Device for preparation of fuel-air mixture for small gas turbine preferably in model aircraft

摘要

The device draws combustion air through the compressor turbine (1) and diffusor (2). About 85% of the flow continues through holes (3,4) into the mixing and buffer zones. The remainder is directed with the fuel distribution pipe (5) through angled hollow blades (6) into the annular evaporator (9) between the inner wall of the flame tube (7) and the exhaust pipe (8). The angle of the blades creates strong eddies within the evaporator as well as ahead of the turbine (10). The distribution pipe has radial bores from which fuel is sprayed on to the inner and/or outer walls of the evaporator.