Towards simulation of NASA35 axial compressor

Abstract

Purpose

This paper aims to validate and analyse the NASA35 axial compressor performance based on a numerical approach.

Design/methodology/approach

Knowledge about flow property change during compressor operation at high and relatively low speed is still limited. This work provides a numerical approach to address these problems. Validation of numerical methods is proposed to generate confidence the numerical approach adopted, and after that, analysis of compressor performance at different operation conditions is carried out.

Findings

The numerical methods proposed are proved capable in predicting compressor performance. Changes of flow property during compressor operation are discussed and explained.

Research limitations/implications

The current numerical work is carried out based on the first stage of the NASA35 axial compressor, where the interactive effects from adjacent stage are not counted in. Furthermore, the steady-state simulation enforces an averaging of flow at rotor-stator interface, where the transient rotor-stator interaction is removed.

Practical implications

This work validates the numerical methods used in the prediction of NASA35 axial compressor performance, and a similar numerical approach can be used for other turbomachinery simulation cases.

Originality/value

This work reinforces the understanding of axial compressor operation and provides reliable results for further investigation of a similar type of compressor. In addition, details of flow field within the NASA35 compressor during operation are given and explained which experiments still have difficult to achieve.

Citation

Xiang, J., Schlüter, J.U. and Duan, F. (2015), "Towards simulation of NASA35 axial compressor", Aircraft Engineering and Aerospace Technology, Vol. 87 No. 6, pp. 571-583. https://doi.org/10.1108/AEAT-03-2015-0073