Instantaneous mole-fraction PLIF imaging of mixing layers behind hypermixing injectors

A theoretical model is presented for the determination of the optimum excitation frequency for the production of a fluorescence signal which is proportional to the mole-fraction of the target species while having minimal sensitivity to pressure and temperature variations. The results of the model are applied to the mixing region behind a range of scramjet fuel injectors in a shock tunnel with the aim of obtaining measurements of fuel mole-fraction. Experimental images are presented of fluorescence in streamwise and cross-planes. Analysis of the flowfields produced by a castellated and a plane-base injector shows that the castellated injector has a slight advantage over the plane-base injector, particularly in the near field.

[1]  J. L. Durant,et al.  Collisional quenching corrections for laser-induced fluorescence measurements of NO A2Sigma(+) , 1994 .

[2]  R. J. Stalker,et al.  A study of the free-piston shock tunnel. , 1967 .

[3]  R. Hanson,et al.  Temporally resolved, two-line fluorescence imaging of NO temperature in a transverse jet in a supersonic cross flow. , 1993, Applied optics.

[4]  P. Logan,et al.  Measurements of temperature, density, pressure, and their fluctuations in supersonic turbulence using laser-induced fluorescence , 1987 .

[5]  R. Hanson,et al.  Concentration measurements in a transverse jet by planar laser-induced fluorescence of acetone , 1994 .

[6]  Ephraim Gutmark,et al.  Mixing Enhancement in Supersonic Free Shear Flows , 1995 .

[7]  R. Hanson,et al.  Simultaneous planar measurements of velocity and pressure fields in gas flows using laser-induced fluorescence. , 1988, Applied optics.

[8]  Richard G. Morgan,et al.  Wave Processes in Scramjet Thrust Generation , 1988 .

[9]  I. Vardavas,et al.  Modelling reactive gas flows within shock tunnels , 1984 .

[10]  Frank E. Marble,et al.  Enhanced mixing with streamwise vorticity , 1997 .

[11]  Frank P. Houwing,et al.  A comparison of two hypermixing fuel injectors in a supersonic combustor , 1998 .

[12]  T. Mcintyre,et al.  Comparison of theoretical laser-induced fluorescence images with measurements performed in a hypersonic shock tunnel , 1996 .

[13]  P. Danehy,et al.  Instantaneous PLIF measurement of species mole-fraction in a varying temperature supersonic flow , 1998 .

[14]  S. Gai,et al.  Flow behind castellated blunt-trailing-edge aerofoils at supersonic speeds , 1998, Journal of Fluid Mechanics.

[15]  M. D. Dirosa High-resolution line shape spectroscopy of transitions in the gamma bands of nitric oxide , 1996 .

[16]  P. C. Palma,et al.  Optical and Pressure Measurements in Shock Tunnel Testing of a Model Scramjet Combustor , 1997 .

[17]  R. Hanson,et al.  Planar laser-induced fluorescence imaging of velocity and temperature in shock tunnel free jet flow , 1992 .

[18]  T. Teichmann,et al.  Introduction to physical gas dynamics , 1965 .