| 摘要 |
Gas turbine in which the compressor and the radial turbine form but one element, said turbine overcoming the problems relating to the cooling of the turbine blade, having fewer moving parts and being more lightweight, easy to maintain and with greater potential than a four-stroke engine. It comprises an air intake orifice followed by a radial turbine compressor that forms but one element compressing air and supplying it to the combustion chamber, this same turbine compressor converts some of the energy of the combustion gases into mechanical energy. The turbine comprises a casing (1) an air intake (7) followed by a turbine compressor (4) (turcomp) supplying the combustion chamber (9) with air in its lower part. The gases are converted into mechanical energy by the turbine compressor (4) (turcomp) in its upper part then discharged into the exhaust (10). Baffles which act as deflectors are interposed (6-6a and 5). The turbine according to the invention is particularly intended for pleasure and business aviation and transport in turboprop versions. It may also be fitted to helicopters. In the jet engine version, it may be used for business air travel.
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