Constant volume combustion turbine with plurality flow turbine wheels

A gas turbine engine having a housing, air compressor, bearings, seals, fuel system, ignition system, and starter;

• the improvements juxtaposed coaxially in a direction of gas flow and in the following order comprising:
• (a) a stationary flat and circular combustor air inlet plate having one or more elongated openings positioned for regulating combustion air from said air compressor and incorporating means for securing combustion ignitors;
• (b) a rotating combustor having multiple substantially triangular shaped combustion chambers in a cylindrical drum shaped rotor, said chambers intermittently sealed on an upstream side by said inlet plate, said fuel and ignition systems generating gases by constant volume combustion in said combustor mounted on a combustor shaft rotated by a gear train reducing speed from a main turbine shaft;
• (c) a stationary flat and circular valve plate having a plurality of elongated inlet openings angularly spaced and shaped to intermittently communicate with said combustion chambers, said valve plate inlet openings dividing said combustor discharge gas into multiple flow streams as individual said combustion chambers rotate past each said opening which transmits said flow streams through internal passages tapering to outlet areas, said valve plate intermittently sealing said chambers of said combustor in cooperation with said air inlet plate;
• (d) a stationary flat and circular distributor plate having multiple coaxial and annular passages, said distributor plate passages aligned with said outlet area of said valve plate on one side and aligned with nozzle blade rings on an opposite side, said annular passages converting concentrated gas flow streams into multiple, annular streams;
• (e) a plurality of stationary flat, circular nozzle plates, an upstream of said nozzle plates incorporating three or more concentric rings of nozzle vanes alternating with concentric solid rings, each following of said nozzle plates incorporating one less of said concentric nozzle vane rings, and each said nozzle plate accelerating said gases received from said distributor plate to substantially acoustic velocity;
• (f) a plurality of flat, circular turbine wheels incorporating multiple concentric rings of turbine blades separated by concentric solid rings, said turbine wheels being interposed between adjacent nozzles plates, the number of said turbine blade rings in said turbine wheels equal to the number of matched vane rings in each said nozzle plate preceding each said turbine wheel receiving said gases from said nozzle plates, said turbine wheels attached to said main shaft driving said air compressor and said gear train, additional said turbine wheels driving an output shaft;
• said stationary improvements fixed into said housing which contains all improvements integrated with said turbine components in a manner providing a low pressure loss functioning device, and said improvements producing three or more separate coaxial and annular gas streams whereby said gas turbine utilizing said improvements can convert energy of constant volume combustion into useful rotational power.