Accession Number:

AD0731239

Title:

Mixing and Combustion of Hydrogen in a Supersonic Airstream.

Descriptive Note:

Doctoral thesis,

Corporate Author:

SHEFFIELD UNIV (ENGLAND) DEPT OF FUEL TECHNOLOGY AND CHEMICAL ENGINEERING

Personal Author(s):

Report Date:

1971-02-01

Pagination or Media Count:

190.0

Abstract:

The report is concerned with the mixing and combustion of hydrogen in a high enthalpy Mach 3.5 airstream, in which the conditions are such that the combustion process is mixing limited. The high enthalpy conditions are obtained using a combustion driven hypersonic shock tunnel. A gas composition probe having a response time of 0.25 msec. has been constructed and used in contamination and combustion studies. Combustion results have been obtained from a 2-D Mach 3.5 test section using both a mid-stream vortex generating injector and a plain wedge injector. The turbulent mixing characteristics of the two wakes were determined using a semi-quantitative approach which utilizes well established relationships of structural turbulence theory. The results of this analysis showed the importance of the initial turbulence generation on the overall mixing process. Author

Subject Categories:

  • Combustion and Ignition

Distribution Statement:

APPROVED FOR PUBLIC RELEASE