Numerical analysis of scramjet combustion chamber under varied strut configuration
摘要
The objective of this paper is to enhance the combustion efficiency of a scram jet engine by varying the design parameters. The two dimensional numerical analysis is carried out with four different strut model using the k epsilon method for this study with the Mach number of 2 to evaluate the combustions efficiency and pressure loss. The results shows that strut model design 4 is providing the maximum efficiency of 99% with the total pressure loss of 3.08043 × 105 Pa compare to other strut model. The novelty of the model is to vary the two parameter like strut configuration along with fuel injection locations to enhance the combustion efficiency with minimum increment of pressure loss at supersonic conditions. This proposed method can be used for scramjet and supersonic related applications.