초록 ▼

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 t

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.

대표청구항 ▼

The invention claimed is: 1. A method of operating a heat engine having a sliding vane rotary vane compressor and a sliding vane rotary vane turbine, comprising: the sequential steps of: a first step of intaking a fluid in an intake phase into a working chamber of the rotary vane compressor at ambi

The invention claimed is: 1. A method of operating a heat engine having a sliding vane rotary vane compressor and a sliding vane rotary vane turbine, comprising: the sequential steps of: a first step of intaking a fluid in an intake phase into a working chamber of the rotary vane compressor at ambient pressure; a second step of compressing the fluid in a compression phase in the working chamber by rotating a rotor of the rotary vane compressor up to 360�� of rotation; a third step of mixing the compressed fluid with a fuel and igniting the mixture in an initial combustion phase in a combustion chamber external to both the rotary vane compressor and the rotary vane turbine to carry out a limited temperature constant volume combustion process; a fourth step of subjecting the combustion products from the third step to a constant pressure combustion process in a final combustion phase followed by a power expansion phase in an expansion chamber of the rotary vane turbine by rotating a rotor of the rotary vane turbine up to 360�� so that the pressure of the combustion products within the turbine expansion chamber reaches ambient pressure or near ambient pressure when the turbine expansion chamber volume reaches its maximum; and a fifth step of exhausting the combustion products in an exhaust phase from the expansion chamber. 2. A method according to claim 1; wherein for each 360�� of rotation of the rotors of the rotary vane compressor and the rotary vane turbine, there are two complete and consecutive cycles of intake, compression, combustion, power expansion and exhaust phases. 3. A compound propulsion engine comprising: a primary stage including an axial compressor having compressor blades and a rotary shaft defining an axial direction such that ram air is compressed and exits the axial compressor in the axial direction, a sliding vane rotary vane turbine driven by the exiting compressed air and connected by an interconnecting shaft to rotationally drive the axial compressor, and a combustor that is disposed downstream of the axial compressor and that adds heat energy to the exiting compressed air to produce combustion products; and a secondary stage including an axial turbine having turbine blades and a rotary shaft extending in the axial direction and driven by the combustion products exiting the combustor, and a sliding vane rotary vane compressor connected by an interconnecting shaft to the axial turbine so as to be rotationally driven by the axial turbine, the sliding vane rotary vane compressor being connected to receive and further compress a portion of the ram air or a portion of the compressed air exiting the axial compressor to produce a secondary compressed air flow that is directed through one or more transfer passages to an intake of the sliding vane rotary vane turbine. 4. A compound propulsion engine according to claim 3; further including a reheater disposed in one of the transfer passages. 5. A compound propulsion engine according to claim 3; further including an intercooler disposed in one of the transfer passages. 6. A compound propulsion engine according to claim 3; wherein the first and second stages are aero-thermodynamically coupled to each other and are not mechanically connected together by a shaft.