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). In return, the conventional turbines (171) drives a plurality or rotary compressors (164, 166, 168). The
compound engine of the invention combines the
thermal efficiency of the rotary internal
engine cycle (151) and the high
mass flow, high power, compact size and light weight of the gas
turbine engines.