Patent ID: 6553752
Filing Date: 2003-04-29
Classification: F02C,F02G

Abstract:
A turbine engine comprising:at least one combustion chamber; a water jacket constructed and arranged to transfer heat from the combustion chamber to water contained in the water jacket; a high pressure pump constructed and arranged to retain a pressure in the water jacket above a boiling point of the water; a conduit, throttle valve and flash tank in communication with the water jacket constructed and arranged for allowing water to pass from the water jacket to the throttle valve and flash into steam in the flash tank; at least one compressor constructed and arranged to provide a compressed gas to said at least one combustion chamber; at least one turbine blade constructed and arranged to be driven by a pressurized gas formed in said combustion chamber; a conduit connected to the flash tank being constructed and arranged to supply steam to the turbine blade to thereby cool the turbine blade; wherein said combustion chamber comprises: a wall structure defining an interior chamber; an explosion chamber being disposed within said interior chamber; a first reflecting surface for reflecting a pressure wave within said interior chamber; a second reflecting surface for reflecting said pressure wave within said interior chamber, wherein said first and second reflecting surfaces being constructed and arranged to resonate said pressure wave in said interior chamber; at least one first inlet for introducing a first gas into said explosion chamber, said first inlet being located where the pressure in said combustion chamber varies, and said first inlet comprising a first inlet valve for controlling the flow of said first gas into said explosion chamber, said first inlet valve being constructed and arranged to open and close in sync with said resonating pressure wave whereby said first inlet valve is open when lower than average interior chamber pressures are prevalent against said first inlet valve and closed when higher than average interior chamber pressures are prevalent against said first inlet valve; at least one second inlet for introducing said compressed gas into said interior chamber being located where a pressure varies in said combustion chamber, and said second inlet comprising a second inlet valve for controlling the flow of said second gas into said interior chamber, said second inlet valve being constructed and arranged to open and close in sync with said resonating pressure wave whereby said second inlet valve is open when lower than average interior chamber pressures are prevalent against said second inlet valve and closed when higher than average interior chamber pressures are prevalent against said second inlet valve, said second inlet being connected to said at least one compressor; and at least one outlet from said interior chamber for drawing off said pressurized gas from said chamber and being constructed and arranged to supply said pressurized gas to said at least one turbine blade, wherein said first inlet valve and said second inlet valve comprise a rotary valve.