摘要:
高超声速推进技术是国际前沿研究，其中双模态超燃冲压发动机的发展受到极大关注。作为超燃冲压发动机的重要部件，隔离段对发动机的性能和高超声速飞行的实现至关重要，其中所涉及的流动机理问题也极为复杂。自从高超声速飞行的概念被提出和论证以来，相关的理论、试验和仿真研究不断取得进展，但是对其中的机理问题研究仍有待进一步深入。本文将从试验研究的角度回顾并综述近年来超燃冲压发动机隔离段的研究进展，结合精细流动测试技术(nano-tracer planar laser scattering)的发展分析了隔离段流场特征，包括了激波串流场复杂的三维时空结构特点、湍流特性、非线性迟滞运动、不启动流场特征以及激波前缘检测等。从风洞设备、隔离段设计、测试技术等方面对隔离段的试验研究进行了分类比较和论述，对今后隔离段试验研究提出了建议。
关键词:
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湍流
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超声速流动
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激波
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测量
Abstract:
Since the concept of hypersonic flight was proposed, progress of the related theory, experiments and simulations has been gained. As an important component of the scramjet engine, the isolator plays a key role in the engine performance and flight success. The flow mechanism it involves is very complicated. In the view point of experimental research, this paper reviews the recent progress of scramjet isolator studies, analyzes the features of the isolator flow based on fine flow diagnosis technique (nano-tracer planar laser scattering, NPLS), including the three-dimensional structures of the shock train flow field, turbulent characteristics, hysteresis motions, unstart flow and shock train leading edge detection. Studies of the isolator flow can be classified and discussed according to the wind tunnel facility, isolator design and measurement techniques. Based on this, suggestions for further research can be proposed.
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