An engine assembly for use as an aircraft auxiliary power unit, having internal combustion engine(s) in driving engagement with an engine shaft, a generator having a generator shaft directly engaged to the engine shaft such as to be rotatable at a same speed, a compressor having an outlet in communication with the internal combustion engine inlet, and a turbine having an inlet in communication with the internal combustion engine outlet. The turbine may be a first stage turbine, and the assembly may include a second stage turbine having an inlet in communication with the first stage turbine outlet. A method of providing electrical power to an aircraft is also discussed.

A rotary engine includes a housing having a working cavity, a shaft, the shaft having an eccentric portion, a rotor having a first axial face, and a second axial face opposite the first axial face, the rotor disposed on the eccentric portion and within the working cavity, the rotor comprising a first cam on the first axial face, the first came having an eccentricity corresponding to the eccentricity of the eccentric portion of the shaft, and a cover integral with, or fixedly attached to, the housing, the cover comprising a plurality or rollers, each roller engaged with the cam, wherein the cam guides the rotation of the rotor as the rotor rotates within the working cavity and orbits around the shaft.

A rotary engine includes a housing having a working cavity, a shaft, the shaft having an eccentric portion, a rotor having a first axial face, and a second axial face opposite the first axial face, the rotor disposed on the eccentric portion and within the working cavity, the rotor comprising a first cam on the first axial face, the first came having an eccentricity corresponding to the eccentricity of the eccentric portion of the shaft, and a cover integral with, or fixedly attached to, the housing, the cover comprising a plurality or rollers, each roller engaged with the cam, wherein the cam guides the rotation of the rotor as the rotor rotates within the working cavity and orbits around the shaft.

A compound engine system including a Wankel engine having a recess defined in the peripheral wall of the rotor in each of the three rotating chambers, the recess having a volume of more than 5% of the displacement volume of the chambers. The expansion in the turbine section compensates for the relatively low expansion ratio of the rotary engine.

A compound engine system including a Wankel engine having a recess defined in the peripheral wall of the rotor in each of the three rotating chambers, the recess having a volume of more than 5% of the displacement volume of the chambers. The expansion in the turbine section compensates for the relatively low expansion ratio of the rotary engine.

A compound engine assembly with at least one rotary internal combustion engine, an impulse turbine, and an exhaust pipe for each internal combustion engine providing fluid communication between the exhaust port of the respective internal combustion engine and the flow path of the turbine. Each exhaust pipe terminates in a nozzle. For each exhaust pipe, a ratio Vp/Vd between the pipe volume Vp and the displacement volume Vd of the respective internal combustion engine is at most 1.5. A minimum value of a cross-sectional area of each exhaust pipe is defined at the nozzle. In one embodiment, a ratio An/Ae between the minimum cross-sectional area An and the cross-sectional area Ae of the exhaust port of the respective internal combustion engine is at least 0.2. A method of compounding at least one rotary engine is also discussed.

A compound engine assembly with at least one rotary internal combustion engine, an impulse turbine, and an exhaust pipe for each internal combustion engine providing fluid communication between the exhaust port of the respective internal combustion engine and the flow path of the turbine. Each exhaust pipe terminates in a nozzle. For each exhaust pipe, a ratio Vp/Vd between the pipe volume Vp and the displacement volume Vd of the respective internal combustion engine is at most 1.5. A minimum value of a cross-sectional area of each exhaust pipe is defined at the nozzle. In one embodiment, a ratio An/Ae between the minimum cross-sectional area An and the cross-sectional area Ae of the exhaust port of the respective internal combustion engine is at least 0.2. A method of compounding at least one rotary engine is also discussed.

Accordingly, embodiments herein disclose a system (500) for controlling admission volume of an inlet gas for fixed RPM operation of in an apparatus. The system (500) has a boiler (502) for generating a steam at a higher pressure for heating application in a process. A pressure reducing valve (PRV) (504) controls a boiler pressure to process pressure. Inlet ports and exhaust ports are configured by intersection of opening on a rotor housing (614) and opening on a rotating valve. The inlet ports are designed in such a way that a port opening duration can be controlled to admit required volume of a steam corresponding to a mass flow requirement of the process. A port capable of changing the area and timing of opening in such a way that the duration and starting of exhaust can be controlled.

A rotary engine includes a shroud surrounding a rotor. The rotor carries at least one combustion chamber spaced from an axis of rotation of the rotor. A pressure activated valve, such as a relief valve, is located between the combustion chamber and obliquely arranged exhaust nozzles. A drive shaft is engaged to the rotor for mutual rotation. An ECU controls the combustion cycle of the engine based on a signal from a pressure sensor in the combustion chamber. A fuel control valve delivers fuel into the combustion chamber. An air control valve delivers pressurized air into the combustion chamber. The electronic control responds to the pressure signal from the pressure sensor to open the fuel control valve, to fire a spark plug and cause combustion of the fuel within the combustion chamber, and to thereafter open the air control valve to purge the combustion chamber of exhaust gasses. A method of operating the controls is also disclosed.

A rotary engine includes a shroud surrounding a rotor. The rotor carries at least one combustion chamber spaced from an axis of rotation of the rotor. A pressure activated valve, such as a relief valve, is located between the combustion chamber and obliquely arranged exhaust nozzles. A drive shaft is engaged to the rotor for mutual rotation. An ECU controls the combustion cycle of the engine based on a signal from a pressure sensor in the combustion chamber. A fuel control valve delivers fuel into the combustion chamber. An air control valve delivers pressurized air into the combustion chamber. The electronic control responds to the pressure signal from the pressure sensor to open the fuel control valve, to fire a spark plug and cause combustion of the fuel within the combustion chamber, and to thereafter open the air control valve to purge the combustion chamber of exhaust gasses. A method of operating the controls is also disclosed.