Abstract: A method for cooling a high-temperature radial gas turbine engine increases turbine thermal efficiency and/or extends turbine operational lifetime. A bleed flow path enables cooling air to flow from a compressor outlet and along surfaces of the gas turbine rotors. The amount of cooling increases in proportion to a bleed fraction, which is defined as the ratio of mass flow in the bleed flow path to total mass flow in the compressor outlet. The heated air in the bleed flow path is mixed with the main mass flow into the turbine engine, so as to restore mass flow into the turbine, while maintaining a high turbine operating temperature and thermal efficiency. The thermal efficiency of a recuperator also increases in proportion to the bleed fraction.

Abstract: A compact cooling and boosting gas turbine system provides combined cooling, heating, and electrical power with high energy efficiency. The system has a pressure booster and a turbo-compressor. The pressure booster includes a fuel inlet, a fuel outlet, and a piston, and is in fluid communication with a gas turbine engine. The pressure booster also includes a coolant inlet, a coolant chamber, and a coolant outlet, and is in fluid communication with a closed pressurized coolant flow. The turbo-compressor includes a compressor and a turbine, and is in fluid communication with a water input flow and with the closed pressurized coolant flow. A coolant flow control valve controls the closed pressurized coolant flow. The system is configured to provide a cold water flow for a first position of the flow control valve and to provide a hot water flow for a second position of the flow control valve.

Abstract: A cooling system for cooling hot components of a radial or axial gas turbine engine, which includes a recuperator heat exchanger, provides engine cooling without loss of thermal efficiency. Air flow leaving a compressor is split between a recuperator flow path and a bleed flow path. Air in the bleed flow path flows through the hot parts of the engine, thereby cooling the engine and heating the air. The air in the bleed flow path is combined with the output flow from a combustor and directed into a turbine inlet. A reduction of air flow in the recuperator flow path increases the thermal effectiveness of the recuperator heat exchanger by increasing a ratio of hot and cold flows inside the heat exchanger. The increase in thermal effectiveness of the heat exchanger compensates for energy losses incurred by diverting a portion of the compressor air flow for cooling.

Abstract: A compact cooling and boosting gas turbine system provides combined cooling, heating, and electrical power with high energy efficiency. The system has a pressure booster and a turbo-compressor. The pressure booster includes a fuel inlet, a fuel outlet, and a piston, and is in fluid communication with a gas turbine engine. The pressure booster also includes a coolant inlet, a coolant chamber, and a coolant outlet, and is in fluid communication with a closed pressurized coolant flow. The turbo-compressor includes a compressor and a turbine, and is in fluid communication with a water input flow and with the closed pressurized coolant flow. A coolant flow control valve controls the closed pressurized coolant flow. The system is configured to provide a cold water flow for a first position of the flow control valve and to provide a hot water flow for a second position of the flow control valve.

Abstract: A method for cooling a high-temperature radial gas turbine engine increases turbine thermal efficiency and/or extends turbine operational lifetime. A bleed flow path enables cooling air to flow from a compressor outlet and along surfaces of the gas turbine rotors. The amount of cooling increases in proportion to a bleed fraction, which is defined as the ratio of mass flow in the bleed flow path to total mass flow in the compressor outlet. The heated air in the bleed flow path is mixed with the main mass flow into the turbine engine, so as to restore mass flow into the turbine, while maintaining a high turbine operating temperature and thermal efficiency. The thermal efficiency of a recuperator also increases in proportion to the bleed fraction.

Abstract: A cooling system for cooling hot components of a radial or axial gas turbine engine, which includes a recuperator heat exchanger, provides engine cooling without loss of thermal efficiency. Air flow leaving a compressor is split between a recuperator flow path and a bleed flow path. Air in the bleed flow path flows through the hot parts of the engine, thereby cooling the engine and heating the air. The air in the bleed flow path is combined with the output flow from a combustor and directed into a turbine inlet. A reduction of air flow in the recuperator flow path increases the thermal effectiveness of the recuperator heat exchanger by increasing a ratio of hot and cold flows inside the heat exchanger. The increase in thermal effectiveness of the heat exchanger compensates for energy losses incurred by diverting a portion of the compressor air flow for cooling.

Abstract: A multiport valve suitable for use with a gas-turbine allowing switching of a mode of gas-turbine operation between a Brayton cycle and an inverse Brayton cycle, and a gas-turbine configured to switch between a high-pressure operation mode according to a Brayton cycle and a low-pressure operation mode according to an inverse Brayton cycle employing the valve are provided. Also provided are a method and apparatus for operating a gas-turbine according to an inverse Brayton cycle.

Abstract: Hybrid gas-turbine electric vehicles and methods for operating hybrid gas-turbine electric vehicles are provided that make use of the gas-turbine for efficiently providing cooling for the vehicle.

Abstract: An orbiting combustor nozzle (OCN) engine, having a rotating assembly comprising a co-rotating compressor and nozzle wheel enclosed within a non-rotating outer casing, defining a rotating combustion chamber, is disclosed. Combustion occurs in the combustion chamber in a vortex of gas that rotates at the same angular velocity as the rotating assembly. Also disclosed, is a method of cooling a blade of a rotating wheel, such as a turbine wheel or nozzle wheel, by projecting cool air at the base of the vane form a nozzle corotating with the blade. Such cooling is easily implemented in an OCN engine with use of an innovative annular combustor. Also disclosed is a method of countering axial backflow by use of a combustion chamber compressor.

Abstract: An orbiting combustor nozzle (OCN) engine, having a rotating assembly comprising a co-rotating compressor and nozzle wheel enclosed within a non-rotating outer casing, defining a rotating combustion chamber, is disclosed. Combustion occurs in the combustion chamber in a vortex of gas that rotates at the same angular velocity as the rotating assembly. Also disclosed, is a method of cooling a blade of a rotating wheel, such as a turbine wheel or nozzle wheel, by projecting cool air at the base of the vane form a nozzle corotating with the blade. Such cooling is easily implemented in an OCN engine with use of an innovative annular combustor. Also disclosed is a method of countering axial backflow by use of a combustion chamber compressor.

Abstract: An orbiting engine includes a plurality of combustion chambers (52) rigidly connected to and disposed equidistantly from a central shaft (54). The combustion chambers (52) are oriented so that exhaust gases emerge therefrom tangentially to a circle concentric with the shaft (54), thereby causing the shaft to rotate. In preferred embodiments, a centrifugal compressor (62), radially inward from the combustion chambers (52) and driven by the shaft (54), compresses air that serves to oxidize fuel injected into the combustion chambers (52).

Abstract: An air cycle air conditioning system including a turbine for receiving air and providing expansion thereof, thus lowering the temperature and pressure of the air, an air--air heat exchanger defining a first air flow path for air to be cooled and a second air flow path for air from the turbine at sub-atmospheric pressure to pass therethrough and absorb heat from the air to be cooled, and a compressor, at least partially driven by the turbine, for drawing air at sub-atmospheric pressure through the second flow path for air, characterized by a pre-heater which heats a flow of air, preferably comprising a mixer of ambient air and recirculation air, and directs this mixed flow to the air--air heat exchanger, thereby increasing its temperature and, as a result, the outlet temperature of the secondary air flow, thereby increasing its water vapor absorption capacity.

Abstract: An air cycle air conditioning system including an air-air heat exchanger defining a first air flow path for air to be cooled and a second air flow path for air to pass therethrough and absorb heat from the air to be cooled and apparatus for supplying air to the second air flow path at sub-atmospheric pressure.

Abstract: A swim-in-place pool has horizontal inner and outer circulating waterways arranged in such manner that a portion of the inner waterway coincides with a portion of the outer waterway. The non-coincident portion of the inner waterway then provides a swimming space. A plurality of impeller blades are suspended in a spaced series within the coinciding portion of the two waterways, each of the blades in its operative condition extending transversely of that waterway and occupying substantially all of its cross-sectional area. A power drive advances the blades in unison along the coinciding portion of the two waterways so that a rather fixed body of water is captured between each two adjacent blades and advanced therewith. A diversion structure adjacent the entry of the non-coincident portion of the inner waterway diverts a continuous flow of water in a relatively non-turbulent state into and through the swimming space.

Abstract: A swim-in-place pool has an inlet opening to the swimming area, which is comparable in width and height to the space that would be occupied by a swimmer's body. Water is driven through the inlet opening at a velocity which is substantially constant throughout the cross-sectional area of the opening.The illustrated apparatus includes a housing providing an annular cavity within which a circular water advancing means is revolvably disposed. The swimming space lies essentially along a diameter of the annular cavity. The inlet opening is provided at one end of the swimming space for receiving water from the annular cavity, and an outlet opening is provided at the other end to return water to the annular cavity.