a plurality of control subsystems that influence combustion in the engine. The system includes a controller configured to receive a plurality of inputs, to determine a desired subsystem states to operate the engine, and to determine a target value for each of a plurality of control parameters, wherein the target values for one or more control parameters depends on the values of the plurality of inputs. The controller is further configured to communicate the target values of control parameters to the control subsystems.

A system for controlling the combustion behavior of an engine is provided. The engine is equipped with a plurality of control subsystems that influence combustion in the engine. The system includes a controller configured to receive a plurality of inputs, to determine a desired subsystem states to operate the engine, and to determine a target value for each of a plurality of control parameters, wherein the target values for one or more control parameters depends on the values of the plurality of inputs. The controller is further configured to communicate the target values of control parameters to the control subsystems.

Aircraft power plants and associated methods are provided. A method for driving a load on an aircraft includes: transferring motive power from an internal combustion (IC) engine to the load; discharging a flow of first exhaust gas from the IC engine when transferring motive power from the IC engine to the load; receiving the flow of first exhaust gas from the IC engine into a combustor; mixing fuel with the first exhaust gas in the combustor and igniting the fuel to generate a flow of second exhaust gas; receiving the flow of second exhaust gas at a turbine and driving the turbine with the flow of second exhaust gas from the combustor; and transferring motive power from the turbine to the load.

Aircraft power plants and associated methods are provided. A method for driving a load on an aircraft includes: transferring motive power from an internal combustion (IC) engine to the load; discharging a flow of first exhaust gas from the IC engine when transferring motive power from the IC engine to the load; receiving the flow of first exhaust gas from the IC engine into a combustor; mixing fuel with the first exhaust gas in the combustor and igniting the fuel to generate a flow of second exhaust gas; receiving the flow of second exhaust gas at a turbine and driving the turbine with the flow of second exhaust gas from the combustor; and transferring motive power from the turbine to the load.

A GDCI engine has a piston arranged within a cylinder to provide a combustion chamber. According to one embodiment, the GDCI engine operates using a method that includes the steps of supplying a hydrocarbon fuel to the combustion chamber with a research octane number in the range of about 30-65. The hydrocarbon fuel is injected in completely stratified, multiple fuel injections before a start of combustion and supplying a naturally aspirated air charge to the combustion chamber.

Aircraft power plants and associated methods are provided. A method for driving a load on an aircraft includes: transferring motive power from an internal combustion (IC) engine to the load; discharging a flow of first exhaust gas from the IC engine when transferring motive power from the IC engine to the load; receiving the flow of first exhaust gas from the IC engine into a combustor; mixing fuel with the first exhaust gas in the combustor and igniting the fuel to generate a flow of second exhaust gas; receiving the flow of second exhaust gas at a turbine and driving the turbine with the flow of second exhaust gas from the combustor; and transferring motive power from the turbine to the load.

Aircraft power plants and associated methods are provided. A method for driving a load on an aircraft includes: transferring motive power from an internal combustion (IC) engine to the load; discharging a flow of first exhaust gas from the IC engine when transferring motive power from the IC engine to the load; receiving the flow of first exhaust gas from the IC engine into a combustor; mixing fuel with the first exhaust gas in the combustor and igniting the fuel to generate a flow of second exhaust gas; receiving the flow of second exhaust gas at a turbine and driving the turbine with the flow of second exhaust gas from the combustor; and transferring motive power from the turbine to the load.