自适应康达喷气控制在高负荷压气机中的试验研究

doi:10.7527/S1000-6893.2023.28883

Abstract

Abstract:

Future development of aeroengines requires continuous increase in the compressor stage load， which will result in strong secondary flows such as corner separation and boundary layer flow separation in the compressor. In this paper， a new Adaptive Coanda Jet Control （ACJC） technology is proposed to intelligently and efficiently restrain the flow separation in the compressor and improve the diffusion capacity of the compressor， and the stable and efficient operation range of the highly loaded compressor is dramatically broadened. To construct the ACJC system and verify its control effect in a highly loaded compressor， we first employ a highly loaded compressor stator cascade constructed based on the Zierke & Deutsch airfoil to investigate the ACJC system， with the diffusion factor of 0.66 at the design point. Then， the variance analysis method， principal component analysis method and neural network algorithm are adopted to establish the incidence angle prediction model and the optimal injection mass flow rate prediction model of the Coanda jet flap. Finally， an experimental platform based on the ACJC system is built to verify the effectiveness and accuracy of flow separation control for the highly loaded cascade. The experimental results indicate that the ACJC system can accurately predict the incidence angle and adjust the Coanda jet mass flow rate in real time at different incidence angles and different incoming Mach numbers. In addition， compared to the cascade without the ACJC system at the incidence angel of 5°， the total pressure loss coefficient is reduced by 11.5%， 9.8% and 8.0% for incoming Mach numbers of 0.4， 0.5 and 0.6， respectively.

Key words: aeroengine, highly loaded compressor, adaptive Coanda jet, flow control, total pressure loss

CLC Number:

V231.3

Jian ZHANG, Min ZHANG, Juan DU, Weiliang HUANG, Chaoqun NIE. Experimental investigation into adaptive Coanda jet control in highly loaded compressor[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(22): 128883-128883.

Figures/Tables 19

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参数	数值
栅距/mm	37.7
弦长/mm	80.8
展弦比	1.61
安装角/（°）	20.5
弯角/（°）	65
进口几何角/（°）	53
出口几何角/（°）	-12

参数	数值
马赫数	≤1.0
进口气流角/（°）	20~90
总压波动范围/%	±0.3
气流角波动范围/（°）	±0.3
进口湍流度/%	5
稳态压力测量精度/%	±0.05

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Experimental investigation into adaptive Coanda jet control in highly loaded compressor

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