Effects of Internal Nozzle Geometry on Compression-Ramp Mixing in Supersonic Flow
Effects of Internal Nozzle Geometry on Compression-Ramp Mixing in Supersonic Flow
复制标题
内部喷嘴几何形状对超音速流压缩斜坡混合的影响
作者：
Y. Haimovitch;E. Gartenberg;A. S. Roberts;G. Northam
为探索超燃冲压发动机的混合强化技术，在等截面管道内进行了后掠斜板喷油器的流动显示实验研究。主流是马赫数为2的空气，氢燃料由马赫数为1.70的氦气和马赫数为1.63的空气模拟。从乙醇播种氦气或空气的米氏散射被用来可视化模拟燃料流注入到主气流。对六个预处理模拟燃料射流的喷嘴插入件进行了试验，以探索其与斜坡产生的涡流的相互作用。六个喷嘴插入件如下：圆形喷嘴（基线）、在扩散段具有三个面向下游的台阶的喷嘴、具有四个涡流发生器的喷嘴、椭圆形喷嘴、锥形喉部喷嘴和梯形喷嘴。从图像分析推断出不同插入物的混合特性。
An experimental study based on flow visualization has been conducted in a constant-area duct fitted with a swept-ramp fuel injector to explore mixing enhancement techniques for supersonic combustion ramjet (scramjet) engines. The main flow was air at Mach 2, and the hydrogen fuel was simulated by helium injected at Mach 1.70 and by air injected at Mach 1.63. Mie scattering from ethanol-seeded helium or air was used to visualize the simulated fuel flow injected into the main airstream. Six injector nozzle inserts for preconditioning the simulated fuel jet were tested to explore its interaction with the vortical flow produced by the ramp. The six nozzle inserts were as follows: circular nozzle (baseline), nozzle with three downstream facing steps in the divergent section, nozzle with four vortex generators, elliptical nozzle, tapered-throat nozzle, and trapezoidal nozzle. Mixing characteristics of the different inserts were inferred from image analysis.