Turbine engine for aircraft, has axial compressor with number of turbine stages corresponding to number of compressor stages that are driven by turbine stages, and guide plates effecting axial direction of air flow

摘要

The engine (1) has an axial compressor (3), combustion chamber and a turbine. The turbine comprises of two turbine stages that are reversibly rotated. The axial compressor has number of turbine stages corresponding to a number of compressor stages, which are driven by the turbine stages. Guide plates effect axial direction of air flow, and an additional guide plate is provided at the end of the turbine stages.