Liquid propellants combustion

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. 

D.T. Harrje and F.H. Reardon. Liquid propellant rocket combustion instability. Technical Report SP-194, NASA, Washington, DC, 1972. 

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. 

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... 

Law, C. K. 1995. Vaporization and combustion of high-energy-density liquid propellants. 35th Israel Annual Conference on Aerospace Science Proceedings. Israel. 

Addnl Refs A) L. Crocco S.I. Cheng, "Theory of Combustion Instability in Liquid Propellants , AGARD Monograph No 8, Butter-worths, London(1956) B) J.E. Crump ... 

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,... 

Sirignano L. Crocco, "A Shock Wave Model of Unstable Rocket Combustors , AIAA 2, 1285(1964) I) B.T. Zinn, "A Theoretical Study of Nonlinear Transverse Combustion Instability in Liquid Propellant Rocket Motors (PhD Thesis)> Princeton Univ, May 1966 J) C.E. Mitchell, "Axial Mode Shock Wave Combustion Instability in Liquid Propellant Rocket Engines (PhD Thesis), Princeton Univ, NASA CR 72229(1967) K) E.L. 

M) L. Crocco, "Research on Combustion Instability in Liquid Propellant Rockets , 12thSympCombstn, Poitiers, France, July 14-20, 1968 (published in 1969), pp 85-99... 

N) E.W. Price, "Recent Advances in Solid Propellant Combustion Instability , Ibid, pp 101-113 O) G.A. Marxman C.E. Wooldridge, "Finite-Amplitude Axial Instability in Solid-Rocket Combustion , Ibid, pp 115-27 P) W.A. Sirignano, "A Theory of Axial-Mode Shock-Wave Oscillations in a Solid-Rocket Combustor ,Ibid, pp 129-37 Q) B.T.Zinn C.T. Saveli, "A Theoretical Study of Three-Dimensional Combustion Instability in Liquid-Propellant Rocket Engines , Ibid, pp 139-47 R) R.J. Priem E.J. Rice, "Combustion Instability with Finite Mach Number Flow and Acoustic Liners , Ibid, pp 149-59 S) M.W. Thring, "Combustion Oscillations in Industrial Combustion Chambers , Ibid, pp 163-68... 

A Study of Combustion and Recombination Reactions During the Nozzle Expansion Process of a Liquid Propellent Rocket Engine , Ibid, pp 366-74 F2) W.E. Johnson W. 

D.W. Rice, CombstnFlame 8(1), 21-8 (1964) CA 60, 14325 (1964) (Effect of compositional variables upon oscillatory combustion of solid rocket propellants) N ) R.W. Hart F.T. McClure, "Theory of Acoustic Instability in Solid Propellant Rocket Combustion , lOthSympCombstn (1965), pp 1047-65 N2) E.W. Price, "Experimental Solid Rocket Combustion Instability , Ibid, pp 1067-82 Qi) R.S. Levine, "Experimental Status of High Frequency Liquid Rocket Combustion Instability , Ibid, pp 1083-99 O2) L. Crocco,... 

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,... 

Combustion Instability in Liquid Propellant Rockets , 12thSympCombstn (1968)... 

Detonation and Two-Phase Flow is discussed at ARS Propellants, Combustion and Liquid Rocket Conference in 1961. Published by Academic Press, NY (1962)... 

Western States Sect Combust Inst, Paper, WSCI 65-23 (1965) 27) G.R. Mistier T.F. Seamans, Vacuum ignition characteristics of flox/diborane and oxygen difluoride/diborane, NASA Contract Report 1969, NASA-CR-100678. Avail CFSTI. From SciTechAerosp Rep 7 (12), 2196 (1969) 28) W.B. Powell et al, ClFj-Njli, liquid propellant evaluation and rocket motor development, TechRept 32-305, Jet Propulsion Lab, Calif Inst Tech, Pasadena, Ca, (May 1963) (NASA N63-21722) 29) H. Allen, Jr Pinna, Relative ignitability of typical solid propellants with C1F3, NASA TN-D-1533, NASA, Wash, DC, (Jan 1963) (NASA N63-11616) 30) R.F. Sawyer et al, AIAA J, 6, 11, 2111 (1968) CA 70, 13118 (1969) 31) M.C. Branch ... 

The main component of a modem liquid-propellant rocket thrust-chamber assembly is called the coolant jacket. There are many jacket designs but, in nearly all cases, the jacket structure extends thru the throat region as well as the combustion chamber Ref J.W. Herrick E. Burgess, Rocket Encyclopedia Illustrated , Aero Publ, Los Angeles, Calif (1959), p 240... 

W.H. Jones, Recent advances in the chemistry of liquid solid propellants, Combust PropeUenti Nuovi, AttiConv, Milan, 1963, 249 (Pub 1964) CA 62, 1505 (1965)... 

Mechanism for Deriving Energy. The mechanism by which propulsive energy is derived from propellant systems containing metals and their compounds is somewhat different from that of conventional liquid propellant systems. For hydrazine and nitrogen tetroxide, for example, their combustion leads to the formation of N2, H20, and H2 through a relatively simple series of intermediate species ... 

Thermal initiation of an explosion as well as the temperature of decomposition of propellants are measured by standard test No. 6 developed by the Joint Army-Navy-Air Force Panel on Liquid Propellants (2). The primary purpose of this test is to determine at what temperature an unstable material will undergo rapid exothermic decomposition. If the rate at which the heat is generated is greater than the rate at which it can be dissipated, an explosion will be likely. This test attempts to predict the result of conditions that can exist in the regenerative heating section of a rocket engine as well as at the propellant injector. Both of these sections experience relatively rapid local temperature rises owing to combustion. 

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

Injector design determines the physicochemical processes occurring in liquid propellant rocket engines. A complete quantitative description of the processes in liquid rockets is impossible because of our limited understanding of chemical reaction mechanisms and rates. The use of similarity principles simplifies the solution of theoretical combustion problems and is described for channel flow with chemical reactions and for diffusion flames over liquid droplets involving two coupled reaction steps. We find the new result that the observed burning rate of a liquid droplet is substantially independent of the relative rates of the coupled reactions. 

---