7 IIIIIIIIIEIl DEPT OF MECHANICAL AND AEROSPACE ......inm vaorization, gas phase decomposition of...

'ADAO94 618 PRINCETON UNIV NJ DEPT OF MECHANICAL AND AEROSPACE --ETC F/G 21/9.27 SOLID PROPELLANT COMBUSTION MECHANISM RESEARCH 1975-1980.(U)APR 80 L H CAVENY, M SUMMERFIELD. J BELLAN N00014-75-C-0705

UNCLASSIFIEO MAE-149O NL* IIIIIIIIIEIlIIIIIImIrI

SOLID PROPELLANT COMBUSTION

MECHANISM RESEARCH

1975-1980 FINAL REPORT TO THE0OFFICE OF NAVAL RESEARCH

By

Leonard H. Caveny, Martin Summerfield,Josette Bellan and Moshe BenReuven

Performed under Office of Naval ResearchContract N00014-75-C-0705

Partial support provided byU. S. Army Ballistic Research Laboratory

Submitted by

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UNCLASSIFIEDSECURITY CLASSIFICATION OF THIS PAGE (When Date Entered)

REPORT DOCUMENTATION PAGE READ INSTRUCTIONSBEFORE COMPLETING FORM

I. REPORT NUMBER / 12. GOVT ACCESSION NO. 3. RECIPIEN r'S CATALOG NUMBER

4. TITLE (and Subtitle) -5

.YP F &D OD COVERED

Final-'.b, j SOLID PROPELLANT .OMBUSTION MECHANISM RESEARCH F 1 I, Mar8..' " 197-19 F 'u v~., 'u __...._.__ \I Apr'Ni75-31 Mar4ftglf,

7. AUTHOR(s) f. CONTRACT OR GRANT NUMBER(*)

Leonard H.!Caveny Martin/Summer ield/ 'N,14-75-C- P7-5

Josette/Bellan amd Moshe'BenReuvef IN?'" l4- ....... s

9. PERFORMING ORGANIZATION NAME AND ADDRESS 10. PROGRAM ELEMENT. PROJECT, TASKAREA & WORK UNIT NUMBERS

Dept. of Mechanical & Aerospace Engineering

Princeton University ( -Princeton, NJ 08544

I1. CONTROLLING OFFICE NAME AND ADDRESS 12- RFP T F.__

Power Branch 1 Aprfl 1,80Office of Naval Research 13. NUMBER OF.WGES

Washington, DC14. MONITORING AGENCY NAME & ADDRESS(if different from Controlling Office) 15. SECURITY CLASS. (of this report)

I5a. DECLASSIFICATION DOWNGRADINGSCHEDULE

16. DISTRIBUTION STATEMENT (of this Report)

Approved for public release; distribution unlimited.

17. DISTRIBUTION STATEMENT (of the abstract entered In Block 20, if different from Report)

IS. SUPPLEMENTARY NOTES

Partial support provided by U. S. Army Ballistic Research Laboratory.

19. KEY WORDS (Continue on reverse side if necessary and identify by block number)

Solid Propellant Combustion Acoustic Admittance Nitramines

Droplet Combustion Nonsteady burning Combustion instabilityDroplet extinction Combustion stabilityErosive burning HM<

4 Laser Doppler Velocimetry RDX20. ABSTRACT (Continue on reverse side If necessary and identify by block number)

-The multi-task research conducted during the five years of the contractwas aimed at furthering the scientific understanding of propellant combustionprocesses. The low pressure deflagrations of nitramines were interpreted bya physical model that accounts for the interactions among the condensed phase,surface, and near field flame zones. The model demonstrated the importanceof considering both primary and secondary gas phase processes. Chamber flowinteractions with propellants having extended flame zones elucidated contri-butions to erosive burning and sustained acoustic oscillations. The analysisDD FORM

DD jAN 73 1473 EDITION OF I NOV 65 IS OBSOLETE UNCLASSIFIED , -"/ ,SECURITY CLASSIFICATION OF THIS PAGE (Wh7en t1.ts Fntered)

UNCLASSIFIED

SECURITY CLASSIFICATION OF THIS PAGE("hen Date Entered)

.points to the existence of an additional source of acoustic energy produced bycouplings with heat addition from residual reactions in the chamber gases.Droplet burning was analyzed in terms of a reduced boundary condition at thesurface and the quasi-steady heat feedback assumption. A formalism is offeredfor experimentally evaluating the boundary conditions for nonsteady conditions.Direct measurements of solid propellant acoustic admittance were made usinglaser doppler velocimetry coupled with an optical technique for tracking theburning surface. This report contains abstracts of the detailed publicationson each topic.

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PREFACE

The research referred to in this final report was carried out under

Contract N00014-75-C-0705 from the Power Branch, Office of Naval Research.

Dr. Richard S. Miller, of the Power Branch, was the Program Manager. The

U. S. Army Ballistic Research Laboratory, Aberdeen Proving Ground, MD

provided partial support for this research. Mr. C. W. Nelson provided

technical liaison with the Army.

APERgU

The Office of Naval Research sponsorship of solid propellant research

at Princeton University spanned more than two decades. Over the last year

solid propellant and rocket research at Princeton University as a major

activity was brought to an orderly end. All of the major contributors have

elected to pursue their careers with other organizations. Several of us

who have benefited from ONR sponsorship have reflected often on the many

opportunities it provided. As we prepared the renewal proposals, we always

felt the competition of our counterparts and the high standards set by ONR,

but we were comfortable in the knowledge that a properly posed approach could

be continued to its logical conclusion. Often approaches explored and found

to be promising under ONR sponsorship were continued on a larger scale under

other sponsorship. ONR funds were considered t. be too valuable to be tied

up on a single approach. The continuous nature of the funding was ideal

for graduate student research which was usually planned for three years but

often extended beyond that. Possibly the most important legacy of all this

is the continuing contributions to propulsion and combustion by the faculty,

staff, students, and visitors who were involved in the research.

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TABLE OF CONTENTS

Page

TITLE PAGE

DD FORM 1473

PREFACE . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

APERU .............. .............................

TABLE OF CONTENTS ........... ........................

INTRODUCTION AND TECHNICAL OBJECTIVES ........ .............. 1

ACCOMPLISHMENTS UNDER CONTRACT .......... ................. 2

Publications ............. ....................... 2

Abstracts .............. ........................ 3

DISTRIBUTION LIST

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INTRODUCTION AND TECHNICAL OBJECTIVES

Research was performed on steady and unsteady combustion and reacting

flow processes. The analytical and experimental approaches were motivated

by broad scientific objectives. The immediate implications of the research

are to greater understanding and new developments in solid propellant

rocketry.

Investigations of items such as dynamic flame responses, high speed

reacting flows, unsteady chamber flows, chemical kinetics, and mechanistic

chemical interactions are conducted largely independently of each other.

A continuing requirement exists for the investigators working in the various

disciplines to interact and to give more attention to applying the results

of research evolving from their areas of specialization. The physical mea-

surements and mathematical models which were developed and refined as part

of this endeavor provided many opportunities to use data and theories of

other investigators. This was accomplished as data were acquired for vali-

dation of the models and for incorporation into the models. Also, chemical

mechanisms proposed by others were evaluated by using the physical models

in attempts to interpret observed phenomena.

During the period of the contract, four main topics were addressed:

1) Droplet burning

2) Nitramine monopropellant combustion

3) Interaction of chamber flow processes withpropellant combustion

4) Direct measurement of acoustic admittance.

Abstracts of publications on each of these subjects are given in the next

section.

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ACCOMPLISHMENTS UNDER CONTRACT

Publications

Throughout the period of the contract, the research results were

subjects of technical papers. Since the technical papers are distributed

according to the CPIA mailing list as they become available, this report

merely contains abstracts of the publications.

The publications summarized in the abstracts that follow are the

papers which have been (or will be) archived by the appropriate libraries

and agencies. Some types of publications (i.e., preprints of papers later

published in journals, progress reports which were superseded by final

reports, administrative summary reports which merely summarize other publi-

cations listed, and informal presentation summaries) have not been included

if the results reported in them are also contained in a more comprehensive

archive publication. It should be noted that the interplay among the publi-

cations is great since there has been a commonality of propellants, fuels,

data reduction techniques, etc., throughout our investigations.

Abstracts of Publications

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"rLAME~ BONE AND SUB-SURFACE REACTION MODEL FOR DEFLAGRATING.DX"

M. Deneuven, L. H.Caveny, R. J. Vichnevetsky, and M. Summer-fi1ld

Proceedincs of 16th Symposium (International) on Combustion,'The Ca::.bustion Institute, Pittsburgh, PA, 1976, pp. 1223-1233.

z tudy% of 1,3,5 Trinitro Hexahydro 1,3,5, Triazine, RDX,burning as a monopropellant was undertaken to obtain a betterunderszanding of the important chemical steps that control heatfeedback to the condensed phase, to determine the contributionsof che liquid layer, and to provide a means of evaluatingtheories for modifying the burning rate of nitramines. Thefollowinc chemical mechanism is proposed: first, partial de-com.gosition of RDX molecule in the liquid phase; second, follow-inm vaorization, gas phase decomposition of RDX; third, oxida-tion of formaldehyde by N02. The flame structure and liquidlayer reactions of deflagrating RDX were expressed in terms ofthe energy, continuity, and species equations corresponding toRDX decomposing in liquid and gaseous phases and the N02/CH20reactions adjacent to the surface. In addition to the tempera-ture profile and burning rate, the numerical solution providesthe details of the interactions at the liquid/gas interface andthe concentration profiles for the nine most prominent species.Using published kinetic data, the calculated results revealthat even though the liquid layer becomes thinner withincreasing pressure, the increase in surface temperature causesits heat feedback contribution to increase. The pressuresensitivity of burning rate between 0.7 and 0.8 is interpretedin terms of the relative contributions of gas phase and liquidlayer RDX decomposition and the oxidation of CH20. In particular,as pressure increases, the contribution from liquid layerreactions and the second order, N02/CH20 reaction become moreprominent.

Based on work performed under Contract N00014-75-C-0705sponsored by the Power Branch of the Office of Naval Research.

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"ON THE QUASI-STEADY ASSUMPTIONS FOR A BURNING DROPLET."

Josette Bellan and Martin Summerfield

AIAA Journal, Vol. 14, No. 7, July 1976, pp. 973-975.

A large number of results obtained in the field of dropletcombustion are based upon the assumption that the gas fieldbehaves in a quasi-steady manner. However, this assumption isintroduced usually without adequate justification. Therefore,it is felt here that the discussion on the possibility ofrealistically making the quasi-steady assumption for the gasphase deserves particular attention. It was shown that fordroplets in the range encountered in Diesel engines or rockets,there is a domain in the plane (Tp,p) (Tp is a characteristictime and p is a pressure) where the quasi-steady assumptionis valid for typical pressures developed in the above combus-tion systems. As the droplet size decreases, the domain isshown to be larger.

Based on work performed under Contract N00014-75-C-0705 issuedby the Power Branch of the Office of Naval Research.

Accession No. A76-39441. Available from AIAA.

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A MODEL FOR STUDYING UNSTEADY DROPLET COMBUSTION

Josette Bellan and Martin Summerfield

UAA 'Jornai, Vol. 15, No. 2, February 1977, pp. 234-242.

The concept of a reduced boundary condition at the surfaceor a droplet is used to develop a new theory of unsteady dropletzurninc.:. This theory utilizes a quasi-steady gas phase assump-tion which has been shown to be realistic for a wide range ofdroplet sizes at low pressures. The most significant conse-quence of the theory is that the problem of unsteady dropletburninca is reduced to the solving of a single diffusion-typenonlinear partial differential equation having one of itsboundary conditions determined by an algebraic function of thequasi-steady gas phase variables. This reduced boundarycondition incorporates the entire dependence of the solutionon fuel characteristics, chemical kinetics and thermal proper-ties or the gases. An experiment is proposed for determiningthis boundary condition so that the nonsteady droplet combustionproblem can be solved for a realistic situation. By usingadditional assumptions, a numerical estimate of the boundarycondition has been made.

Based on work performed under contract N00014-75-C-0705sponsored by the Office of Naval Research.

Accession No. A76-38167 - available from AIAA. Accessionnumber identifies AIAA Paper 76-614 which is superseded byabove Journal article.

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"T-O r'TCAL FXA:IINATION OF ASSUMPTIONS COMMONLY USED FOR THEGAS P'IASE SURROUNDING A BURNING DROPLET"

j. Bellan and M. Summerfield

Como'stion and Flame, Vol. 33, No. 2, 1978, pp. 107-122

-fnite reaction rate model is compared to three commonlyusei flame-sheet models. These three models differ in theirtreatment of the evaporation from the surface and the valueises for the molecular weights. All four models are valid foro0th steady and unsteady burning of droplets. Further, theyaccount for variations of droplet radii and allow for differ-ences in ambient conditions. Numerical results (obtained forn-JIecane) show that if the radius of the droplet is 10-2 cm thethin flame approximation is excellent at 10 atm if the dropletsurface temoerature is not close to either the boiling point orthe ambient temperature. However, this approximation is unac-ceutable at I atm. Among the three flame-sheet models, the oneusing non-t.cuilibrium evaporation at the surface and individual.oLecular weights best approximates the finite reaction ratetheory. ic.-ever, this agreement breaks down for smaller drop-lets with lower surface temperatures, or for air with a largeroxygen content. These conclusions are independent of the chosenkinetics. The Clausius-Clapeyron approximation is shown to beexcellent away from the boiling point for R = 10- 2 cm. How-ever, as the droplet surface temperature approaches the boilingpoint, or the droplet radius decreases, this assumption leadsto considerable errors in the evaporation rate and also dis-tortion of the thermal layer. Even larger errors are obtainedwhen an average molecular weight is used. Here, large under-estimates of the evaporation rate and great distortions of thethermal layer of the droplet are obtained. In spite of theseerrors, all four models agree at wet-bulb conditions.

Based on work performed under Contract N00014-75-C-0705 issuedby the Office of Naval Research.

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"NITRAMINE FLAME CHEMISTRY AND DEFLAGRATION INTERPRETED IN TERMS OFA FLAME MODEL"

M. Ben Reuven and L. H. Caveny

AIAA Paper 79-1133, AIAA 15th Propulsion Conference, June 1979

The diversity of chemical kinetic time scales associated withnitramine decomposition has led to incorporation of two simultaneousoverall reactions in the vapor phase model of deflagration. Thisallowed derivation of an asymptotic burning rate formula, showingvariable pressure dependence. The comprehensive model considers areacting melt layer, coupled to the gas field through -onservationconditions satisfied by all chemical species and enthalpy, is solvednumerically; the initial version was presented in Proceedings of16th Combustion Symposium, 1976. The structure of the deflagrationwave near the propellant surface is obtained, along with the overallpressure dependence of the surface temperature and the flame speedeigenvalue, comparing RDX and HMX. A mechanism of coupling betweensecondary reactions and heat feedback to the surface is proposed,and a quantitative measure of the effect of condensed phaseexothermicity on burning rate is demonstrated.

Based on research sponsored by the Power Branch of the Office ofNaval Research and supplemented by Army Research Office underContract N00014-75-C-0705.

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"EROSIVE BURNING THEORY FOR PROPELLANTS WITH EXTENDED FLAME ZONES"


AIAA Paper 80-0142 AIAA 18th Aerospace Sciences Meeting, January1980.

Propellants containing large amounts of nitramines experienceburning rate increases under rocket motor cross-flow conditions.Such propellants have relatively low burning rates and thick flamezones, which make them susceptible to velocity coupling. Asimplified theory is advanced, postulating two thermodynamiccoupling criteria between the coreflow and the extended gaseousflame zone. Calculated results reveal that coupling between thecore and the far fi d in the flame, which involves only a fewpercent unreactednL ., may result in appreciable burning ratemodification. Increases of pressure and port diameter tend todecrease the extent of burning rate enhancement and increase thethreshold mass flux in the core. Increasing axial length has theopposite effect.

Based on research sponsored by the Power Branch of the Office ofNaval Research and supplemented by the Army Ballistic ResearchLaboratory under Contract N00014-75-C-0705.

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"DIRECT MEASUREMENTS OF ACOUSTIC ADMITTANCE"

Leonard H. Caveny, S. W. Cheng and W. A. Sirignano

Proceedings of 16th JANNAF Combustion Meeting CPIA Publ. 308,Vol. II, pp. 343-361, Dec. 1979; submitted to AIAA Journal.

Research was directed at making measurements of velocities inpropane/air and solid propellant flames using laser Dopplervelocimetry (LDV) instrumentation. Combustors were developed toimpose a controlled periodic pressure disturbance on burning solidpropellants and to excite a propane/air flame. A tracking systemwas developed to maintain the LDV control volume at a fixed positionabove the regressing propellant surface. The research demonstratedthat unsteady velocities (up to 1000 Hz) could be measured forspecific double base and composite propellants and for aluminaseeded propane/air flames. The simultaneous velocity and pressuremeasurements were used to obtain acoustic admittances.


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"NITRAMINE MONOPROPELLANT DEFLAGRATION AND GENERAL NONSTEADY

REACTING ROCKET CHAMBER FLOWS"


Mechanical and Aerospace Engineering Report 1455, PrincetonUniversity, Princeton, NJ January 1980.

A theoretical investigation is presented on the deflagration ofcyclic nitramines (e.g., RDX and HMX), which are considered ashighly-energetic components in solid propellant formulations forrocket motors. The first part of the study involves a steady statedeflagration analysis of these monopropellants. This serves as anecessary preliminary step in the elucidation of these compoundswithin a propellant matrix. The analysis in the second part isaimed at the behavior of nitramine-like propellants within aninterior burning propellant grain. This was prompted by the notionof thick overall gaseous flame zone associated with nitraminecompounds at pressures up to 5 MPa. The analysis revealed thatrelatively small deviations from fully-burnt state at the wall layeredge may be associated with appreciable burning rate perturbations.The problem of dynamic coupling between the axial acoustic field andthe pressure-sensitive residual reaction in the core was addressed.A comparison of chemical relaxation (secondary reaction) andfluid-dynamic timescales indicates possible areas of Rayleigh-typecoupling. This analysis points to the existence of an additionalcomponent to acoustic instability, namely, an acoustic coupling withheat addition by residual reaction in the core.


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"UNSTEADY REACTING FLOWS IN SOLID ROCKET CHAMBERS"


AIAA Paper 80-1125, AIAA 16th Propulsion Conference, June 1980.

Residual exothermic reactions within the core-flow ofinterior-burning motor grains can result when propellants containinglarge amounts of nitramines (RDX, HMX) are utilized. Thesepropellants tend to burn with thick flame zones, which may extendbeyond the wall-layer region. The stationary aspects ofcore/wall-layer interaction for such motor configurations have beeninvestigated previously, leading to an erosive burning theory. Thepresent analysis addresses the problem of dynamic coupling betweenthe axial acoustic field and the pressure-sensitive residual coreexothermicity. Comparison between timescales for chemicalrelaxation and acoustics indicate possible areas for Rayleigh-typecoupling. In a finite-difference solution of the nonsteady, onedimensional core flowfield, along with a quasi steady wall-layer,such dynamic coupling has been demonstrated, in the form ofspontaneous evolution of acoustic oscillations withslowly-increasing amplitude. In cases of vanishing core/wall-layerinteraction, such instability does not evolve. The effects of meanpressure, overall kinetics constant, extent of fuel/oxidizernonstoichiometry and turbulence intensity for heat feedback to thewall-layer have been investigated in a parametric study. Theexistence of an additional component to acoustic instability istherefore pointed out this phenomenon must be studied within therealm of the particular chamber configuration, since it combinespropellant properties with the flowfield in a non-linear manner.

Based on research sponsored by the Power Branch of the Office ofNaval Research and supplemented by the Army Ballistic ResearchLaboratory Under Contract N00014-75-C-0705.

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ENERGETIC MATERIALS RESEARCH

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