Steady-State Rocket Combustion of Gaseous Hydrogen and Liquid Oxygen. Part 2: Analysis for Coaxial Jet Injection

Combs, L.P.; Schuman, M. D.

doi:10.21236/ad0623401

Cited by 4 publications

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“…However, before adoption of the current approach of developing empirical spray mass and dropsize distributions through cold flow and molten .x studies, some quasi-one-dimensional combustion models were developed in an attempt to calculate the progress of the propellant combubtion within this R-8377 The first generalized coaxial model (Ref. 33 ) was formulated for axisymmetric, cylindrical single element combustion, assumed to be representative of the overall engine combustion. In its original form it applied strictly to injectors ha--ng "flush posts," i.e., both an inner cylindrical tube through which the liquid propellant was delivered, and a surrounding annular space for passage of the gaseous propellant were terminated at the injector fa'ýe.…”

Section: Quasi-one -Dimensional Modelsmentioning

confidence: 99%

Propellant Spray Combustion Processes During Stable and Unstable Liquid Rocket Combustion

Sutton

1970

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Information resulting from this study will allow formulation of new and very general analytical models and criteria to permit a priori design of reliable and stable liquid rocket motors and supersonic air-breathing engines required for future weapons delivery systems. From the test data drop diameterso, velocity and pressure wave growth or decay as a function nf chamber length and initial conditions will be determined. These data can then be input to appropriate newly deyeloped combustion models and the validity of the coupling term expressions evaluated by directly comparing the resulting predictions to experimental data.vi R-8377 ACKNOWLEDGMENT

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Section: Quasi-one -Dimensional Modelsmentioning

confidence: 99%

Propellant Spray Combustion Processes During Stable and Unstable Liquid Rocket Combustion

Sutton

1970

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Study on Breakup Length of Liquid Jet by Liquid-Gas Coaxial Injector —Evaluation of Atomization Characteristics of Rocket Engine Injectors—

Yatsuyanagi

2006

Trans. Japan Soc. Aero. S Sci.

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Based on the experimental observations using a liquid-gas coaxial injector with fairly dense liquid injection, an empirical calculation model of the breakup length of a liquid jet was derived. It is based on the one-dimensional momentum conservation equation for two-phase flow, as well as on the critical Eötvös number, which was derived experimentally by the author in a previous study. This model was applied to evaluate the local stripping rate of the liquid mass at the interaction surface between a liquid and a gas, and was applied to calculate the size of the formed droplets. Comparisons of the mean droplet size, distribution histogram of the size, and breakup length of the liquid jet were made with experimental data. This calculation model was also applied to evaluate the characteristics of the rocket injectors chosen as candidates for the LE-5, the liquid oxygen/hydrogen engine of the second stage of the Japanese H-1 launcher.

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Study on the Design Criteria of the Coaxial Injector for a LOX/Hydrogen Rocket Engine —Evaluation of Design for Injectors of the LE-5 Engine and Its Derivatives—

Yatsuyanagi

2007

Trans. Japan Soc. Aero. S Sci.

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Based on the author's recent study on detailed modeling of the atomization characteristics of a liquid/gas phase coaxial injector, an improved computation model for predicting the combustion performance of a LOX/hydrogen engine is proposed. The features of this model are that it allows calculation of the local rate of atomization of the LOX jet and deals with droplet size distribution of the LOX spray. Additionally the model applies the burning rate constant of LOX/hydrogen combustion derived by the author's former experiment. Using this model, evaluations of the design criteria for the LE-5 engine, which was equipped on the H-2 launcher, and its derivative engines, which have been used with the H-2A launcher, were conducted. Furthermore, optimization of the derivative engine's injector design to improve combustion stability and combustion performance was discussed.

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Steady-State Rocket Combustion of Gaseous Hydrogen and Liquid Oxygen. Part 2: Analysis for Coaxial Jet Injection

Cited by 4 publications

References 0 publications

Propellant Spray Combustion Processes During Stable and Unstable Liquid Rocket Combustion

Propellant Spray Combustion Processes During Stable and Unstable Liquid Rocket Combustion

Study on Breakup Length of Liquid Jet by Liquid-Gas Coaxial Injector —Evaluation of Atomization Characteristics of Rocket Engine Injectors—

Study on the Design Criteria of the Coaxial Injector for a LOX/Hydrogen Rocket Engine —Evaluation of Design for Injectors of the LE-5 Engine and Its Derivatives—

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