Combustor design, test and thermodynamic analysis for a small scale turbojet engine

In this thesis; design, test and thermodynamic analysis of a through flow combustor that has an air-blast fuel-air injector fuel supply system for 400 N thrust level turbojet engine is analyzed. Thesis study includes conceptual, preliminary and detailed design phases of a through flow combustor. Within the present studies, an atmospheric combustor test rig, its first kind in the country, has been designed and built in order to carry out the performance tests of the combustor. As a result of the conducted experiments in the test system; combustor pressure drop, exit gas temperature profile, emission profiles and liner metal temperatures have been experimentally measured and compared with theoretical calculations. Moreover; in scope of this study, an original flowpath design code, PreCoDe, has been developed and validated to perform preliminary design calculations in a more effective and faster way. The numerical calculations calculated by software predict a peak liner metal temperature of 953 K while thermal paint results show a temperature of 969 K that indeed shows a good agreement between the predictions and measurements. Finally, exergy calculations have been performed based on the experimental data and combustor exergy efficiency has been found as 49.4 %. The theoretical and experimental research activities carried out within the scope of the present thesis should greatly enhance further research and development studies of gas turbine combustor in our country by performed theoretical calculations, designed test system and conducted experimental studies.