| 摘要 |
<p>The gas turbine engine comprises a rotor with combustion chambers and a turbine, which are arranged in a housing and are rigidly fastened to a shaft. The combustion chambers are arranged around the periphery of the rotor. The shaft of the rotor and turbine has a cavity for the passage therethrough of air from a compressor. A dividing disc is mounted in the housing between the rotor and the turbine, said dividing disc being rigidly connected to the housing and having elongated apertures opposite the axis of symmetry of the disc. A plurality of blades is arranged in each aperture along the length thereof, said blades being connected to the dividing disc or being integral therewith and together forming air ducts for the passage of gas from a combustion chamber of the rotor to the turbine blades. The axis of the nozzle of each combustion chamber is inclined with respect to the transverse axis of the combustion chamber. The invention is intended to increase the efficiency and power of an engine and simplify the design thereof.</p> |
