Abstract: A heat engine having a rotary vane compressor and a rotary vane turbine operates in a highly efficient thermodynamic cycle which includes a power expansion phase up to ambient pressure and a limited temperature constant volume combustion followed by a constant pressure combustion and/or a constant temperature combustion. A compound propulsion engine utilizing the thermodynamic cycle has a primary stage having an axial compressor and a rotary vane turbine, and a secondary stage having an axial turbine and a rotary vane compressor, the two stages being aero-thermodynamically coupled to each other without provision of an interconnecting drive shaft.

Abstract: For low mass flow, the solo use of the turbo-rotary engine overcomes the limitations of conventional internal combustion engines and enable significant improvement in power, torque and efficiency. The solo configurations (FIG. 1, 2, 3, 4) of the invention comprise compressor (48) and turbine housings (59), each housing receiving an eccentrically placed rotor (135), equipped by a single sliding vane (50, 63). Contact wear of the sliding vane tips (86, 109) with the chamber non-circular cycloidal peripheral (88, 97), is eliminated by a pivot axle vane retention mechanism (139, 150). For high mass flow rate, a compound configuration (FIGS. 8, 9, 10) of rotary compressors and turbines with conventional gas turbine engine components. Allows an improvement in efficiency and performance. Conventional long and heavy concentric main shafts are eliminated. In this invention, rotary turbines drive compressors (158), fans (153), propellers and rotary wings (186).