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在典型高超声速飞行工况下,数值模拟分析了高温合金尖楔前缘结构沿气流方向大温度分布梯度将带来严重的热强度问题,产生大温度分布梯度的根本原因是尖楔结构头部区域平均热流密度与后段平板区域平均热流密度之差,而受头部区域热流密度具体分布的影响不大;进而提出了一种低速高/中温双路气流组合热试验方案,并通过数值模拟方法证明了该方案具有两股气流参数可以独立调节分别满足尖楔结构头部驻点区域及后段平板区域大、小两种热流密度的优点,进而解决单喷口低速高温燃气流热模拟试验难题,满足尖楔结构高超声速飞行工况下大温度梯度模拟要求.同时,该方案通过高/中温气源的合理组合搭配可以大大降低尖楔结构热试验所需高温气源发生功率,推广应用于电弧风洞可拓展其热试验范围.
Under typical hypersonic flight conditions, the numerical simulation shows that the large temperature distribution gradient of the wedge leading edge structure of the superalloy along the gas flow will bring about serious thermal strength problems. The root cause of the large temperature gradient is the wedge structure head The difference between the average heat flux density in the region and the average heat flux density in the back plate region is not affected by the specific distribution of the heat flux density in the head region and a combination of low- The method proves that this method has the advantages that two airflow parameters can be independently adjusted to meet the large and small heat flux density in tip stagnation zone and tip slab zone of tip wedge structure respectively, so as to solve the difficult problem of single-jet low temperature and high temperature gas flow thermal simulation test , Which meets the requirement of large temperature gradient simulation under the hinging wedge hypersonic flight conditions.At the same time, the reasonable combination of high / medium temperature gas source can greatly reduce the high-temperature gas source power required for the thermal wedge structure test, which is widely applied in Arc wind tunnel can expand its thermal test range.