Design of Reverse Bleed Slot for Curved Axisymmetric Inlet Based on Kantrowitz Criterion and Flow Field Characteristics

Aerospace Pub Date : 2024-07-04 DOI:10.3390/aerospace11070553

Yongzhou Li, Di Sun, Xinhui Tian, Yiqi Yuan, Xisheng Luo, Kunyuan Zhang

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Abstract

Conventional forward bleed slots reduce the hypersonic inlet starting Mach number but suffer from excessive flow leakage after restart. This paper proposes a novel reverse bleed slot design method for curved axisymmetric inlets of a solid-fuel scramjet. Leveraging the Kantrowitz criterion and detailed flow analysis, the method optimizes bleed slot placement, number, area, and angle. Results show superior aerodynamic performance by placing slots in the non-starting region of the internal compression section, considering both unstarted flow and separation bubble dynamics during restart. Each bleed slot area is calculated successively down-stream based on the Kantrowitz criterion. Finally, the effects of bleed slot angle have been extensively studied. The key inlet performance reaches its optimum at a slot angle of approximately 130°, achieving a significant reduction in the starting Mach number (from 4.80 to 3.65) and a 50% decrease in bleed flow rate compared to the forward slot design. This method demonstrates its feasibility and effectiveness, enabling substantial improvement in inlet starting performance with minimal flow loss.

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基于 Kantrowitz 准则和流场特征的曲线轴对称进水口反向排放槽设计

传统的正向放气槽可降低高超音速进气道的起始马赫数，但在重新启动后会出现过多的气流泄漏。本文针对固体燃料扰流喷气发动机的曲面轴对称进气口提出了一种新颖的反向放气槽设计方法。利用 Kantrowitz 准则和详细的流动分析，该方法优化了放气槽的位置、数量、面积和角度。结果表明，考虑到重新启动过程中的未启动流和分离气泡动力学，在内部压缩段的非启动区域放置放气槽具有优异的气动性能。根据 Kantrowitz 准则，每个放气槽的面积都是顺流连续计算的。最后，还对放气槽角度的影响进行了广泛研究。与正向开槽设计相比，开槽角度约为 130°时，关键入口性能达到最佳，起始马赫数显著降低（从 4.80 降至 3.65），排气流量减少 50%。这种方法证明了其可行性和有效性，能够在流量损失最小的情况下大幅提高进气口的启动性能。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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Aerospace

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