基于角度约束松弛的固体ATR进气道改进设计

发布时间：2019-02-13 14:06

【摘要】：为满足高性能弹用固体ATR对入口流场品质的要求,对ATR进气道开展了总体构型论证和几何设计。从5个方面整体论证后,确定弹用固体ATR宜采用后置"X型"四旁侧二元倒置混压式进气道。超声速扩压段综合"给定总压恢复系数法"和"给定气流总转折角法"完成几何设计,避免了单一设计方法中人工调整压缩楔角引起的设计中断;亚声速扩压段采用"方转扇环"构型,有效减弱了"方转扇形"的几何扭曲和出口流场畸变。保证外压缩楔角不变情况下,通过减小内压缩楔角对混压式进气道"内外压缩楔角之和相等"角度约束加以松弛,以及其他辅助措施改进设计后,进气道长度缩短30.28%,抗背压能力、冲压比和总压恢复系数均提升50%左右,出口总压畸变减小55.35%,但流量系数因附面层吸除下降11.58%。
[Abstract]:In order to meet the requirements of solid ATR for high performance projectile to the quality of inlet flow field, the overall configuration demonstration and geometric design of ATR inlet are carried out. After 5 aspects of the whole demonstration, it is determined that the rear "X" four side binary inverted mixed pressure inlet should be used in the missile solid ATR. The supersonic expansion section synthesizes "the method of the total pressure recovery coefficient" and "the method of the total turning angle of the air flow" to complete the geometric design, which avoids the interruption of the design caused by the manual adjustment of the compression wedge angle in the single design method. In the subsonic expansion section, the "square fan ring" configuration is adopted, which effectively attenuates the geometric distortion of the "square rotating fan" and the distortion of the outlet flow field. Under the condition that the external compression wedge angle is invariable, the angle constraint of "equal sum of internal and external compression wedge angles" is relaxed by reducing the internal compression wedge angle, and other auxiliary measures are adopted to improve the design, and the length of the inlet is shortened by 30.28%. The ability of resisting back pressure, stamping ratio and total pressure recovery coefficient are all increased by about 50%, the total pressure distortion of outlet is reduced by 55.35%, but the flow coefficient decreases by 11.58% because of the boundary layer adsorption.
【作者单位】：西北工业大学燃烧热结构与内流场重点实验室;
【分类号】：V435

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