Ignition and Combustion of Multiphase Fuels in a High Speed Air Stream

Ignition and Combustion of Multiphase Fuels in a High Speed Air Stream
Author: Stephen Schmotolocha
Publisher:
Total Pages: 63
Release: 1971
Genre:
ISBN:

An investigation of some basic flow and combustion characteristics of storable fuels was performed. The work is concerned with the injection, mixing, and chemical reaction processes associated with direct injection of metallized slurries in a high speed air stream. Experiments were performed in a direct connect constant area combustor supplied by a Mach 2 air stream at pressure levels of approximately 1 atm. Penetration and spray formation observations were made at ambient (530R) total temperatures whereas mixing and combustion tests were performed for temperatures ranging from 1500R up to approximately 3500R. The fuels examined in the current study were a magnesium-hexane slurry and a boron-magnesium-hexane slurry. Emphasis was on the Mg/Hex slurry although some revealing preliminary tests were performed for the B/Mg/Hex fuel. The results include the observation that autoignition of the Mg/Hex slurry occurs at about 2600R total temperature and is the same as the pure hexane case; staged ignition and combustion was generally observed with the hydrocarbon igniting first, followed by the metal oxidation process; combustion efficiencies of over 90% were obtained, and the preliminary boron/magnesium/hexane tests indicate that above a certain temperature its performance is superior to the Mg/Hex slurry. (Author).

Ignition of Liquid Fuels in Supersonic Air Streams

Ignition of Liquid Fuels in Supersonic Air Streams
Author:
Publisher:
Total Pages: 80
Release: 1978
Genre:
ISBN:

An experimental study of the ignition of liquid fuels injected transverse to a hot supersonic (M=1.65) air stream was conducted. The liquids considered were kerosene, CS2 and water as an inert control. The major variables were: air stagnation temperature in the range 1500 to 2300 F, injectant flow rate and injection angles from 90 to 45 deg upstream. The experimental observations were: temperature measurements on the wall near the injector and in the flow downstream of injection, self-luminosity photographs and infrared photographs taken with a Thermographic camera. Special attention was directed at the behavior of the liquid layer that had previously been found to form near the injector. No unequivocal evidence of ignition of either fuel was found for normal injection at these conditions. However, clear evidence of ignition of CS2 was found for the upstream injection angle for T sub o> or = 2030 F and 80

NASA SP.

NASA SP.
Author:
Publisher:
Total Pages: 448
Release: 1984
Genre: Aeronautics
ISBN: