N 8 4 - 2 45 84NASA Technical Memorandum 83682

Combustion Gas Properties of VariousFuels of Interest to GasTurbine Engineers

Robert E. Jones, Arthur M. Trout, and Jerrold D. WearLewis Research CenterCleveland, Ohio

Prepared for thePower Generation Conferencesponsored by the American Society of Mechanical EngineersToronto, Canada, October, 1-4, 1984

NASA

https://ntrs.nasa.gov/search.jsp?R=19840016516 2018-05-30T02:44:23+00:00Z

COMBUSTION GAS PROPERTIES OF VARIOUS FUELS OF INTEREST TO GAS TURBINE ENGINEERS

Robert E. Jones,. Arthur M. Trout, and Jerrold D. Wear

National Aeronautics and Space AdministrationLewis Research CenterCleveland, Ohio 44135

ABSTRACT

A series of computations have been made using thegas property computational schemes of Gordon andMcBride to compute the gas properties and species con-centration of ASTM-Jet A and dry air. The purpose ofthis work was to present the computed gas thermo-dynamic properties in a revised graphical format thatwould present this information in a way very usefulto combustion engineers. The plan is to publish anextensive series of reports covering the propertiesof many fuel and .air combinations. The revisedgraphical presentation displays on one chart the out-put from hundreds of computer sheets. The publishedreports will contain microfiche cards, from which com-plete tables and graphs can be obtained. This reportdocuments the extent of the planned effort and pro-vides samples of the many tables and charts that willbe available on the microfiche cards.

INTRODUCTION

The purpose of this paper is twofold: it isfirst to acquaint the reader with the present activityat NASA Lewis where combustion gas properties of manyfuel and air combinations are being computed andsecond to elicit additional input from the technicalcombustion community as to additional fuel-air com-binations that should be computed.

In the past, the combustion gas properties ofgas turbine fuels as well as a variety of other hydro-carbon fuels have been computed and reported, Refs. 1to 5. These reports have been extensively used bothat NASA and throughout the industry. The computa-tional schemes that have been developed over the yearsby Huff, Gordon, Morrell, Zeleznik, and McBride,Refs. 6 to 8, form the basis for these reports andhave been used to compute combustion gas propertiesfor a wide spectrum of fuel and oxidant combinations.

Often, however, the tables and charts have notbeen prepared for specific fuels, as for instanceRef. 5. This work can be used to .obtain the desiredvalues of gas property for specific fuels, butrequires that multiple extrapolations be made toaccount for the proper value of fuel carbon-to-hydrogen ratio, inlet-air temperature, fuelrair ratio,and pressure. In addition to being tedious to use,tables fail to graphically portray the influence, orlack of influence, of the various parameters on acombustion gas property.

The information on combustion gas propertiesobtainable from the referenced works has been puttogether in an entirely different format as a seriesof tables and charts. These charts have proven to beextremely useful in combustion research and copies ofsuch charts have been prepared in the past for a widevariety of fuels. Due to the numerous requests forthese charts as well as the interest in high pressurecombustion research, Ref. 9, we have decided to pre-pare a new series of charts and tables and extend theapplicable range of parameters covered.

This paper will present sample tables and thermo-dynamic charts of the type that will be included ineach report. At the present time, reports coveringthe gas properties of ASTM-Jet A and dry air, and

natural gas and dry air, are being published. Com-bustion gas properties have been computed for a rangeof pressures from 0.5 to 50 atm, inlet-air tempera-tures from 250 to 1150 K and equivalence ratios from0 to 2. The complete tables and figures will not bereproduced in each report; only sample figures areprovided. The complete tables and charts are providedon'microfiche cards supplied with each report..

SCOPE

The complete preparation and publication of thesecombustion gas property charts is expected .to takeseveral years. This is particularly true if the num-ber of planned fuel-oxidant combinations should in-crease. Table I is a listing of the fuel and oxidantcombinations that are planned for computation. Addi-tions or deletions can be made in response to theinterest we receive for this work. The computationalscheme that has been devised, using the programsdeveloped in Refs. 4, 6 to 8 permits one to generatethese tables and charts of gas properties withrelative ease. . .

PROCEDURE

The computations of combustion gas propertiesare performed using the computer routines that havebeen developed by Gordon, McBride et al. and aredocumented in detail in Refs. 5 to 8. .The computa-tional codes have been extensively utilized in thepast to generate tables of combustion gas properties.The most recent publication of tables is to be foundin Ref. 5. In this referenced work, combustion gasproperties were computed for parametric values ofhydrogen to carbon ratios, rather than specific ratiosrepresentative of actual fuels. The graphs and tablesshown in the present report were made specificallyfor the fuel-oxident choice of ASTM-Jet A and dryair. An average molecular carbon-to-hydrogen ratioof 1.9067 was used for the computation. This valuewas an average obtained from analysis of severalsamples of ASTM-Jet A, a wide specification rangekerosene-type, commercial grade aviatiorrfuel. Cal-culation of combustion gas properties was performedusing the referenced computer codes. Normally, manyhundreds of pages of computer printouts would beobtained in order to amass the information requiredto generate the appropriate graphs. The computerprogram has been modified slightly to avoid theproblems of cross-plotting this information by handand can now directly generate the tables and chartsuseful to combustion engineers. For example, chartsof equilibrium gas temperature were generated over arange of inlet-air temperatures, pressures, and fuel-air ratios. This has been done by selecting a con-stant value for the equilibrium temperature, a pres-sure and fuel-air ratio, and then computing in aniterative manner the required value of the inlet-airtemperature. Computed values are stored as a dataset and charts are produced by the computer. Inregions where the results become highly nonlinear,.additional computations are performed to present theresults with the desired level of accuracy. A carefulexamination of the charts in these regions will show

that the curve fit consists of very short linear seg-ments. Nonetheless, the appropriate level of accuracythat one needs from such charts is still provided.

In a similar fashion, an appropriate iterativeprocedure was used to generate the other gas propertycharts.

RESULTS

The computation procedure was used to generatethe tables and charts that will be presented in eachsubsequent report. The bulk of the information thatwas generated is presented on microfiche cards pro-vided with each report. Sample tables and figuresare presented in this paper to illustrate the natureof the information that is available.

Tabular Listings

Table II of this report is a copy of a typicallisting of combustion gas properties and species.Included in.these tables are the following:

1. Case number and description which includesthe oxidant-fuel ratio (0/F), the fuel-air ratio,(F/A), percent fuel, and the equivalence ratio (Phi).The change in case number has been used to specify achange in the inlet-air temperature; e.g., case 1 is250 K, in Case 2 is 400 K (shown), case 7 is 1150 K.

2. Combustion gas properties which are equili-brium temperature (K), density (g/cc), molecularweight, specific heat at constant pressure, (cal/g-K),isentropic exponent-gamma(s), and sonic velocity(m/sec).

3. Mole fractions of the various gas species aregiven when their concentration is equal to or greaterthan 5 ppmv.

The listing at the top of Table II is the inputinformation on the fuel and oxidant. Listed are,reading from left to right, the fuel and oxidantatomic formulas, the weight fraction of each compo-nent, the heats of formation, the inlet temperature(fuel was always introduced at 298 K and air forCase 2 is at 400 K), and the density of the fuel inthe last column. This is typical input listing thatis used by Gordon in Ref. 5.

The tables list the gas properties and speciesconcentrations for 1820 different combinations ofparametric conditions. The parameters and valuesused are listed below.

Combustion pressure, atm.: 0.5, 1, 1.5, 2, 3,4, 6, 10, 15, 20, 30, 40, 50

Inlet-air temperature, K: 250, 400, 600, 800,1000, 1100, 1150 (cases 1 to 7.)

Equivalence ratio, 4, (Phi): 0.1, 0.2, 0.3,0.4, 0.5, 0.6, 0.7, 0.8, 0.85, 0.9, 0.95, 1.0, 1.05,1.10, 1.15, 1.2, 1.4, 1.6, 1.8, 2.0

The information contained in these tables hasbeen used to generate the thermodynamic properties'shown in Figs. 1 to 3, and 6.

Table III presents a sample of another type oftabular listing supplied in these reports. Thesetables list thermodynamic combustion gas propertiesfor different combinations of parametric conditions.These tables were computed by selecting the combustionpressure, mixture temperature, and fuel-air ratio andthen performing iterative calculations to generate theproperties of these combustion gas mixtures. Theparameters used and ranges were:

Combustion pressure, atm: 0.5 to 50 (in steps asindicated above)

Mixture temperature, K: 2800 to 300 in 100 Kincrements

Fuel-air-ratio (weight): 0.0 to 0.1 inincrements of 0.01

Information contained in these tables has beenused to generate the thermodynamic properties shownin Fig. 4 and 5.

Graphical Presentations of Thermodynamic Properties

Some typical figures have been included in thispaper to illustrate the nature of the charts that areavailable on the report microfiche cards. Figure 1presents computed values showing the effect of varyingthe inlet-air temperature, the fuel-air ratio, and thecombustion pressure on the equilibrium gas tempera-ture. The figure covers a range of pressures from 4to 50 atmospheres. Curves at lower pressures (0.5 to4 atm,) are available on the microfiche cards, butwere not included on this figure as the curves tend tooverlap and become confusing.

Figure 2 is similar to figure 1 except that theequilibrium temperature is a function of fuel-airratio, for various values of the inlet-air temperatureat a single specified level of combustion pressure; 1atmosphere in this case.

Figure 3 is similar to Fig. 2 except that tem-perature rise values are plotted versus the fuel-airratio for a range of inlet-air temperatures at the 1atm pressure level. Curves at other pressure levelsare available on the microfiche cards. Figure 4presents the variation in the isentropic exponent,gamma(s) of Ref. 7, as a function of the gas mixturetemperature for various values of fuel-air ratio at asingle value of combustion pressure; again 1 atmo-sphere for the illustrated figure. For the purpose'of these reports, mixture temperature and equilibriumtemperature may be used interchangeably.

Figure 5 presents the variation in mixture molec-ular weight as a function of mixture temperature forvarious values of fuel-air ratio at specified levelsof combustion pressure.

Figure 6 shows the relationship between the com-puted equilibrium temperature for various values ofthe equivalence ratio, * (Phi), at specified pres-sure levels.

SUMMARY

The computational schemes that have been used inthe past to compute thermodynamic combustion gas pro- .perties have been modified to generate a series oftables and charts that are believed to be particularlyuseful for gas turbine combustion engineers. At pre-sent, reports covering the thermodynamic propertiesand species concentration of ASTM-Jet A and dry air,and natural gas and dry air, are complete and inpublication.

REFERENCES

1. Pinkel, B., and Turner, R. L.: ThermodynamicData for the Computation of the Performance ofExhaust-Gas Turbines. NACA ARR-4B25, 1944.

2. Turner, L. R., and Lord, A. M.: ThermodynamicCharts for the Computation of Combustion andMixture Temperatures at Constant Pressure. NACATN 1086, 1946.

3. Turner, L. R., and Bogart, D.:Constant-Pressure Combustion Charts IncludingEffects of Diluent Addition. NACA Rep. 937,1949 (Formerly NACA TNs 1086 and 1655).

Huntley, S. C.: Ideal Temperature Rise Due toConstant-Pressure Combustion of a JP-4 Fuel.NACA RM-£55G27a, 1955.Gordon, S.: Thermodynaroic and TransportCombustion of Hydrocarbons With Air. I -Properties in SI Units. NASA TP-1906, 1982Huff, V. N.; Gordon, S.; and Morrell, V. E.:General Method and Thermodynamic Tables forComputation of Equilibrium Composition andTemperature of Chemical Reactions. NACA Rep.1037, 1951.Zelezm'k, F. J., and Gordon, S.: A General IBM704 or 7090 Computer Program for Computation ofChemical Equilibrium Compositions, Rocket

Performance, and Chapman-Jouguet Detonations.NASA TN D-1454, 1962.Gordon, S., and McBride, B. 0.: ComputerProgram for Calculation of Complex ChemicalEquilibrium Composition, Rocket Performance,Incident and Reflected Shocks, andChapman-Jouguet Detonations. NASA SP-273,Revised, 1976.Claus, R. W.; Neely, G. M.; and Humenik, F. M.Flame Radiation and Liner Heat Transfer in aTubular-Can Combustor. NASA TM-83538, 1984.

TABLE I. - LIST OF PLANNED FUEL-OXIDANT COMBINATIONS

1. Jet-A and Air2. Jet-A and Air + 2% Oxygen3. Oet-A and Air + 456 Oxygen4. JET-A and Air + 6% Oxygen5. JET-A and Air + 8% Oxygen6. JET-A and Air + 10% Oxygen7. JET-A and Humid Air8. JP-4 and Air9. ERBS and Air10. Gasoline and Air11. Natural Gas and Air12. Methane and Air13. Methane @ 589K and Air14. Methane & 922K and Air

15. Propane and Air16. ERBS + 2% Methanol and Air17. ERBS +• 4% Methanol and Air18. ERBS + 6% Methanol and Air19. ERBS + 8% Methanol and Air20. ERBS + 10% Methanol and Air21. Low BTU Gas and Air22. Medium BTU Gas and Air23. Hydrogen and Air24. JP-10 and Air25. JP-10 + 50% Carbon and Air26. JP-10 + Aluminum and Air27. JP-10 + Boron and Air

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1. Report No.

NASA TM-836822. Government Accession No. 3. Recipient's Catalog No.

4. Title and Subtitle 5. Report Date

Combustion Gas Properties of Various Fuels of Interestto Gas Turbine Engineers

6. Performing Organization Code

505-40-227. Authors)

Robert E. Jones, Arthur M. Trout, and Jerrold D. Wear

8. Performing Organization Report No.

E-213310. Work Unit No.

9. Performing Organization Name and Address

National Aeronautics and Space AdministrationLewis Research CenterCleveland, Ohio 44135

11. Contract or Grant No.

12. Sponsoring Agency Name and Address

National Aeronautics and Space AdministrationWashington, D.C. 20546

13. Type of Report and Period Covered

Technical Memorandum

14. Sponsoring Agency Code

15. Supplementary Notes

Prepared for the Joint Power Generation Conference sponsored by the AmericanSociety of Mechanical Engineers, Toronto, Canada, October 1-4, 1984.

16. Abstract

A series of computations have been made using the gas property computationalschemes of Gordon and McBride to compute the gas properties and species concen-tration of ASTM-Jet A and dry air. The purpose of this work was to present thecomputed gas thermodynamic properties in a revised graphical format that wouldpresent this information in a way very useful to combustion engineers. The planis to publish an extensive series of reports covering the properties of many fueland air combinations. The revised graphical presentation displays on one chartthe output from hundreds of computer sheets. The published reports will containmicrofiche cards, from which complete tables and graphs can be obtained. Thisreport documents the extent of the planned effort and provides samples of themany tables and charts that will be available on the microfiche cards.

17. Key Words (Suggested by Author(s))

Combustion gas properties

19. Security Classif. (of this report)

Unclassified

18. Distribution Statement

Unclassified - unlimitedSTAR Category 07

20. Security Classif. (of this page)

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