Combustion of liquid propellants

Combustion of Liquid Propellants and the Use of Similarity Principles in Theoretical Combustion Research... 

D. Altman and S. S. Penner, Combustion of Liquid Propellants, Princeton University Press, Princeton, N.Y., 1956. 

The applicable theoretical and experimental papers on atomization, evaporation, and combustion of liquid propellants are summarized and applied to the problem of the combustion of atomized liquid propellants. The available reports on ignition delay, performance, and stability limits for liquid propellant combustors are reviewed and the data correlated in accordance with the experimental data and theoretical concepts summarized above. The results of this survey indicate that more rapid ignition, higher performance, and lower stability limits are achieved by fine atomization and that the effects of unstable combustion and erosive burnout of combustion chamber walls are minimized by coarser atomization. Several atomization criteria for optimum performance are proposed as a consequence of this investigation. 

Crocco S.I.Cheng, "Theory of Combustion Instability in Liquid Propellant Rocket Motors , Butterworths, London(1956) 23)D.Altroan S.S. Penner, "Combustion of Liquid Propellants , in Vol 2 of B.Lewis et al, "High-Speed Aerodynamics and Jet Propulsion Combustion Processes ,... 

Suzuki, T., Chiu, H. H., "Multi-Droplet Combustion of Liquid Propellants, ... 

If the injection of a readily vaporized liquid into a motor could be shown to terminate the combustion of the propellant, the development of such a system for operational motors would offer a number of significant advantages. In fact, several studies (A12, Jl, M8, N2) have been conducted to demonstrate... 

Investigation of Transverse Mode Combustion in Liquid Propellant Rocket Motors (PhD Thesis), Princeton Univ, June 1, 1961 E) L.A. Dickinson, "Command Initiation of Finite Wave Axial Combustion Instability in Solid Propellant Rocket Motors , ARS 32, 643(1962) F) S.Z. Burstein V.D. Agosta, "Combustion Instability Non-Linear Analysis of Wave Propagation in a Liquid Propellant Rocket Motor , Polytechnic Institute of Brooklyn, Dept of Mechanical Engineering,... 

Theoretical Studies of Liquid-Propellant Rocket Instability , Ibid, pp 1101-28 Pj) G.A. McD. Cummings A.R. Hall, "Perchloric Acid Flames Premixed Flames With Methane and Other Fuels , Ibid, 1365-72 P2) D.J. Carlson, Emittance of Condensed Oxides in Solid Propellants Combustion Products , Ibid, 1413-24 Qj) Ibid, "Perchloric Acid Flames Some Flame Temperatures and Burning Velocities , Ministry of Aviation,... 

Aliphatic hydrocarbons petrol, paraffin. In the U.S.A. several types of combustibles for liquid propellant jet aircraft are used. One of them, i.e. JP-4, is employed for rocket propulsion, with nitric acid as an oxidizing agent (it can also be used with hydrogen peroxide or liquid oxygen). The specification of JP-4, is as follows ... 

Method for detg burning rates of liquid rocket proplnts) 17)M.Summerfield, JetPropn (JARS) 21, 108-14(1951), "A Theory of Unstable Combustion in Liquid Propellant Rocket Systems ... 

The Mechanism of Combustion of Solid Propellants in "Selected Combustion Problems-Fundamentals and Aeronautical Applications , AGARD Publication, Butterworths, London(1954) 22)S.S. Penner P.P.Datner, "Combustion Problems in Liquid-Fuel Rocket Engines , in 5th Symposium on Combustion, Reinhold, NY(1955), 11-28(A review with 84 refs) 22 a)Anon, "Military Explosives , TM 9-1910(1955), 229 31 22b)L. 

Crocco, L., Theoretical Studies of Liquid-Propellant Rocket Instability Tenth Symp. Int. on Combustion, The Combustion Inst., Pittsburgh, 1965, pages 1101-1128. 

D. E. Rosner, Liquid Droplet Vaporization and Combustion, Section 2.4 of Liquid Propellant Rocket Combustion Instability, D. T. Harrje and F. H. Reardon, eds., NASA SP-194, Washington (1972), 74-100. 

Only chemical propulsion will be further discussed, and in particular, that associated with liquid, solid, and hybrid motors and engines. These motors and engines are uniquely different from other chemical propulsion systems in that they carry on board the necessary propellants, as contrasted to jet engines that rely on atmospheric oxygen for combustion of the fuel. 

The combustion process is carried out in a thrust chamber or a motor case, and the reaction products are momentarily contained therein. The newly formed species are heterogeneous in composition and involve a wide variety of low molecular weight products. The temperature of these products is generally high, and it ranges from about 2,000°F (1,100°C) in gas generators to well over 8,000°F in advanced liquid propellant engines. The combustion products leave the chamber and are directed and expanded in a nozzle to obtain velocities from about 5,000 to 14,000 ft/sec. 

L. Crocco and S. Cheng. Theory of Combustion Instability in Liquid Propellant Rocket Motors. Butterworths, London, 1956. 

L. Crocco. Aspects of combustion instability in liquid propellant rocket motors, part 1. /. Am. Rocket Soc., 21 163-178, 1951. 

F.E.C. Culick and V. Yang. Overview of combustion instabilities in liquid-propellant rocket engines. Liquid Rocket Engine Combustion Instability. Progress in Astronautics and Aeronautics, Vol. 169, pp. 3-37, Chapter 1, AIAA, 1995. 

Ignition and Combustion of Solid Rocket Propellants Robert S. Brown, Ralph Anderson, and Larry J. Shannon Gas-Liquid-Particle Operations in Chemical Reaction Engineering Knud Ostergaard... 

Liquid resoles, chemical shifts of methylene carbons in, 18 775t Liquid rocket propellants, 10 726-727 Liquid rubber technology, 9 563-566 Liquid runaround systems, 10 144 Liquids. See also Nonideal liquid mixtures boiling points of, 24 2841 bulk handling of, 18 5 combustion of, 13 174 degree of fire hazardousness of, 24 284 density of, 24 282... 

The liquid propellant rocket combination nitrogen tetroxide (N204) and IJDMII (unsymmetrical dimethyl hydrazine) has optimum performance at an oxidizer-to-fuel weight ratio of 2 at a chamber pressure of 67 atm. Assume that the products of combustion of this mixture are N2, C02, H20, CO, H2, O, H, OH, and NO. Set down the equations necessary to calculate the adiabatic combustion temperature and the actual product composition under these conditions. These equations should contain all the numerical... 

Diffusion flames can best be described as the combustion state controlled by mixing phenomena—that is, the diffusion of fuel into oxidizer, or vice versa—until some flammable mixture ratio is reached. According to the flow state of the individual diffusing species, the situation may be either laminar or turbulent. It will be shown later that gaseous diffusion flames exist, that liquid burning proceeds by a diffusion mechanism, and that the combustion of solids and some solid propellants falls in this category as well. 

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