Effects of Hybrid Diffuser in Axial-Flow Jet Engine Combustor

It is believed that the turbine engine plays a vital role in the performance of aircraft. Most jet engines nowadays use the axial compressor. In axial-flow compressors, the rising pressure through each stage is dependent on the axial flow velocity. A high axial velocity is essential to achieve the design pressure with the minimum number of stages. Thus, before the combustion can proceed, the air velocity must be reduced to about 20% of the compressor outlet velocity. This depletion is accomplished by fitting a diffuser between the compressor outlet and the upstream end of the liner. Throughout much research into diffuser performance, it has been shown that the operation depends particularly on the flow. Besides, there are several problems that could result in the loss of its efficiency. This study will focus on increasing the diffuser performance of a hybrid type one via pressure-recovery coefficient C_p and loss coefficient λ.