Abstract: A method and apparatus for improving the efficiency of an integrated combined cycle Brayton-Rankine engine is disclosed. The engine has a main power turbine operating on an open-loop Brayton cycle. Its air supply is furnished by a compressor independently driven by the turbine of a closed-loop Rankine cycle which derives heat energy from the exhaust of the Brayton turbine. A portion of the exhaust gas is recirculated into the compressor inlet during part-load operation. The recirculation of exhaust gas improves the efficiency of the engine at part-load over that which would occur with only ambient temperature air entering the compressor. Also, the controlled application of exhaust gas recirculation improves the dynamic response of the engine to demands for changes in power output and is predicted to reduce the emission of polluting nitros oxides from the engine combustor.

Abstract: A combined gas turbine-Rankine cycle powerplant with improved part load efficiency is disclosed. The powerplant has a gas turbine with an organic fluid Rankine bottoming cycle which features an inter-cycle regenerator acting between the superheated vapor leaving the Rankine turbine and the compressor inlet air. The regenerator is used selectively as engine power level is reduced below maximum rated power.

Abstract: A method and apparatus for improving the efficiency of an integrated combined cycle Brayton-Rankine engine is disclosed. The engine has a main power turbine operating on an open-loop Brayton cycle. Its air supply is furnished by a compressor independently driven by the turbine of a closed-loop Rankine cycle which derives heat energy from the exhaust of the Brayton turbine. A portion of the exhaust gas is recirculated into the compressor inlet during part-load operation. The recirculation of exhaust gas improves the efficiency of the engine at part-load over that which would occur with only ambient temperature air entering the compressor. Also, the controlled application of exhaust gas recirculation improves the dynamic response of the engine to demands for changes in power output and is predicted to reduce the emission of polluting nitrous oxides from the engine combustor.

Abstract: A method and apparatus for control of an integrated combined cycle Brayton-Rankine engine is disclosed. The engine has a combustor and main power turbine operating on the Brayton cycle. Combustion air is supplied by a compressor independently driven by a Rankine vapor turbine. The closed loop Rankine cycle derives its heat energy from the exhaust of the Brayton turbine. Engine speed and power level are controlled by varying the fuel flow to the combustor and by throttling the air flow to the compressor.

Abstract: An engine consisting of an open Brayton cycle gas turbine mechanically as well as thermodynamically integrated with a closed cycle Rankine turbine engine is disclosed. The engine heat exchangers, including Rankine vapor generator, regenerator and condenser, are of annular configuration and are concentric with the axis of rotation of the turbomachinery components. A cooling fan is mounted coaxially with the condenser for improved cooling effectiveness. The engine components also are balanced around the gearbox for improved installation and use.

Abstract: A method and apparatus for improving the efficiency of a compressor of a gas turbine engine is disclosed. The inlet gas entering the compressor is stratified into two portions of different temperatures. The higher temperature gas is introduced adjacent the outer tips of the compressor blades to reduce the relative Mach number of the flow at that area.

Abstract: An engine having a main power turbine operating on the Brayton cycle, has its air supply furnished by a compressor independently driven by a Rankine turine which derives its heat energy from the exhaust of the Brayton turbine. The engine is constructed in modules. One module consists primarily of a single stage Brayton turbine, with an output gearing system, and a coaxial extension containing an intercycle heat exchanger. A second module comprises a single stage Rankine turbine and a single stage compressor driven thereby for supplying air to the Brayton turbine, a feed pump for the Rankine fluid interposed between the Rankine turbine and the compressor, and accessory devices driven by the Rankine turbine for starting the engine. The second module has its axis perpendicular to the axis of the first-mentioned module. A condenser-regenerator module is disposed in a plane perpendicular to the axis of the second module and parallel to the axis of the first-mentioned module.

Abstract: A radial inflow turbine with supersonic inlet nozzles in an axial-tangential plane is disclosed. The nozzles discharge into an annular vaneless space around the turbine rotor and the fluid flow enters the rotor vanes in a radially inward direction.