Accession Number : ADA134035

Title :   Shock Tube Study of the Ignition and Combustion of Aluminum.

Descriptive Note : Final rept. 11 Jun 79-10 Mar 82,


Personal Author(s) : Driscoll,J. F. ; Nicholls,J. A. ; Patel,V. ; Khatib-Shahidi,B. ; Liu,T. C.

Report Date : AUG 1983

Pagination or Media Count : 72

Abstract : The goal of this project is to obtain data that will help identify the reaction mechanism and the ignition limits of aluminum at elevated temperatures and pressures. Formidable problems arise when attempting such measurements in rocket motors since conditions are unsteady and not easy to control. Therefore, it was decided to mount a pure aluminum sample to the end wall of a shock tube and to ignite the sample using a reflected shock wave. The pressures and temperatures that can be achieved (40 atm, 5000 K) are typical of rocket motor conditions and are much higher than those obtained in previous studies using incident shock waves in conventional shock tubes. The aluminum sample reacts with a test gas in which the proportions of nitrogen, hydrogen, oxygen and chlorine are the same as found in ammonium perchlorate.

Descriptors :   *Aluminized propellants, *Combustion, *Ignition, *Shock tubes, Chemical reactions, Combustion products, High temperature, Aluminum, Oxidation, Spectroscopy, Reaction kinetics, Experimental design

Subject Categories : Test Facilities, Equipment and Methods
      Combustion and Ignition

Distribution Statement : APPROVED FOR PUBLIC RELEASE