| 摘要 |
FIELD: transport.SUBSTANCE: proposed method comprises feed of air and creation of azimuthal and axial flow to be compressed by compressor, flow heating and discharge at the rate higher than the turbine blades azimuthal rpm and feed of extra air volume. First, hot flow pulse is transferred to said extra air volume. Then, turbine torque is developed to change the flow azimuthal moment to axial force. At compression said flow is directed in azimuthal and axial directions from the axis. Azimuthal vortex is developed to force air flow beyond the compressor blade edges. Said flow is turned azimuthally and axially to the axis to develop the azimuthal vortex. This job is reiterated more than once. Note here that proposed turbojet comprises low-pressure compressor with wing-like elements of blade profiles, turbine, azimuthal combustion chamber, teeth rows with blades upstream and downstream of said combustion chamber. Flow ejection mixing chamber is arranged downstream of combustion chamber. Screws of low-pressure compressor and turbine are made integral and composed of lengthwise surfaces including the sections with profile structure with wing-like elements and centrifugal sections. Fixed row with blades is arranged downstream of turbine, trailing edges of said blades being directed along the axis of engine. The latter comprises extra high-pressure compressor. Compressor rotor incorporates more than one section of variable profile reaching the screw blade outer edge at section edges and having the minimum at its centre. Screw blades are secured at rotor minimums while there leading and trailing edges are directed along rotor spinning. Blades of the last row are directed at outlet along rotor axis. Flow exhaust device is arranged above the rotor is sectionalized and comprises shaped blades fitted at the profile maximums. Blades leading and trailing edges are directed against the rotor rotation.EFFECT: simplified aircraft design, expanded range of applications.2 cl, 1 dwg |
