| 摘要 |
<p>The invention is directed to a gas turbo engine comprising a compressor, a combustion chamber, and a turbine section installed one after the other in series in the direction of the air and gas flow. The compressor consists of two The deviation of the performance defined as "air mass flow(s)" between both compressor groups is minimized by dividing the blade wheels of the compressor into two groups, wherein the blade wheels of the two compressor groups are made to rotate in opposite directions. Detachment of the air mass flow from the blades of the second compressor groups is avoided by using a bypass. The blade wheels of the second compressor group, beginning at the first blade wheel, are progressively bigger to allow a bypass for the air stream coming from the first compressor group to serve all the blade wheels of the second group simultaneously.</p> |
