A Computational Study of Characteristics of the JT8D Transonic Single-Stage Axial Compressor Engine in the Test Experiment Context

Enhancement of bypass turbojets depends on the potential of techniques for modelling three-dimensional viscous flows in the flow paths of turbomachine in conjunction with the external flow. These techniques can provide information that complements experimental data. The key stage in the development of these techniques is their validation in the whole range of operating modes on the basis of test experiments. A rational technique is developed, and a computational study is performed to investigate flow fields in a small-scale model of a transonic single-stage axial compressor of the JT8D engine. The calculation and the experimental data are compared. The simulation of a shortened domain shows a good agreement of the calculations with the experiment on mass flow rate and fan total pressure ratio, with a relative error generally not exceeding 1%. Basic requirements to the technique components are formulated along with the directions for its improvement. An analysis of distribution of the total parameters and flow velocity components in the flow path of the compressor is performed for subsequent modeling of the compressor operation in the air intake.

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