Publications

The ability to design and manufacture our own micro gas turbines would support economic growth and an independent military defence capability. Micro gas turbines can propel cruise missiles, one of the most important air strike weapons. Also, a turbojet, which is a basic form of gas turbine, can be developed into an industrial gas turbine. Grace Palimbunga (2005) built a micro gas turbine (TJ-24), but it ran on gas fuel and produced no thrust. The objective of this research was to improve the design and component geometry of TJ24 in order to produce 24 Newtons of thrust. In this experiment, the modified TJ-24 micro gas turbine was tested to find its maximum thrust, thermal efficiency, and thrust specific fuel consumption. The research began with parametric analysis, the results of which were used to improve compressor efficiency, combustor operating temperature, and air mass flowrate. Some components needed to be re-designed to suit the new operating condition and new compressor and turbine dimensions, including the compressor housing, diffuser, nozzle guide vane, shaft, shaft housing, fuel vaporiser, and turbine housing. Performance testing using liquid fuel showed the TJ24 could produce 13.72 N thrust, with a thermal efficiency of 16.87%, and thrust fuel specific consumption of 0.102 gram/sec/N. Keywords: turbojet, thrust, thermal efficiency, thrust specific fuel consumption, vaporiser, parametric analysis