초록 ▼

A gas turbine engine having a turbine housing, air compressor, diffuser, shafts, bearings, seals, ignition system, fuel system and starter with improvements comprising an air charge combustor inlet plate (44), a rotating constant volume combustor (74), a gas metering valve plate (46), a gas distribu

A gas turbine engine having a turbine housing, air compressor, diffuser, shafts, bearings, seals, ignition system, fuel system and starter with improvements comprising an air charge combustor inlet plate (44), a rotating constant volume combustor (74), a gas metering valve plate (46), a gas distributor plate (102), gas nozzle plates (48), (104) and (112), and turbine wheels (66), (68) and (70); which enables changing pressures inherent to constant volume combustion, in combustion chambers (74E)-(74T), to simultaneously produce a plurality of initially separate, coaxial and annular, virtually continuous gas flow streams for efficiently converting combustion gas energy into useful work. The combustor (74), rotating very slowly relative to the speed of the main turbine shaft, with individual combustion chambers (74E)-(74T) equally spaced circumferentially about the center of rotation, provides sufficient time for complete combustion, supplying gas metering valve plate (46) and gas distributor plate (102) with gases at predetermined pressure steps for a high production rate of high frequency, coaxial, annular gas streams driving turbine wheels (66), (68) and (70) juxtaposed coaxially with paired nozzles plates (48), (104) and (112). The turbine wheels and the nozzle plates incorporate conventional axial flow blades and nozzle vane air foils, but said vanes and blades are arranged in a plurality of radially displaced concentric patterns with circular separators for accommodating a plurality of annular gas streams. After passing through the nozzle plates and the turbine wheels, spent gas streams merge into predetermined equal temperature, equal pressure and equal velocity confluence zones and exhaust to atmosphere. The turbine assembly provides short and smooth passages for the air and gas processes. Alternate embodiments include a different number of turbine wheels and nozzle plates, and other embodiments incorporate optional features similar to existing technology equipment and heat recovery cycles.

대표청구항 ▼

[ I claim:] [1.] 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 havi

[ I claim:] [1.] 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; d 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.