| 摘要 |
The subject of the invention is a gas turbine with axial fuel gas flow and external blade cooling, in which the turbine wheels are cooled by an air flow ducted in the separate housing sector. The reduced power output of these gas turbines due to the partial fuel gas admission to the turbine wheels cannot be sufficiently overcome, even with subsequent heating of the fuel gas following the first turbine stage, because the power of the succeeding turbine stages is less than that of the first stage. According to the invention fresh air from the compressor is fed to each successive combustion chamber by way of a pipe connection so that the same fuel gas pressure as in the first stage also exists there. As an aircraft jet engine this gas turbine is equipped for stratospheric flight with additional external combustion chambers, which in the event of oxygen deficiency are operated with oxyhydrogen gas and at supersonic speed with the known ram pressure compression. Owing to the optimum blade cooling of the turbine wheels this gas turbine is suitable for high performance operation with hydrogen as fuel. Without the additional external combustion chambers this gas turbine is also a non-polluting vehicle engine.
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