Advances in critical technologies for hypersonic and high-enthalpy wind tunnel

Hypersonic and high-enthalpy wind tunnels and their measurement techniques are the cornerstone of the hypersonic flight era that is a dream for human beings to fly faster, higher and further. The great progress has been achieved during the recent years and their critical technologies are still in an urgent need for further development. There are at least four kinds of hypersonic and high-enthalpy wind tunnels that are widely applied over the world and can be classified according to their operation modes. These wind tunnels are named as air-directly-heated hypersonic wind tunnel, light-gas-heated shock tunnel, free-piston-driven shock tunnel and detonation-driven shock tunnel, respectively. The critical technologies for developing the wind tunnels are introduced in this paper, and their merits and weakness are discussed based on wind tunnel performance evaluation. Measurement techniques especially developed for high-enthalpy flows are a part of the hypersonic wind tunnel technology because the flow is a chemically reacting gas motion and its diagnosis needs specially designed instruments. Three kinds of the measurement techniques considered to be of primary importance are introduced here, including the heat flux sensor, the aerodynamic balance, and optical diagnosis techniques. The techniques are developed usually for conventional wind tunnels, but further improved for hypersonic and high-enthalpy tunnels. The hypersonic ground test facilities have provided us with most of valuable experimental data on high-enthalpy flows and will play a more important role in hypersonic research area in the future. Therefore, several prospects for developing hypersonic and high-enthalpy wind tunnels are presented from our point of view.     

空心气冷低压涡轮动叶气热耦合数值模拟

以空心气冷低压涡轮动叶为研究对象,采用高质量的流体域和固体域网格控制技术,带转捩模型的双方程SST湍流模型,开展了基于CFD方法的叶片气热耦合问题研究。获得了不同冷气流量比(分别为1.0%,1.38%,1.8%和2.2%)、温比(分别为2.1,2.25,2.3,2.4和2.5)和压比(分别为1.4,1.6和1.8)对叶片换热特性的影响规律,设计状态中截面按弧长平均的叶片壁面金属温度计算值较试验值偏小0.3%,气热耦合计算的叶片壁面温度分布与试验结果吻合良好,验证了气热强耦合计算方法的精度,为涡轮叶片温度场分析提供了一种有效的方法。     

Measurements of heat transfer and pressure in a trailing edge cavity of a turbine blade

 An experimental investigation is conducted to obtain the heat transfer and pressure drop data for an integral trailing edge cavity test section that simulates a novel turbine blade's internal cooling passage with bleed holes. Local heat transfer is measured on both the suction and pressure sides by a transient liquid crystal technique, while pressures at six positions are recorded by pressure calibrators. Moreover, flow characteristic and its effect on heat transfer are analyzed for conditions with or without bleed flow. The experimental results show that, in the cases with bleed flow, local heat transfer on the pressure side exceeds that on the suction side in the first and second channels. In the cases without bleed flow, in the first and third channels, local heat transfer on the suction side weakens whilst it increases significantly on the pressure side. For the second channel, non-bleed condition leads to a more balanced heat transfer distribution between the upstream and downstream channel. Besides, after the bleed holes are blocked, heat transfer in the first bend region on the suction side declines sharply, while the opposite phenomenon occurs for the second bend region on the pressure side. In both bleed and non-bleed cases, the total pressure of six measurement positions decreases continuously along the channel at the same Reynolds number and it promotes for higher Reynolds number. Among all the measurement points, under the same flow rate condition, the highest speed occurs at Position 5, which also shows the maximum difference between the total and static pressures. When the bleed holes are blocked, the total pressure at each measurement position appears to increase.     

舱内航天服散热途径分析

为分析常压下航天员穿着舱内航天服时的散热性能，６名健康男性青年按二次复合设计分组共进行２４人次试验，经分析计算了获得了服装各散热途径的散热率随通风气源参数及人体活动水平变化的数学模型。对影响服装散热性能的因素及服装散热特性进行了分析讨论。     

热管式表面温度计检定装置

叙述一种热管式表面温度计检定装置的原理、结构。该装置可用于航天领域在实验室条件下对表面温度计的检定。     

热流限制下的最优气动力辅助变轨

以变轨能量消耗最小为优化目标，应用极大值原理研究了飞行过程受热流限制和升力系统约束下的气动力辅助共面变轨问题，飞行过程成分第一自由弧段，约束弧段，第二自由弧段三个部分，讨论了升力系数的最优表达式，分析了飞行过程中两种约束的相互作用，给出了约束弧起始位置的角点条件和终端的横截条件下，对不同的初值选取方法讨论了三种计算策略，并给出了数值算例。     

超燃冲压发动机燃烧室主动冷却设计研究

超燃冲压发动机燃烧室主动冷却模型制造和热考核试验的费用高昂、周期长,为了降低试验风险,采用三维计算和经济的验证试验相结合的方法开展了超燃冲压发动机燃烧室主动冷却设计。冷却结构基本参数设计和侧壁冷却流动设计是确定设计方案的两大基础,前者采用三维传热计算结合冷却面板传热验证试验完成,后者采用超临界燃料流动三维并行计算结合水流动验证试验完成。在此基础上,经过多轮的结构设计与三维传热及强度计算评估迭代,确定了最终的燃烧室主动冷却结构。设计的主动冷却燃烧室在来流马赫数2.5,总温1700K条件下成功通过200s热考核试验,表明所采用的设计方法、验证试验和计算工具是有效和可信的。     

轻质隔热纳米孔结构耐烧蚀酚醛材料

在一定温度下,通过改性剂组分与热固性钡酚醛树脂之间热共聚反应,制备了改性酚醛树脂。采
用模压工艺制备出具有目标尺寸和形状的改性酚醛树脂固化物,对该样品分别进行了400 和700℃的炭化处
理,得到了相应的酚醛炭化样品,并测试其密度、失重率、收缩率等特征参数。研究改性剂用量对碳化物特征参
数和性能的影响,如密度、失重率形貌、比表面积、隔热性能、压缩强度等。SEM 研究表明,700℃炭化后样品形
成了“珊瑚状”碳结构,形成了30 ~150 nm 纳米孔。比表面积测试(BET)结果表明其比表面积可达464 m2 / g。
隔热性能与力学性能的测试结果表明,相对于未改性酚醛树脂碳化物,改性酚醛碳化物的热导率降低了
45． 57%,并且保持了较好的压缩强度。     

刚性隔热瓦重复使用性评价研究

为满足未来新型飞行器对隔热材料的需求,将刚性隔热瓦在1 200℃热处理30 min,对其质量稳定性、尺寸稳定性、力学性能、隔热性能以及微观结构等进行了评价.结果表明,热处理20次的质量损失率、xy向线性收缩率、隔热性能以及微观结构变化都很小,仅z向线性收缩率稍大(3.19％).综合来看,1 200℃/30min的使用条件下,隔热瓦能够满足20次的重复使用要求.     

关于对喷水室热工计算公式的分析及修正

通过分析喷水室内水和空气之间的热质交换过程，指出目前采用的热工计算公式的不足，并在此基础上推导出喷水室热平衡方程新公式，对理论教学起到一定的指导作用。