A Feasibility Study of a High-Speed Burner
GENERAL APPLIED SCIENCE LABS INC WESTBURY NY
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The theoretical analyses, the design, and the experimental verification of a high-speed combustion chamber are described. For turbomachines, this type of burner is used when compressor outflow speed is so high that diffusion to low speed presents severe pressure loss penalties. The present study showed that for a low-mass flow, high-pressure-ratio turbomachine, combined diffuser and combustor losses are minimum for a burner entrance Mach number of about 0.5. The use of the GASL finite-rate chemistry and turbulent mixing programs is discussed along with the combustor modeling and flame spread predicitons. Finally, a series of experiments is described, and burner pressure loss and temperature profiles are shown over a wide range of burner airflow conditions, i.e., pressures from 1 to 11 atmospheres and inlet air temperatures from ambient to 1200 degrees R.
- Combustion and Ignition
- Jet and Gas Turbine Engines