Patent ID: 6481197
Filing Date: 2002-11-19
Classification: F02C,F02G

Abstract:
A turbine engine comprising:at least one combustion chamber; 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; and a conduit connected to the combustion chamber in a location where the combustion chamber pressure varies and being constructed and arranged to supply the compressed gas 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.