各种腔基超燃冲压发动机火焰罩方案的数值研究

IF 2.6 Q2 THERMODYNAMICS
Heat Transfer Pub Date : 2025-03-18 DOI:10.1002/htj.23320
Nachiketh Nadig,  Priya, Aditya Gautam, Ajin Branesh Asokan
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引用次数: 0

摘要

由于停留时间有限、燃料-空气混合不完全以及总压损失大,在超燃冲压发动机中实现高效燃烧具有挑战性。传统的空腔式火焰固定器稳定性较好,但往往存在压降过大和燃料利用率低的问题。尽管对空腔几何形状进行了研究,但它们对不同马赫数的影响仍未得到充分探讨。本文研究了7种新型腔体构型,即带内斜面的外围环形腔体、带外斜面的内环形腔体、带外环形腔体的内环形腔体、内外双椭圆腔体、梯形基底内三角形腔体、奇异内三角形阶梯形腔体和外梯形腔体、凹弧内嵌梯形腔体,这些腔体的L/D比均为3,以达到最佳混合和保火效果。通过书目分析选择。通过56次在1.5-5.0马赫范围内的计算流体动力学模拟,设计6的单片内三角阶梯外梯形空腔在峰值静态温度为3700 K时的燃烧效率最高(99.9%),而设计5在峰值静态温度为3300 K时的效率达到99.7%。在设计1、5和6中观察到较高的出口马赫数恢复(2.7-5.02),尽管激波列形成阻碍了较高马赫数的恢复。设计6也获得了最高的湍流动能(70.49 kJ/kg),有助于持续燃烧,而设计3具有最高的h2o质量分数(0.99594)。这些发现强调了腔体几何形状在超燃冲压发动机性能中的关键作用。此外,该研究揭示了线性空腔几何形状(如设计5和6)如何增强再循环和燃料-空气混合,而非线性设计则表现出不同的流动物理和激波结构。通过澄清这些影响,研究推进了用于超音速运输、导弹技术和空间探索的空腔超燃冲压发动机火焰支架的发展。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Numerical Investigation of Various Schemes of Cavity-Based Scramjet Flame Holders

Achieving efficient combustion in scramjet engines is challenging due to limited residence time, incomplete fuel–air mixing, and high total pressure losses. Traditional cavity-based flame holders improve stability but often suffer from excessive pressure drop and inefficient fuel utilization. Despite studies on cavity geometries, their impact across varying Mach numbers remains underexplored. This study investigates seven novel cavity configurations, namely, Peripheral Annular Channel with Internal Ramp, Inner Annular Channel with Peripheral Ramp, Inner Annular with Peripheral Annular Channel, Peripheral and Inner Dual Elliptical Cavity, Trapezoidal-Base Inward Triangular Cavity, Singular Inward Triangular Stepped and Outward Trapezoidal Cavity, and Concave Arc-Inset Trapezoidal Cavity, all with an L/D ratio of 3 for optimal mixing and flame-holding, chosen through bibliographical analysis. Through 56 computational fluid dynamics simulations across Mach 1.5–5.0, the Monolithic Inward Triangular Stepped and Outward Trapezoidal Cavity (Design 6) exhibited the highest combustion efficiency (99.9%) with a peak static temperature of 3700 K, while Design 5 reached 99.7% efficiency at 3300 K. Higher Exit Mach number recovery (2.7–5.02) was observed in Designs 1, 5, and 6, though shock train formation hindered recovery at higher Mach numbers. Design 6 also achieved the highest turbulent kinetic energy (70.49 kJ/kg), aiding sustained combustion, while Design 3 had the highest H₂O mass fraction (0.99594). These findings highlight the crucial role of cavity geometry in scramjet performance. Additionally, this study reveals how linear cavity geometries, like, Designs 5 and 6, enhance recirculation and fuel–air mixing, while nonlinear designs exhibit distinct flow physics and shock structures. By clarifying these effects, the research advances cavity-based scramjet flame holder development for supersonic transport, missile technology, and space exploration.

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来源期刊
Heat Transfer
Heat Transfer THERMODYNAMICS-
CiteScore
6.30
自引率
19.40%
发文量
342
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