33th Congress of the International Council of the Aeronautical Sciences

05 - Propulsion


C.-A. Phamı, Q.-H. Nguyenı, T.-A. Vuı, N.-V. Nguyenı; ıViettel Aerospace Institute, Viettel Group, Vietnam

The comprehensive multidisciplinary optimization of combustion chamber for small gas turbine engines is summarized and presented. The in-house analysis using CFD and post processing methodology is proposed and verified for the NASA low-cost turbine engine of 650 lbf sea-level static thrust with the key parameters such as combustion efficiency, total-pressure loss, exit-temperature profile, reference velocity. The comparison of experiment data with CFD results (1/12, 1/2 and full scale of combustor chamber) is presented for the radial and circumferential exit temperature profile. The analysis results show very good agreements with the experimental data for the 1/2 and full-scale combustion chamber at the sea-level test conditions from the NASA TM X-2857 report. rnThe proposed methodology is implemented for the 1st combustor prototype while satisfying the requirements. The fabrication and test results of 1st prototype are obtained and enhanced for the next design loop. The proposed methodology shows the feasibility and effectivity of the cost saving and low turnaround time while developing the small and low-cost turbojet engines. rn

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