Title page for ETD etd-06062008-154721

Type of Document Dissertation
Author Fuller, Raymond Preston
URN etd-06062008-154721
Title Fuel-vortex interactions for enhanced mixing in supersonic flow
Degree PhD
Department Aerospace Engineering
Advisory Committee
Advisor Name Title
Schetz, Joseph A. Committee Chair
Grossman, Bernard M. Committee Member
Nejad, Abdollah S. Committee Member
Ng, Fai Committee Member
Simpson, Roger L. Committee Member
  • supersonic
  • injection
  • vortex
  • mixing
  • aerodynamic
  • ramp
Date of Defense 1996-08-05
Availability restricted

An experimental investigation was conducted to compare the supersonic mixing performance between a novel aerodynamic ramp injector and a physical ramp injector. The aerodynamic ramp injector consisted of nine, flush-wall jets arranged to produce multiplicative fuel-vortex interactions for mixing enhancement in a supersonic main flow. The physical ramp injector was a previously optimized and tested swept-ramp design. Test conditions included a Mach 2.0 freest ream of air with a Reynolds number of3.63 x 107 per meter and helium injection with jet-to-freestream momentum flux ratios of 1.0 and 2.0. Planar-laser Rayleigh scattering and conventional probing techniques including species composition sampling were employed to interrogate the flow field at several downstream locations. Results show that with increasing jet momentum, the aero-ramp exhibited a significant increase in penetration while the physical ramp showed no discernible change. The near-field mixing of the aero-ramp was superior to that of the physical ramp. At the higher jet momentum, the far-field mixing of the aero-ramp was comparable to the physical ramp. In all cases, the total pressure losses suffered with the aero-ramp were less than those incurred with the physical ramp. For both injectors, the total pressure losses decreased with increasing jet momentum. Finally, an analytical relationship predicting the Rayleigh scattering intensity as a function of helium concentration, pressure, and temperature was derived and experimentally validated. It is concluded that these results merit further studies and parametric optimization of the aero-ramp or similar configurations. It is also concluded that further studies may be conducted to establish the absolute quantitative nature of the Rayleigh scattering technique.

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