Accession Number : ADB100941
Title : Laboratory Methods for Measuring Combustion Response Functions.
Descriptive Note : Technical rept. 1 May 67-10 Oct 85,
Corporate Author : CHEMICAL PROPULSION INFORMATION AGENCY LAUREL MD
Personal Author(s) : Strand,L. D. ; Brown,R. S.
Report Date : MAR 1986
Pagination or Media Count : 28
Abstract : Evaluation of the combustion stability of a solid-propellant rocket requires information on the dynamic combustion properties of the propellant, particle-size distributions of condensed-phase combustion products, and the mean flow and acoustic behavior in the gas chamber. Analytical methods for estimating the flow on acoustic behavior have been used, but no such methods have been developed to predict either combustion dynamics or the particle size distributions. Hence, a series of laboratory test methods has been explored for obtaining the necessary data. Experimental methods for measuring the dynamic combustion properties (acoustic admittance or response function) or solid-propellant rocket motors are reviewed. The pressure-coupled methods include the T-burner, the rotating valve apparatus, the impedance tube, the microwave burner, and the magnetic flowmeter. The velocity-coupled methods comprise the velocity-coupled T-burner, the dual-rotating apparatus, and the velocity-coupled impedance tube. Also considered are methods for measuring the particle size distribution of condensed-phase combustion products. Keywords: Combustion chambers; Combustion stability.
Descriptors : *COMBUSTION CHAMBERS, *COMBUSTION STABILITY, COMBUSTION PRODUCTS, TEST METHODS, TEST EQUIPMENT, MAGNETIC DEVICES, MICROWAVE EQUIPMENT, ACOUSTICS, ADMITTANCE, CHAMBERS, GASES, LABORATORY PROCEDURES, FLOWMETERS, MAGNETIC FIELDS, COMBUSTION, ACOUSTIC PROPERTIES, DYNAMICS, IMPEDANCE, TUBES, LABORATORY TESTS, FLOW, MEAN, BURNERS, FUNCTIONS, MEASUREMENT, DISTRIBUTION, PARTICLE SIZE, SOLID PROPELLANT ROCKET ENGINES, MICROWAVES
Subject Categories : Test Facilities, Equipment and Methods
Combustion and Ignition
Solid Rocket Propellants
Distribution Statement : APPROVED FOR PUBLIC RELEASE