Accession Number:

ADA050051

Title:

Combustion Properties of High Density Fuels.

Descriptive Note:

Final rept. 1 Nov 76-31 Oct 77,

Corporate Author:

MARTIN MARIETTA LABS BALTIMORE MD

Personal Author(s):

Report Date:

1977-11-01

Pagination or Media Count:

35.0

Abstract:

A novel experimental technique has been developed to simulate combustion of liquid propellants in rocket engines. The method uses an ultrasonic nebulizer coupled to the downstream end of a shock tube, which is equipped with visible, infrared, and pneumatic monitoring devices. This system was used to initiate RJ-5 mist combustion in oxygen at around 1500 K with an associated reflected shock pressure of about 2 atm. Under these conditions, the ignition delay of RJ-5 droplets with a mean particle diameter of about 3 micron was 200 micro sec, whereas ignition delay of RJ-5 vapor in the same experiment was very short less than 1 micro sec. The droplet ignition delay decreased with increasing temperature and was approximately 100 micro sec at 1700 K. Author

Subject Categories:

  • Combustion and Ignition
  • Liquid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE