Abstract
The turbine coolant collection/distribution chamber, as an important component of the secondary air system, undertakes the task of collecting and distributing coolant for guide vanes. To improve the outflow uniformity and reduce the flow loss, a multiobjective optimization method is developed for geometric parameters of turbine chamber. Numerical experiments were designed by Latin hypercube sampling and solved by the CFD method. Based on these data sampling, least square support vector machine (LS-SVM) was used for the surrogate model, and a kind of chaotic optimization algorithms was used for searching for the Pareto solution set. The results show that the streamline change in the optimized chamber is smoother, and the jet impingement effect of the coolant from the inlet tube was significantly weakened. At the condition that each goal has the weight of 0.5, the optimized discharge coefficient increases by 26%, and the outflow nonuniformity decreases by 79% compared with reference structure.
Highlights
With the development of aviation gas turbine engine, the compressor pressure ratio and turbine inlet gas temperature show continuous increase, and the working environment of high-temperature components becomes worse and worse [1]
Zhang et al.[7] investigated the influence of geometric parameters including inlet diameter, outlet hole diameter, and circumferential spacing between inlet and outlet on the outflow distribution characteristics in the turbine chamber. Their CFD and experimental results both show that at the constant pressure ratio, the geometric parameters of turbine chambers have an obvious effect on outflow nonuniformity
The outflow distribution characteristics of turbine chamber can be affected by geometric parameters and incoming thermal parameters obviously
Summary
With the development of aviation gas turbine engine, the compressor pressure ratio and turbine inlet gas temperature show continuous increase, and the working environment of high-temperature components becomes worse and worse [1]. The flow loss in the turbine chamber directly affects the working efficiency of the engine. The total flow rate increases with the increase of the chamber height and inlet/outlet pressure ratio, but the change of these two parameters will not affect the outflow distribution law. Zhang et al.[7] investigated the influence of geometric parameters including inlet diameter, outlet hole diameter, and circumferential spacing between inlet and outlet on the outflow distribution characteristics in the turbine chamber. Their CFD and experimental results both show that at the constant pressure ratio, the geometric parameters of turbine chambers have an obvious effect on outflow nonuniformity.
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