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Numerical optimization of S-shaped intake performance using special cross-sectional profiles

Numerical optimization of S-shaped intake performance using special cross-sectional profiles An intake has to provide air for the engine uniformly with minimum total pressure loss. Nowadays, regarding the usage of S-shaped intakes, optimization of these ducts has been considered. Uniform distribution of flow at the compressor inlet directly influences the engine performance, and non-uniformity of flow increases surge occurrence possibility. Flow separation along the duct causes a reduction of pressure recovery and engine thrust force. This research has optimized an S-shaped intake to reduce the total pressure loss and flow distortion. The genetic algorithm and artificial neural networks have been combined to decrease the computational cost. Two optimizations, using different conditions, have been studied. In the first case, by modifying centerline coordinates and area ratio of sections, new geometries have been produced, which has caused an improvement of 32.5 % in pressure recovery coefficient and a decrease of 35.8% in flow distortion. In the second optimization, the shape of each section has also been changed. Superellipse, egg-shaped and circular profiles are considered as cross-sections of the duct. The second optimization has improved the pressure recovery coefficient by 35.5 % and decreased flow distortion by 39.2 %. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Thermophysics and Aeromechanics Springer Journals

Numerical optimization of S-shaped intake performance using special cross-sectional profiles

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References (19)

Publisher
Springer Journals
Copyright
Copyright © S.H. Sadatpour, A. Madadi, and R. Ahadian 2022
ISSN
0869-8643
eISSN
1531-8699
DOI
10.1134/s0869864322050079
Publisher site
See Article on Publisher Site

Abstract

An intake has to provide air for the engine uniformly with minimum total pressure loss. Nowadays, regarding the usage of S-shaped intakes, optimization of these ducts has been considered. Uniform distribution of flow at the compressor inlet directly influences the engine performance, and non-uniformity of flow increases surge occurrence possibility. Flow separation along the duct causes a reduction of pressure recovery and engine thrust force. This research has optimized an S-shaped intake to reduce the total pressure loss and flow distortion. The genetic algorithm and artificial neural networks have been combined to decrease the computational cost. Two optimizations, using different conditions, have been studied. In the first case, by modifying centerline coordinates and area ratio of sections, new geometries have been produced, which has caused an improvement of 32.5 % in pressure recovery coefficient and a decrease of 35.8% in flow distortion. In the second optimization, the shape of each section has also been changed. Superellipse, egg-shaped and circular profiles are considered as cross-sections of the duct. The second optimization has improved the pressure recovery coefficient by 35.5 % and decreased flow distortion by 39.2 %.

Journal

Thermophysics and Aeromechanics – Springer Journals

Published: Sep 1, 2022

Keywords: S-shaped intake; genetic algorithm; artificial neural network; flow uniformity; pressure recovery

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