Micro gas turbine performance evaluation.

[摘要] ENGLISH ABSTRACT: The performance of the BMT 120 KS micro gas turbine engine is investigatedin this thesis. The study includes component matching of the engine elementsusing compressor and turbine characteristic maps to analyse the engine's performance.Analytical and numerical calculations were used to assess the variousthermodynamic parameters of the engine and loss of engine power exacerbatedby poor performance of the engine components. Engine performancewas modelled using commercial simulation software GasTurb and Flownex SEand an in-house one-dimensional code. Using the numerical computations, acomponent sensitivity and matching analysis was performed for the engine usingthe various engine components. The theoretical performance of the enginewas validated with experimental engine tests. The comparison of engine simulationresults and experimental test data showed a consistent trend. A thrustdifference of between 0.5% and 6% was achieved between the experimentaland simulated results for the baseline engine. The experimental and simulatedexhaust gas temperature of the BMT engine showed differences between 1.4%and 6%. Furthermore, a mean-line turbine design analysis was undertaken tostudy the possibility of improving the performance of the engine's axial turbine.Simulations that made use of the mean-line turbine predicted a thrustof approximately 190 N and exhaust gas temperature of 993 K at a speed of120 000 rpm.

[发布机构] Stellenbosch University