Spectral and total flame radiation measurements exhibited: (1) that radiant heat flux increases with vision combustor inlet air pressure; (2) the effect of fuel atomization characteristics on radiant heat flux; and (3) that a reduction in fuel hydrogen content produces a significant increase in radiant heat flux primarily at low combustor pressures

Claus, R. W.

Humenik, F. M.

Neely, G. M.

English

NASA Technical Reports Server

FLAME RADIATION MEASUREMENTS 
R. W. Claus, F. M. Humenik and G. M. Neely 
NASA Lewis Research Center 
Cleveland, Ohio 44135 
BACKGROUND: 
One of the fundamental combustion experiments being 
conducted here at the Lewis Research Center consists of a 
series of flame radiation measurements on a single JT8D tubular 
combustor assembled in a cylindrical housing having optical 
viewing ports at three axial stations. 
Preliminary flame radiation data were obtained with the 
JT8D tubular combustor during August 1979. Technical paper, 
TP-1722, which was published in February 1981 presents some of 
the spectral radiation data which shows the relative radiance 
at three axial locations in the combustor for a few test 
conditions generally representative of low power settings. 
Supplementary radiant heat flux data, which were measured with 
thermopile type heat flux transducers at two axial stations 
were presented at the LeRC Symposium "Aircraft Research and 
Technology for Future Fuelsff, April 1980 (NASA Conference 
Publication 2146, pp. 153-160). All of these data were 
obtained with Jet A and ERBS fuels, and were limited to 
relatively low operating pressures and relatively mild 
operating conditions. Thus, a continuation and expansion of 
the previous experimental arrangement is required to include a 
broader range of operating conditions ( P 3 ,  Tj, f/a, fuel 
type) so that flame radiation characteristics can be mapped 
more fully. 
Since combustion gases, predominantly carbon dioxide and 
water vapor, emit and absorb radiant energy in discrete 
spectral bands, calculations of flame temperature and soot 
concentration can be performed using the experimentally 
measured spectral radiance profiles. In addition, these 
spectral radiation data can be used for possible correlations 
with local liner temperatures and/or the radiant heat flux 
measurements. Characteristic differences attributed to fuel 
property variations may also be evident from the spectral 
radiance signatures. Thus, there is considerable potential for 
obtaining very valuable data which could improve our 
understanding of the effects of operating conditions, fuel 
type, and other variables on total flame radiation. 
https://ntrs.nasa.gov/search.jsp?R=19830020957 2020-03-22T00:49:24+00:00Z
RESEARCH OBJECTIVES : 
1. Improve and develop flame emissivity correlations. 
2. Evaluate effects of combustor pressure, inlet air 
temperature, and reduced fuel hydrogen content on 
flame radiance. 
3. Correlate increases in flame radiance with increases 
in average liner temperature. 
SIGNIFICANCE - APPLICATIONS: 
1. Establish a comprehensive flame radiation model. 
2. Calculate flame temperature and soot concentration. 
PRELIMINARY RESULTS : 
Spectral and total flame radiation measurements have 
exhibited the following characteristics: 
1. Radiant heat flux increases substantially with rising 
combustor inlet air pressure. 
2. Fuel atomization characteristics can have substantial 
effects on radiant heat flux. 
3. Tests with ERBS fuel indicate that a reduction in fuel 
hydrogen content produces a significant increase in radiant 
heat flux primarily at low combustor pressures. At high 
combustor pressures (14-20 atm.) fuel effects are less 
distinct. 
REFERENCES: 
1. Claus, Russell W.: Spectral Flame Radiance from a 
Tubular-Can Combustor. NASA TP-1722, 1981. 
2. Aircraft Research and Technology for Future Fuels, NASA 
Conference Publication 2146, pp. 153-160; April 1980. 
FLAME RADI AT1 ON MEASUREMENTS 
OBJECTIVE: IMPROVE L INER THERMAL ANALYSIS 
BENEFITS : r REDUCE DEVELOPMENT COST 
r IMPROVE COOLING AIRFLOW D ISTRIBUT ION 
@ INCREASE LOYG TERM DURABIL ITY  OF L INER 
APPROACH: EXPERIMENTALLY ESTABLISH THERMAL MODEL PARAMETERS 
THROUGH D l  RECT MEASUREMENT OF : 
1 ,  SPECTRAL FLAME RADIANCE 
2. TOTAL RADIAT IVE  HEAT FLUX 
FUME RADIATION COMBUSTOR HOUSING ASSEMBLY 
WEKT FLUX 1 
RANSDUCER 
EFFECT OF COMBUSTOR PRESSURE 
r, 3 e l m  
r3 7 
A 14 
0 21 
Zone +l I Zone +2 
Fuel  nozz le  4 2  
J e l  A fue l  
Zone +3 
,008 ,012 ,016 ,020 .008 .012 .018 .020 .008 .012 .Ole .020 
FUEL-AIR RATIO 
EFFECT OF FUEL ATOMIZATION 
O Fuel  nozz le  +l 
Fuel  nozzle +2 
Zone +1 I z o n e  +2 
Combustor pressure.  7 e lm.  
J e t  A fuel  
Zone +3 
.008 .012 .Ole .020 , .008 .012 .018 .020 .008 .012 . O l 6  .020 
FUEL-AIR RATIO 
EFFECT OF FUEL TYPE 
JET A 
ERBS 
Zone + 1 
,008 .012 ,018 .020 .008 .012 ,018 .020 .008 ,012 .016 .020 
FUEL-AIR R A T I O  
EFFECT O F  PRESSURE ON TOTAL FLAME RADIATION 
FOR TWO DIFFERENT FUELS.  
70r ZONE 1 
Combustor pressure.  7 atm. 
Fue l  nozzle + 2  
EFFECT OF PRESSURE ON SPECTRAL 
FLAME RADIANCE. 
VIEW - ZONE 2 
T3 - 533 K 
F/A - 0.016 
N A V E L E N G T H  MICRONS I 
I


Flame Radiation Measurements

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