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首页> 外文会议>AIAA/ASME/SAE/ASEE joint propulsion conference;AIAA propulsion and energy forum >Analysis of Successful Pulsed Detonation vs. a Deflagration in a Supersonic Combustor Using a C_2H_4-Air Mixture
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Analysis of Successful Pulsed Detonation vs. a Deflagration in a Supersonic Combustor Using a C_2H_4-Air Mixture

机译：使用C_2H_4-空气混合物的超音速燃烧器成功脉冲爆震与爆燃的分析

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A detailed high fidelity numerical experiment is conducted on a 3D hypersonic air-breathing propulsion engine that integrates a small pulse detonator as an innovative concept to aid supersonic ignition. The 3rd-Order unsteady hybrid-LES turbulent analysis replicates an azimuthal slice of the internal flow path to determine its feasibility and performance as a supersonic combustion augmenter. Previous two-dimensional efforts using a hydrogen-oxygen mixture on the same detonator upstream of the cavity supported the initial design concept. Herein, an analogous combustor utilizes a stoichi-ometric C_2H_(4(g))+Air detonation as a means to augment the fuel penetration, mixing characteristics, and early ignition process of a C_2H_(4(g)) fueled supersonic combustor. The pulse detonation process is divided into two parts. First, an asymptotic solution of the hydrocarbon-fueled scramjet is achieved allowing the tube to be filled by the resulting mixture as in a long tubular cavity with an open end. In the second part, the solution inside the tube is replaced by a 1D solution of the pulse, individually calculated. In an instant, the flow properties in the tube are initialized and evolve up to its interface. The mixture has either: 1) fully transitioned from a deflagration to a detonation (Deflagration to Detonation Transition, or DDT), or 2) not transitioned to detonation. The primary objective of this research evaluates and compares the differential effects of the gaseous mixture on the overall performance and pressure recovery across the system whether DDT is achieved or not. Results from the discharge into the supersonic combustor seem to aid the mixing in the cavity and fuel penetration differently in the case of the DDT versus the deflagration; these were compared and analyzed. The numerical simulation assumes finite-rate conditions with a reduced chemical mechanism to model the pulse deonation and the scramjet fuel flow.
机译：在3D高超音速呼吸推进发动机上进行了详细的高保真数值实验，该发动机集成了小脉冲雷管作为辅助超音速点火的创新概念。三阶非定常混合LES湍流分析复制了内部流动路径的方位角切片，以确定其作为超音速燃烧增强器的可行性和性能。之前在腔体上游的同一雷管上使用氢-氧混合物进行的二维研究支持了最初的设计理念。在本文中，类似的燃烧器利用化学计量的C_2H_（4（g））+空气爆震作为增加C_2H_（4（g））燃料的超音速燃烧器的燃料渗透，混合特性和早期点火过程的手段。脉冲爆震过程分为两部分。首先，实现了以烃为燃料的超燃冲压发动机的渐近解决方案，使管子能够像在带有开口端的长​​管状腔体中那样被所形成的混合物填充。在第二部分中，将管内的溶液替换为单独计算的一维脉冲溶液。瞬间，管中的流动特性被初始化并发展到其界面。混合物具有：1）从爆燃完全过渡到爆震（爆燃到爆轰过渡或DDT），或2）没有过渡到爆轰。这项研究的主要目的是评估和比较气体混合物对整个系统的整体性能和压力恢复的不同影响，无论是否实现了滴滴涕。在DDT与爆燃的情况下，排放到超音速燃烧器中的结果似乎有助于腔内混合和燃料渗透的方式有所不同。对它们进行了比较和分析。数值模拟假设采用有限化学条件的有限速率条件，以模拟脉冲去离子和超燃冲压燃料流。

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