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

Abstract

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.