Supersonic Combustion and Burning in Ramjet Combustors.
Abstract
Induction distances, transient pressures, and wave propagation rates were determined in cylindrical tubes for detonation waves in stoichiometric hydrogen-oxygen mixtures initially at one atmosphere and temperatures ranging from 300K down to 123K. The induction distances became considerably shorter as the initial gas temperature was decreased. At temperatures from 500 to 123K the normal burning speed of stoichiometric hydrogen-oxygen mixtures was found to be proportional to the absolute temperature of the unburnt gas. High-strength shock waves were fired into lean hydrogen-oxygen mixtures to study the propagation rates of the flames behind these waves (overdriven detonations). Ignition delay times in hydrogen-nitric oxide mixtures were found to be very long. Stable detonation waves could not be produced in these mixtures. Quantum yields and induction times have been measured in flowing mixtures of hydrogen, oxygen, and chlorine to determine the feasibility of photochemically initiated supersonic combustion. Expressions have been derived to predict the induction times and quantum yields. A method has been developed for calculating the state of the gas behind a normal shock in a shock tube for the case that both the driver and the driven gas undergo chemical changes during the process. Resulst indicate that for dissociating hydrogen calculations based on the use of certain values of the specific heat ratio may be in error by 30% for the calculated particle speed. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1970
- Accession Number
- AD0716855
Entities
People
- Rudolph Edse
Organizations
- Ohio State University