Abstract
Presented paper consists detailed mass model of micro gas turbine single spool turbojet in well-known Scheckling design layout (1R/1A). One of major criteria in aviation is weight that is granted by airworthiness requirements. At present, exempt from certification process are RC airplanes or UAV with total take-off weight less than 22.5 kg. From the 70's mass model was added as a part of aero engines design process. Engine weight affects airplane or UAV weight greatly, because it is a source of variety structure loads. Weight reduction efficiency factor, verifying in terms of design quality a micro gas turbine, and the flying object as a system. Developed computational model allows to estimate weight of the components (gas generator shaft, compressor rotor, compressor diffuser, combustor, turbine nozzle, turbine rotor, jet pipe, casings and housings) and whole engine as well. Model inputs are related to technological axisymmetric dimensions obtained from thermo gas dynamic and construction equations, making it easy to use. Obtained results was presented for several micro gas turbines (mSO1-designed by author, FD3-64, TK-50, JF-50, MW-54, KJ-66, AMT Olympus). Advantage of this model allows to avoid time consuming CAD modelling process at design study level. Presented algorithm can be used also in the design of UAV as well as issues related to the preliminary multidisciplinary design and optimization PMDO cases.
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