A series of computations were made using the gas property computational schemes of Gordon and McBride to compute the gas properties and species concentration of ASTM-Jet A and dry air. The computed gas thermodynamic properties in a revised graphical format which gives information which is useful to combustion engineers is presented. A series of reports covering the properties of many fuel and air combinations will be published. The graphical presentation displays on one chart of the output of hundreds of computer sheets. The reports will contain microfiche cards, from which complete tables and graphs can be obtained. The extent of the planned effort and is documented samples of the many tables and charts that will be available on the microfiche cards are presented

Jones, R. E.

Trout, A. M.

Wear, J. D.

English

NASA Technical Reports Server

N 8 4 - 2 45 84
NASA Technical Memorandum 83682
Combustion Gas Properties of Various
Fuels of Interest to Gas
Turbine Engineers
Robert E. Jones, Arthur M. Trout, and Jerrold D. Wear
Lewis Research Center
Cleveland, Ohio
Prepared for the
Power Generation Conference
sponsored by the American Society of Mechanical Engineers
Toronto, Canada, October, 1-4, 1984
NASA
https://ntrs.nasa.gov/search.jsp?R=19840016516 2020-03-20T22:25:36+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 Administration
Lewis Research Center
Cleveland, Ohio 44135
ABSTRACT
A series of computations have been made using the
gas property computational schemes of Gordon and
McBride to compute the gas properties and species con-
centration of ASTM-Jet A and dry air. The purpose of
this work was to present the computed gas thermo-
dynamic properties in a revised graphical format that
would present this information in a way very useful
to combustion engineers. The plan is to publish an
extensive series of reports covering the properties
of many fuel and .air combinations. The revised
graphical presentation displays on one chart the out-
put from hundreds of computer sheets. The published
reports will contain microfiche cards, from which com-
plete tables and graphs can be obtained. This report
documents the extent of the planned effort and pro-
vides samples of the many tables and charts that will
be available on the microfiche cards.
INTRODUCTION
The purpose of this paper is twofold: it is
first to acquaint the reader with the present activity
at NASA Lewis where combustion gas properties of many
fuel and air combinations are being computed and
second to elicit additional input from the technical
combustion community as to additional fuel-air com-
binations that should be computed.
In the past, the combustion gas properties of
gas turbine fuels as well as a variety of other hydro-
carbon fuels have been computed and reported, Refs. 1
to 5. These reports have been extensively used both
at NASA and throughout the industry. The computa-
tional schemes that have been developed over the years
by Huff, Gordon, Morrell, Zeleznik, and McBride,
Refs. 6 to 8, form the basis for these reports and
have been used to compute combustion gas properties
for a wide spectrum of fuel and oxidant combinations.
Often, however, the tables and charts have not
been prepared for specific fuels, as for instance
Ref. 5. This work can be used to .obtain the desired
values of gas property for specific fuels, but
requires that multiple extrapolations be made to
account 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, or
lack of influence, of the various parameters on a
combustion gas property.
The information on combustion gas properties
obtainable from the referenced works has been put
together in an entirely different format as a series
of tables and charts. These charts have proven to be
extremely useful in combustion research and copies of
such charts have been prepared in the past for a wide
variety of fuels. Due to the numerous requests for
these charts as well as the interest in high pressure
combustion research, Ref. 9, we have decided to pre-
pare a new series of charts and tables and extend the
applicable range of parameters covered.
This paper will present sample tables and thermo-
dynamic charts of the type that will be included in
each report. At the present time, reports covering
the 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 range
of pressures from 0.5 to 50 atm, inlet-air tempera-
tures from 250 to 1150 K and equivalence ratios from
0 to 2. The complete tables and figures will not be
reproduced in each report; only sample figures are
provided. The complete tables and charts are provided
on'microfiche cards supplied with each report..
SCOPE
The complete preparation and publication of these
combustion gas property charts is expected .to take
several 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 oxidant
combinations that are planned for computation. Addi-
tions or deletions can be made in response to the
interest we receive for this work. The computational
scheme that has been devised, using the programs
developed in Refs. 4, 6 to 8 permits one to generate
these tables and charts of gas properties with
relative ease. . .
PROCEDURE
The computations of combustion gas properties
are performed using the computer routines that have
been developed by Gordon, McBride et al. and are
documented in detail in Refs. 5 to 8. .The computa-
tional codes have been extensively utilized in the
past to generate tables of combustion gas properties.
The most recent publication of tables is to be found
in Ref. 5. In this referenced work, combustion gas
properties were computed for parametric values of
hydrogen to carbon ratios, rather than specific ratios
representative of actual fuels. The graphs and tables
shown in the present report were made specifically
for the fuel-oxident choice of ASTM-Jet A and dry
air. An average molecular carbon-to-hydrogen ratio
of 1.9067 was used for the computation. This value
was an average obtained from analysis of several
samples of ASTM-Jet A, a wide specification range
kerosene-type, commercial grade aviatiorrfuel. Cal-
culation of combustion gas properties was performed
using the referenced computer codes. Normally, many
hundreds of pages of computer printouts would be
obtained in order to amass the information required
to generate the appropriate graphs. The computer
program has been modified slightly to avoid the
problems of cross-plotting this information by hand
and can now directly generate the tables and charts
useful to combustion engineers. For example, charts
of equilibrium gas temperature were generated over a
range 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 an
iterative manner the required value of the inlet-air
temperature. Computed values are stored as a data
set and charts are produced by the computer. In
regions where the results become highly nonlinear,
.additional computations are performed to present the
results with the desired level of accuracy. A careful
examination of the charts in these regions will show
that the curve fit consists of very short linear seg-
ments. Nonetheless, the appropriate level of accuracy
that one needs from such charts is still provided.
In a similar fashion, an appropriate iterative
procedure was used to generate the other gas property
charts.
RESULTS
The computation procedure was used to generate
the tables and charts that will be presented in each
subsequent report. The bulk of the information that
was generated is presented on microfiche cards pro-
vided with each report. Sample tables and figures
are presented in this paper to illustrate the nature
of the information that is available.
Tabular Listings
Table II of this report is a copy of a typical
listing of combustion gas properties and species.
Included in.these tables are the following:
1. Case number and description which includes
the 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 a
change in the inlet-air temperature; e.g., case 1 is
250 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), molecular
weight, 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 are
given when their concentration is equal to or greater
than 5 ppmv.
The listing at the top of Table II is the input
information on the fuel and oxidant. Listed are,
reading from left to right, the fuel and oxidant
atomic formulas, the weight fraction of each compo-
nent, the heats of formation, the inlet temperature
(fuel was always introduced at 298 K and air for
Case 2 is at 400 K), and the density of the fuel in
the last column. This is typical input listing that
is used by Gordon in Ref. 5.
The tables list the gas properties and species
concentrations for 1820 different combinations of
parametric conditions. The parameters and values
used 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 has
been used to generate the thermodynamic properties'
shown in Figs. 1 to 3, and 6.
Table III presents a sample of another type of
tabular listing supplied in these reports. These
tables list thermodynamic combustion gas properties
for different combinations of parametric conditions.
These tables were computed by selecting the combustion
pressure, mixture temperature, and fuel-air ratio and
then performing iterative calculations to generate the
properties of these combustion gas mixtures. The
parameters used and ranges were:
Combustion pressure, atm: 0.5 to 50 (in steps as
indicated above)
Mixture temperature, K: 2800 to 300 in 100 K
increments
Fuel-air-ratio (weight): 0.0 to 0.1 in
increments of 0.01
Information contained in these tables has been
used to generate the thermodynamic properties shown
in Fig. 4 and 5.
Graphical Presentations of Thermodynamic Properties
Some typical figures have been included in this
paper to illustrate the nature of the charts that are
available on the report microfiche cards. Figure 1
presents computed values showing the effect of varying
the inlet-air temperature, the fuel-air ratio, and the
combustion pressure on the equilibrium gas tempera-
ture. The figure covers a range of pressures from 4
to 50 atmospheres. Curves at lower pressures (0.5 to
4 atm,) are available on the microfiche cards, but
were not included on this figure as the curves tend to
overlap and become confusing.
Figure 2 is similar to figure 1 except that the
equilibrium temperature is a function of fuel-air
ratio, for various values of the inlet-air temperature
at a single specified level of combustion pressure; 1
atmosphere in this case.
Figure 3 is similar to Fig. 2 except that tem-
perature rise values are plotted versus the fuel-air
ratio for a range of inlet-air temperatures at the 1
atm pressure level. Curves at other pressure levels
are available on the microfiche cards. Figure 4
presents the variation in the isentropic exponent,
gamma(s) of Ref. 7, as a function of the gas mixture
temperature for various values of fuel-air ratio at a
single value of combustion pressure; again 1 atmo-
sphere for the illustrated figure. For the purpose'
of these reports, mixture temperature and equilibrium
temperature may be used interchangeably.
Figure 5 presents the variation in mixture molec-
ular weight as a function of mixture temperature for
various values of fuel-air ratio at specified levels
of combustion pressure.
Figure 6 shows the relationship between the com-
puted equilibrium temperature for various values of
the equivalence ratio, * (Phi), at specified pres-
sure levels.
SUMMARY
The computational schemes that have been used in
the past to compute thermodynamic combustion gas pro- .
perties have been modified to generate a series of
tables and charts that are believed to be particularly
useful for gas turbine combustion engineers. At pre-
sent, reports covering the thermodynamic properties
and species concentration of ASTM-Jet A and dry air,
and natural gas and dry air, are complete and in
publication.
REFERENCES
1. Pinkel, B., and Turner, R. L.: Thermodynamic
Data for the Computation of the Performance of
Exhaust-Gas Turbines. NACA ARR-4B25, 1944.
2. Turner, L. R., and Lord, A. M.: Thermodynamic
Charts for the Computation of Combustion and
Mixture Temperatures at Constant Pressure. NACA
TN 1086, 1946.
3. Turner, L. R., and Bogart, D.:
Constant-Pressure Combustion Charts Including
Effects of Diluent Addition. NACA Rep. 937,
1949 (Formerly NACA TNs 1086 and 1655).
Huntley, S. C.: Ideal Temperature Rise Due to
Constant-Pressure Combustion of a JP-4 Fuel.
NACA RM-£55G27a, 1955.
Gordon, S.: Thermodynaroic and Transport
Combustion of Hydrocarbons With Air. I -
Properties in SI Units. NASA TP-1906, 1982
Huff, V. N.; Gordon, S.; and Morrell, V. E.:
General Method and Thermodynamic Tables for
Computation of Equilibrium Composition and
Temperature of Chemical Reactions. NACA Rep.
1037, 1951.
Zelezm'k, F. J., and Gordon, S.: A General IBM
704 or 7090 Computer Program for Computation of
Chemical Equilibrium Compositions, Rocket
Performance, and Chapman-Jouguet Detonations.
NASA TN D-1454, 1962.
Gordon, S., and McBride, B. 0.: Computer
Program for Calculation of Complex Chemical
Equilibrium Composition, Rocket Performance,
Incident and Reflected Shocks, and
Chapman-Jouguet Detonations. NASA SP-273,
Revised, 1976.
Claus, R. W.; Neely, G. M.; and Humenik, F. M.
Flame Radiation and Liner Heat Transfer in a
Tubular-Can Combustor. NASA TM-83538, 1984.
TABLE I. - LIST OF PLANNED FUEL-OXIDANT COMBINATIONS
1. Jet-A and Air
2. Jet-A and Air + 2% Oxygen
3. Oet-A and Air + 456 Oxygen
4. JET-A and Air + 6% Oxygen
5. JET-A and Air + 8% Oxygen
6. JET-A and Air + 10% Oxygen
7. JET-A and Humid Air
8. JP-4 and Air
9. ERBS and Air
10. Gasoline and Air
11. Natural Gas and Air
12. Methane and Air
13. Methane @ 589K and Air
14. Methane & 922K and Air
15. Propane and Air
16. ERBS + 2% Methanol and Air
17. ERBS +• 4% Methanol and Air
18. ERBS + 6% Methanol and Air
19. ERBS + 8% Methanol and Air
20. ERBS + 10% Methanol and Air
21. Low BTU Gas and Air
22. Medium BTU Gas and Air
23. Hydrogen and Air
24. JP-10 and Air
25. JP-10 + 50% Carbon and Air
26. JP-10 + Aluminum and Air
27. JP-10 + Boron and Air
COCNJsO-J-*0
in N(MOr-t
o ooo o
O O O CD
K) lOCJOi-H
11.OOOO
00 C3O OO
o min tnm
CM CM (M CM CM
(M K) CM O r-l
r-l %D CM Of-H
a
CJ>
Q
^10 • • I SOOCO • CM K1 xT so CM CMO - • I *O CO rO •
C3 . »O O O* *CM>O\o CD i-t »-H r~-cO O • O 00 (M •CMIOID
II r-t intMOrH II rH tfCMOr-l
CM K) sj- sO CNJ
5i
ft«
o o o >o r».
o oo cr> V
o co o CM CM
o m tn m KI
o to-a- CM«J-
ocj o in i-i
O rH O IT) K)
OOOOO -tf OOOOO
D O 00 • CM K) «d- so CO O * • I sDCOfO • CM CM \O sf K)
ii
o
a:
o
OOOOO
O O O O O HI
sO CM IOCM O t-4
> | s O O O O * CMtOsTsOCM O - ' I s D e O t O tMCMsOsf K)
O C3 O O
• ^  inC\]Oi-<
O O O O K) o o o o
* O O O O
l-l r-l i-l CM fj
H O Z
u UJ O
^ tn M
o x H
UJ-^^E O
.03X40 * <
JO-Kt UJ U.
J OOO
i *E E UJ
^ tn
« o z
•^  111 O
* en M
o x t-
U)-^« E O
. 03 x w » <
s -t^ -j t*.O-K ui a.
o<ozo
OIOOOO
* CM CM C\J O r-4
000000<*.-«0(MOO.rf
f OtOOf*.
O OOOfs. Qr-t
;»oooooor-»oOf-i
CD <
z o:
• OOOCOOO-lTtO
o or-, o r-4
OOOOOOOOOOOOC3
o o o o r*. OI-H II •tOt
otnooo
(7- O O* O K> O N
O Cd <-l O f-v O f
o o o o r>- o •
a o o o o o o r-»
it cs o o r» o
N • rocomeo
oooor>>-o*o>ofO C7» o CT* o CM o %o oe O*sJ-sDt-IOOK)r^OO»vJ-COO-
EOO
t— LULU
< QQ
bJ
O
X -»^
0-J<I
OCJ <
-*-"^E O
.
X -i^-t
O-K UJ
U OUO
-I <M CM
3in C- tOXZZOO
7^
_
 7
£ 'S.
at
<D
S! 'E°
d "So
o =
w
CD
£i
O.
t/1
O
_E
R>
»—1
"S
CD
0> 0> 2.
Q^ I- O
evl ca
. o
,S 2
•3aniwa3dN3i wn iaanmoa
o o o o
S UJS: S =
^-T__..
2 2 S g
_O
13
.— O)
O 1_
S x:
o _o
S "G*= <=>CD
01
n>
O (/I Q>
Z^ (Q ^^
.
CD CD
o; »-
ra&_
CD
'3aruva3dW3i
= c.
~ TO
2
-^  I**
-O *-
CO d.
1- O>
s S £ co
Is
O
E
p N ~. -
,o <u C
^^ to ^^3». ">
T3 S <U
o> o>
fa
re
re
o
3 03 •—
fjl
l l
\
\
\
\
\
\\
\
\
\
\
t
•l
\
\
\
\
s i s
\
«- X
0.2 £
._ M_ CD
E
- o
— .o o S
T3 E
-53 <" toO w, ._
o-ro -i.d, O) Q.
o; «- o
»- E c
3 OJ O>
o —
o> ''
- S P <u
O)1_
0>
o Q.
S =
_ 00
o
E
(O
o
CD
a. .
cu ^^
fV CTJ
1
</>(XI
O>
OJ
= '
01
,.o
+^
TO
IHDI3M
1. Report No.
NASA TM-83682
2. Government Accession No. 3. Recipient's Catalog No.
4. Title and Subtitle 5. Report Date
Combustion Gas Properties of Various Fuels of Interest
to Gas Turbine Engineers
6. Performing Organization Code
505-40-22
7. Authors)
Robert E. Jones, Arthur M. Trout, and Jerrold D. Wear
8. Performing Organization Report No.
E-2133
10. Work Unit No.
9. Performing Organization Name and Address
National Aeronautics and Space Administration
Lewis Research Center
Cleveland, Ohio 44135
11. Contract or Grant No.
12. Sponsoring Agency Name and Address
National Aeronautics and Space Administration
Washington, 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 American
Society of Mechanical Engineers, Toronto, Canada, October 1-4, 1984.
16. Abstract
A series of computations have been made using the gas property computational
schemes 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 the
computed gas thermodynamic properties in a revised graphical format that would
present this information in a way very useful to combustion engineers. The plan
is to publish an extensive series of reports covering the properties of many fuel
and air combinations. The revised graphical presentation displays on one chart
the output from hundreds of computer sheets. The published reports will contain
microfiche cards, from which complete tables and graphs can be obtained. This
report documents the extent of the planned effort and provides samples of the
many 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 - unlimited
STAR Category 07
20. Security Classif. (of this page)
Unclassified
21. No. of pages 22. Price*
*For sale by the National Technical Information Service, Springfield, Virginia 22161
National Aeronautics and
Space Administration
Washington, D.C.
20546
Official Business
Penalty for Priv«te Use. $300
SPECIAL FOURTH CLASS MAIL
BOOK
Poctaga and Fees Paid
National Aeronautics and
Spec* Administration
NASA-451
NASA POSTMASTER: If Undelrverahle (Srttion I SHPostal Manual) Do Nut Return


Combustion gas properties of various fuels of interest to gas turbine engineers

Abstract

Similar works

Full text

Available Versions

NASA Technical Reports Server