Numerical evaluation on aerodynamic design of pressure-regulating valve in trisonic intermittent wind tunnel

Due to the requirements of the working environment, the marine axial flow control valve needs to reduce the noise as much as possible while ensuring the flow capacity to meet the requirements. To improve the noise reduction effect of the axial flow control valve, this paper proposes a Stacking integrated learning combined with particle swarm optimization (PSO) method to optimize a multi-stage step-down sleeve of the axial flow control valve. The liquid dynamic noise and flow value of the axial flow control valve are predicted by computational fluid dynamics. Based on the preliminary evaluation of its performance, the structural parameters of the multi-stage pressure-reducing sleeve are parameterized by three-dimensional modeling software. The range of design variables is constrained to form the design space, and the design space is sampled by the optimal Latin hypercube method to form the sample space. An automated solution platform is built to solve noise and flow values under different structural parameters. The Stacking method is used to fuse the three base learners of decision tree regression, Kriging, and support vector regression to obtain a structural optimization fusion model with better prediction accuracy, and the accuracy of the fusion model is evaluated by three different error metrics of coefficient of determination (R2), Root Mean Squared Error, and Mean Absolute Error. Then the PSO particle swarm optimization algorithm is used to optimize the fusion model to obtain the optimal structural parameter combination. The optimized multi-stage depressurization structure parameters are as follows: hole diameter t1 = 3.8 mm, hole spacing t2 = 1 mm, hole drawing angle t3 = 6.4°, hole depth t4 = 3.4 mm, and two-layer throttling sleeve spacing t5 = 4 mm. The results show that the peak sound pressure level of the noise before and after optimization is 91.32 dB(A) and 78.2 dB(A), respectively, which is about 14.4% lower than that before optimization. The optimized flow characteristic curve still maintains the percentage flow characteristic and meets the requirement of flow capacity Kv ≥ 60 at the maximum opening. The optimization method provides a reference for the structural optimization of the axial flow control valve.

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Prediction of the performance of the pressure-regulating valve in a large high-speed jet wind tunnel

Luo,

Huang,

Lin

et al. 2023

AIP Advances

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Prediction of the performance of the pressure-regulating valves in a large high-speed jet wind tunnel is important for obtaining and adjusting a high-quality flow field in the test section. In this work, we proposed a prediction method that corrects the theoretical characteristics of the pressure-regulation of the valve based on the experimental testing data of the ratio between the high- and low-pressure of the valve. The current method was validated for a given Mach number of 0.8, and the results showed that compared with the theoretical characteristics, the displacement deviation of the spool was reduced by 9.84%, and the total pressure deviation of the settling chamber was reduced by 43.61%. The results also show that compared with the single low-pressure ratio correction characteristic, the displacement deviation of the spool was reduced by 0.94%, and the total pressure deviation of the settling chamber was reduced by 3.4%. This method can consider the variation of the pressure loss for different pressure ratios and improve the pressure prediction of the valve.

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Numerical evaluation on aerodynamic design of pressure-regulating valve in trisonic intermittent wind tunnel

Cited by 4 publications

References 11 publications

Flow field control for 2-meter high-speed free-jet wind tunnel

Flow field control for 2-meter high-speed free-jet wind tunnel

Structural optimization of multistage depressurization sleeve of axial flow control valve based on Stacking integrated learning

Prediction of the performance of the pressure-regulating valve in a large high-speed jet wind tunnel

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