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首页> 外文学位 >Numerical simulation of cantilevered ramp injector flow fields for hypervelocity fuel/air mixing enhancement.
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Numerical simulation of cantilevered ramp injector flow fields for hypervelocity fuel/air mixing enhancement.

机译：悬臂式坡道喷油器流场的数值模拟，用于增强超高速燃料/空气混合。

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Increasing demand for affordable access to space and high speed terrestrial transport has spawned research interest into various air-breathing hypersonic propulsion systems. Propulsion concepts such as the supersonic combustion ramjet (scramjet) and the shock-induced combustion ramjet (shcramjet) utilize oxygen freely available in the atmosphere and thereby substantially reduce the weight penalty of on-board oxidizer tankage used in rocket based systems. Of key importance to the ultimate success of an air-breathing concept is the ability to efficiently mix the fuel with atmospheric air. In the case of a hypersonic air-breather the challenge is accentuated due to the requirement of supersonic combustion. Flow velocities through the combustor on the order of thousands of meters per second provide the fuel and air with only a brief time to adequately combine. Contemporary mixing augmentation methods to address this issue have focused on fuel injection devices which promote axial vortices to enhance the mixing process. Much research effort has been expended on investigation of ramp injectors for this purpose. The present study introduces a new ramp injector design, based on the conventional ramp injector, dubbed the cantilevered ramp injector.; A two-pronged numerical approach was employed to investigate the mixing performance and characteristics of the cantilevered injector consisting of, (1) comparison with conventional designs and (2) a parametric study of various cantilevered injector geometries. A laminar, three-dimensional, multispecies flowsolver was developed in generalized coordinates to solve the Navier-Stokes equations for the flow fields of injected H2 into high-enthalpy air. The scheme consists of an upwind TVD scheme for discretization of the convective fluxes coupled with a semi-implicit LU-SGS scheme for temporal discretization.; Through analysis of the numerical solutions, it has been shown that the cantilevered ramp injector is a viable fuel injection system facilitating enhanced mixing of fuel and air. Comparison with conventional designs have revealed a competitive and, in most cases, superior design in the context of mixing performance. A strong counter-rotating vortex pair generated under the cantilevered injector was shown to be the distinguishing characteristic of this design and largely accounted for improved mixing performance. Results also elucidated the importance of a coupled design approach between the fuel injector and propulsive duct to optimize mixing performance.
机译：人们对可负担的太空访问和高速地面运输的需求不断增长，引起了对各种空气呼吸高超音速推进系统的研究兴趣。诸如超音速燃烧冲压发动机（scramjet）和冲击感应燃烧冲压发动机（shcramjet）之类的推进概念利用了大气中自由提供的氧气，从而大大减少了基于火箭的系统中车载氧化剂罐的重量损失。空气呼吸概念最终成功的关键在于将燃料与大气有效混合的能力。在高超声速空气呼吸器的情况下，由于需要超音速燃烧，因此挑战更加突出。通过燃烧室的流速约为每秒数千米，仅在很短的时间内就可以使燃料和空气充分混合。解决该问题的现代混合增强方法已经集中在燃料喷射装置上，该燃料喷射装置促进轴向涡旋以增强混合过程。为了这个目的，已经在斜面喷射器的研究上进行了很多研究工作。本研究介绍了一种基于常规斜坡喷射器的新型斜坡喷射器设计，称为悬臂斜坡喷射器。采用两方面的数值方法来研究悬臂式喷油器的混合性能和特性，包括（1）与常规设计的比较以及（2）各种悬臂式喷油器几何形状的参数研究。在广义坐标系中开发了一种层状的三维多物种流动解算器，以求解将H 2 注入到高焓空气中的流场的Navier-Stokes方程。该方案包括用于对流通量离散化的迎风TVD方案，以及用于时间离散化的半隐式LU-SGS方案。通过对数值解的分析，已经表明，悬臂式坡道喷射器是可行的燃料喷射系统，有助于增强燃料和空气的混合。与常规设计的比较表明，在混合性能方面，它是一种竞争性产品，并且在大多数情况下是卓越的设计。悬臂式喷油器下产生的强劲的反向旋转涡流对显示出该设计的显着特征，并在很大程度上改善了混合性能。结果还阐明了在燃油喷射器和推进管之间采用耦合设计方法以优化混合性能的重要性。

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