Optimization and off-design calculations of a turbojet engine using the hybrid ant colony – particle swarm optimization method

Abstract

Purpose

The purpose of the paper is to present component matching and off-design calculations using generic components maps.

Design/methodology/approach

Multi objective hybrid optimization code is integrated with turbojet function code. Both codes are developed for the research study. Initially, methodology is applied on a numerical propulsion system simulation (NPSS) example engine cycle calculations. Effect of matching constants are shown. Later, component matching and application is done on JetCat engine. Calculations are compared with measured test data. And additional operating conditions are calculated using the matched component constants.

Findings

Obtained matching constants provided very good results with NPSS example and also JetCat test measurements. Optimization algorithm is practical for turbojet engine component matching and off-design calculations. Off-design matching provides information about the turbine and exhaust areas of an unknown turbine engine. Thus it is possible to perform off design calculations at various operating conditions. Finding detailed turbine maps is difficult than finding compressor maps. In that case characteristic turbine curve may be a good alternative.

Research limitations/implications

Selected component maps and the target engine components should be similar characteristics. For a one/two stage turbine, characteristic curves can be applied. Validation should be extended on different type of compressor and turbines.

Practical implications

Operators and researchers usually need more information about the available turbojet engines for increasing the effective usage. Generally, manufacturers do not provide such detailed information to public. This study introduces an alternative methodology for engine modeling by using generic component maps and thus obtaining information for off-design calculations. User is flexible for selecting/scaling the compressor and turbine maps.

Originality/value

A hybrid optimization code is used as a new approach. It can be used with other engine functions; for instance functions corresponding to turboshaft or turbofan engines, by modifying the engine function. Number of input parameters and objective functions can be modified accordingly.

Citation

Piskin, A., Baklacioglu, T. and Turan, O. (2022), "Optimization and off-design calculations of a turbojet engine using the hybrid ant colony – particle swarm optimization method", Aircraft Engineering and Aerospace Technology, Vol. 94 No. 6, pp. 1025-1035. https://doi.org/10.1108/AEAT-08-2021-0247