1. By
Ahmed Sh. Yasiry
EXPERIMENTAL STUDY OF THE EFFECT OF
HYDROGEN BLENDING ON BURNING
VELOCITY FOR DIFFERENT FUELS
Supervised By
Prof D. Haroun A.K. Shahad
01:12 PM
3. Introduction
Increasing concern over the fossil fuel shortage and
pollution of air, and the requirement for alternative fuels for
Internal Combustion Engines have been considered by
researchers.
Researchers have re-evaluated the combustion process
and the prospects of alternative fuels to improve the
combustion characteristics.
01:12 PM
4. Flame
Flame is a visible part of a highly exothermic chemical reaction.
Flame can be classified according to :
1) Composition of The Reactants
2) Basic Character of Gas Flow
3) Motion of Flame
Laminar.
Turbulent.
Stationary .
Nonstationary .
Premixed.
Diffusion.
01:12 PM
5. Laminar Burning Velocity
Laminar burning velocity (ul) is defined as the velocity at
which unburned gases move through the combustion
wave in the direction normal to the wave front.
Burning velocity is a measure of the rate at which
reactants are moving into the flame from a reference point
located on the moving frame. The Flame speed is a
measure of how quickly the flame is traveling from a fixed
reference point
01:12 PM
6. • Liquefied petroleum gas (LPG)
liquefied petroleum gas (LPG) consists mainly of butane and
propane. Being one of the primary energy sources used for
domestic and commercial applications.
LPG has many advantages such as:
High heating value.
cleaner burning with low ash.
Less corrosion and engine wear.
Stable flame and low processing cost.
Fuels Used in The Study
01:12 PM
7. Items C2H6 C3H8 C4H10 C5H12
Volumetric Fractions
) (%
by Volume
.0 9 .36 3 .62 3 .0 5
LPG component is supplied by
Gas Filling Company/ Middle
Euphrates Branch
Fuels Used in The Study
01:12 PM
8. Fuels Used in The Study
• Hydrogen
Hydrogen (H2) is a colorless, odorless, tasteless, non-toxic,
non-metallic and highly combustible diatomic gas. It has
high flame speed, wide flammability limit, low minimum
ignition energy and no emissions of HC or CO2.
Hydrogen addition to a fuel could increase thermal
efficiency, lean burn capability and mitigate the global
warming concerns.
01:12 PM
9. Aims of The Study
The scope of the present work covers:
•To design and construct a constant volume combustionTo design and construct a constant volume combustion
chamber with the required measuring instrumentationschamber with the required measuring instrumentations
•To investigate the effect of equivalence ratio, initial pressureTo investigate the effect of equivalence ratio, initial pressure
and hydrogen blending ratio on laminar burning velocity, flameand hydrogen blending ratio on laminar burning velocity, flame
speed and other parameters.speed and other parameters.
•To derive empirical correlations between studied variables ofTo derive empirical correlations between studied variables of
HH22--LPG–air mixtures.LPG–air mixtures.
01:12 PM
11. Experimental Set up
The study of flame propagation subject needs high speed
photography system because of the very short combustion
time and hence the period available for measurement.
The set up consists of the following units:
•Combustion chamber unit.
•Ignition circuit and control unit.
•Mixture preparing unit.
•Capturing unit.
01:12 PM
12. Photograph of The Experimental Apparatus Used in The Study
Combustion
chamber
Mixture
preparing unit
Ignition circuithigh-speed
camera
16. Mixture Preparing Unit
• Gaseous mixer has been designed and constructed for
gaseous fuels with low partial pressure.
• The purpose of the mixture is to prepare a mixture at the
preset mixing ratios at the required equivalence ratio,
partial pressures and initial pressures.
• The purpose of using the mixer is to increase the total
pressure of the mixture. Consequently, this increases the
partial pressure of each component of the mixture.
01:12 PM
18. Test Procedure
A- Mixture Preparation
1- Flushing Process
2- Vacuum Process
3- Mixing Process
B- CVC Preparation
1- Flushing Process
2- Scavenging Process
3- Filling Process
C- Combustion and Recoding
01:12 PM
23. Flame Propagation Analysis
A FORTRAN program is written to calculate the physical
properties of reactance and expected product, in addition
to adiabatic flame temperature and initial admitting
pressure for each of reactance mixture.
The program is designed to calculate the properties of
neat hydrocarbon fuels (CH4, C2H6, C3H8, C4H10, C5H12), blend
with H2 or mixture of multi hydrocarbons blended with H2.
01:12 PM
25. Validation Theoretical Analysis
• The adiabatic flame temperate is the most influential
parameter to determine the properties of the burnt
mixture.
• The validation has been done by comparing the flame
temperature of CH4 and C3H8 with researcher [2] and 2
software.
• Another companion to validate the blending and multi fuel
with researcher [66]
01:12 PM
26.
27. gaseqfortranerror %gaseqfortranerrorgaseqfortranerror
product
1665.31661.5850.22333222262292.6412.9496042057.42013.7022.146741KAdiabatic Temperature
38.39838.284470.29610441.40441.5360.31830240.14339.42391.807536J/mol/kSpecific Heat
1366.911365.4280.1084791509.451503.1470.4184431551.771520.292.049439J/kg/kSpecific Heat
0.205570.2066560.5268950.150171.47E-012.2065380.159021.57E-011.55E+00kg/m
3
Density
9.89E-020.1098810.518251.32E-011.43E-018.0513721.38E-011.35E-011.85E+00W/m.KThermal Conductivity
3.53E-040.0003899.8262525.84E-046.48E-0410.385755.81E-055.69E-052.06E+00m
2
/secThermal Diffusivity
reactance
29.49229.478070.04724429.71129.718710.02594729.86529.887510.075344J/mol/kSpecific Heat
1049.791045.5310.4065251075.131071.6230.3267261093.41090.4510.270073J/kg/kSpecific Heat
1.14121.1457420.3972121.12261.1269540.3870991.10951.1137740.384478kg/m
3
Density
0.0240.026339.2588912.42E-022.65E-029.061042.44E-022.66E-028.69E+00W/m.KThermal Conductivity
2.02E-052.2E-058.4400242.01E-052.19E-058.7556612.01E-052.19E-058.64E+00m
2
/secThermal Diffusivity
0.61.3 1
ch4
gaseqfortranerror %gaseqfortranerrorgaseqfortranerror
product
1701.11690.9850.5963882267.323553.7946482125.12086.2441.845302KAdiabatic Temperature
38.51838.414950.26789641.34941.644990.71328140.16439.582721.457815J/mol/kSpecific Heat
1350.391349.0490.0993541473.431470.2660.2149681506.951481.771.685002J/kg/kSpecific Heat
0.204342.06E-010.5940510.150831.47E-012.8648290.152841.56E-011.880861kg/m
3
Density
9.89E-021.11E-0111.136911.31E-011.42E-018.2800791.35E-011.36E-010.795049W/m.KThermal Conductivity
3.59E-043.99E-0410.508215.86E-046.60E-0411.853865.85E-045.90E-040.775783m
2
/secThermal Diffusivity
reactance
30.2330.186490.14403430.93530.894910.12967831.44931.411420.119566J/mol/kSpecific Heat
1034.321029.1130.5046931049.821044.7760.481621060.971056.0370.466035J/kg/kSpecific Heat
1.18721.1919990.4034131.1971.2016690.3892991.20411.2087190.382872kg/m
3
Density
2.33E-022.58E-0210.090862.31E-022.56E-0210.2422.90E-022.55E-0212.99082W/m.KThermal Conductivity
2.00E-052.10E-054.9381611.84E-052.04E-0510.2391.80E-051.99E-0510.26578m
2
/secThermal Diffusivity
0.61.3 1
C3H8
Percentage Error for CH4 and C3H8 Physical Properties at Different
Equivalence Ratio Comparing with GASEQ Software.
28. 0 . 6 0 . 8 1 . 0 1 . 2 1 . 4
E q u iv a le n c e R a t io
1 6 0 0
1 7 0 0
1 8 0 0
1 9 0 0
2 0 0 0
2 1 0 0
2 2 0 0
2 3 0 0
2 4 0 0
AdiabaticFlameTemperature(K)
2 0 % H 2
8 0 % H 2
0 1 0 2 0 3 0 4 0 5 0 6 0 7 0 8 0 9 0 1 0 0
H y d r o g e n B le n d ( % )
1 6 0 0
1 7 0 0
1 8 0 0
1 9 0 0
2 0 0 0
2 1 0 0
2 2 0 0
2 3 0 0
2 4 0 0
2 5 0 0
AdiabaticFlameTemperature(k)
φ = 0 .6
φ = 0 .8
φ = 1
φ = 1 .1
φ = 1 .3
0 . 6 0 0 . 7 0 0 . 8 0 0 . 9 0 1 . 0 0 1 . 1 0 1 . 2 0 1 . 3 0
E q u iv a l e n c e R a t io
0 . 1 2
0 . 1 3
0 . 1 4
0 . 1 5
0 . 1 6
0 . 1 7
0 . 1 8
0 . 1 9
DensityRatio
1 0 0 % L P G
2 0 % H 2
5 0 % H 2
8 0 % H 2
9 0 % H 2
0 1 0 2 0 3 0 4 0 5 0 6 0 7 0 8 0 9 0
H y d r o g e n B le n d ( % )
0 . 1 2
0 . 1 3
0 . 1 4
0 . 1 5
0 . 1 6
DensityRatio
φ = 0 .8
φ = 1
φ = 1 .3
Theoretical Physical Properties Results
29. Experimental Results Repeatability
• A pre-set mixture is prepared in the mixing chamber at fixed
condition.
Three consecutive combustion tests are carried out using the same
mixture. Another three tests are performed using different pre-set
mixture.
• Also to test the accuracy of our system, the results of burning
mixture of Methane and properties are compared with results of
other researchers.
01:12 PM
30. Repeatability Results
0 . 0 0 5 0 . 0 1 0 0 .0 1 5 0 . 0 2 0 0 .0 2 5 0 . 0 3 0 0 . 0 3 5
R a d iu s ( m )
1 .0
1 .5
2 .0
2 .5
3 .0
3 .5
4 .0
4 .5
5 .0
5 .5
6 .0
Sn(cm/s)
T e s t 1
T e s t 2
T e s t 3
T e s t 4
T e s t 5
T e s t 6
0 . 6 0 0 .8 0 1 . 0 0 1 . 2 0 1 .4 0 1 .6 0
φ
5
1 0
1 5
2 0
2 5
3 0
3 5
4 0
4 5
ul
(cm/s)
C u r r e n t S tu d y ( 2 0 1 5 )
G o s w a m i e t a l. ( 2 0 1 3 )
L o w r y e t a l. ( 2 0 1 1 )
P a r k e t a l. ( 2 0 1 0 )
C o p p e n s e t a l. ( 2 0 0 7 )
H e g h e s ( 2 0 0 6 )
F a r r w ll e t a l. ( 2 0 0 4 )
F a r r w ll e t a l. ( 2 0 0 4 )
R o z e n c h a n e t a l. ( 2 0 0 2 )
G u e t a l. ( 2 0 0 0 )
E g o lo fo p o u lo s e t a l. ( 1 9 8 9 )
S h a r m a e t a l. ( 1 9 8 1 )
A n d r e w s a n d B r a d le y ( 1 9 7 2 )
Measured Schlieren Radius with
Flame Speed for Six Consecutive
Experiments with (60% H2 blend, =ϕ
0.8 and P0 = 1 bar).
Comparison of Experimental Data for The Burning Velocity of
Methane at T0 = 298 K and p0 = 1 bar with The Data Obtained
from [33 & 83].
01:12 PM
31. Photographs of Flame Propagation for Initial Pressure 3 bar with dt of 3.75 ms at
Different Hydrogen Blend at Equivalence Ratio 0.8.
40% H2
60% H2
80% H2
01:12 PM
32. Photographs of Flame Propagation for Initial Pressure 3 bar with dt of 3.75 ms at
Different Equivalence Ratio for 60% H2
Φ=0.8 Φ=1 Φ=1.3
01:12 PM
33. Φ=0.8
Φ=1
Φ=1.3
Stretched Laminar Flame Speed
0 .0 0 0 0 . 0 0 5 0 . 0 1 0 0 .0 1 5 0 .0 2 0 0 . 0 2 5 0 .0 3 0 0 .0 3 5
R a d iu s ( m )
1 .0
1 .5
2 .0
2 .5
3 .0
3 .5
4 .0
4 .5
5 .0
5 .5
6 .0
Sn(m/s)
p = 3 b a r
p = 2 .5 b a r
p = 2 b a r
p = 1 .5 b a r
p = 1 b a r
( a )
0 . 0 0 0 0 .0 0 5 0 .0 1 0 0 . 0 1 5 0 . 0 2 0 0 .0 2 5 0 .0 3 0 0 . 0 3 5
R a d iu s ( m )
1 . 0
1 . 5
2 . 0
2 . 5
3 . 0
3 . 5
4 . 0
4 . 5
5 . 0
5 . 5
6 . 0
Sn(m/s)
p = 3 b a r
p = 2 . 5 b a r
p = 2 b a r
p = 1 .5 b a r
p = 1 b a r
( b )
0 . 0 0 0 0 . 0 0 5 0 .0 1 0 0 .0 1 5 0 .0 2 0 0 . 0 2 5 0 . 0 3 0
R a d iu s ( m )
1 . 0
1 . 5
2 . 0
2 . 5
3 . 0
3 . 5
4 . 0
4 . 5
5 . 0
5 . 5
6 . 0
Sn(m/s)
p = 3 b a r
p 2 .5 b a r
p = 2 b a r
p = 1 .5 b a r
p = 1 b a r
( c )
0 . 0 0 0 0 .0 0 5 0 . 0 1 0 0 .0 1 5 0 . 0 2 0 0 .0 2 5 0 . 0 3 0 0 .0 3 5
R a d iu s ( m )
1 .0
1 .5
2 .0
2 .5
3 .0
3 .5
4 .0
4 .5
5 .0
5 .5
6 .0
Sn(m/s)
( a ) p = 3 b a r
p = 2 . 5 b a r
p = 2 b a r
p = 1 . 5 b a r
p = 1 b a r
0 . 0 0 0 0 .0 0 5 0 . 0 1 0 0 .0 1 5 0 . 0 2 0 0 .0 2 5 0 .0 3 0 0 . 0 3 5
R a d iu s ( m )
1 .0
1 .5
2 .0
2 .5
3 .0
3 .5
4 .0
4 .5
5 .0
5 .5
6 .0
Sn(m/s)
( b ) P = 3 b a r
p = 2 .5 b a r
p = 2 b a r
p = 1 .5 b a r
p = 1 b a r
0 . 0 0 0 0 .0 0 5 0 . 0 1 0 0 .0 1 5 0 . 0 2 0 0 .0 2 5 0 . 0 3 0 0 .0 3 5
r a d iu s ( m )
1 .0
1 .5
2 .0
2 .5
3 .0
3 .5
4 .0
4 .5
5 .0
5 .5
6 .0
Sn(m/s)
( c ) p = 3 b a r
p = 2 .5 b a r
p = 2 b a r
p = 1 .5 b a r
p = 1 b a r
0 . 0 0 0 0 .0 0 5 0 . 0 1 0 0 . 0 1 5 0 .0 2 0 0 .0 2 5 0 . 0 3 0 0 .0 3 5
R a d iu s ( m )
1 .0
1 .5
2 .0
2 .5
3 .0
3 .5
4 .0
4 .5
5 .0
5 .5
6 .0
Sn(m/s)
p = 3 b a r
p = 2 .5 b a r
p = 2 b a r
p = 1 .5 b a r
p = 1 b a r
( a )
0 . 0 0 0 0 . 0 0 5 0 . 0 1 0 0 .0 1 5 0 . 0 2 0 0 . 0 2 5 0 . 0 3 0 0 . 0 3 5
R a d iu s ( m )
1 . 0
1 . 5
2 . 0
2 . 5
3 . 0
3 . 5
4 . 0
4 . 5
5 . 0
5 . 5
6 . 0
Sn(m/s)
p = 3 b a r
p = 2 .5 b a r
p = 2 b a r
p = 1 .5 b a r
p = 1 b a r
( b )
0 .0 0 0 0 .0 0 5 0 .0 1 0 0 .0 1 5 0 .0 2 0 0 .0 2 5 0 .0 3 0 0 .0 3 5
R a d iu s ( m )
1 .0
1 .5
2 .0
2 .5
3 .0
3 .5
4 .0
4 .5
5 .0
5 .5
6 .0
Sn(m/s) p = 3 b a r
p = 2 .5 b a r
p = 2 b a r
p = 1 .5 b a r
p = 1 b a r
( c )
0 .0 0 0 0 .0 0 5 0 .0 1 0 0 .0 1 5 0 .0 2 0 0 .0 2 5 0 .0 3 0 0 .0 3 5
R a d iu s ( m )
1 .0
1 .5
2 .0
2 .5
3 .0
3 .5
4 .0
4 .5
5 .0
5 .5
6 .0
Sn(m/s)
p = 3 b a r
p = 2 .5 b a r
p = 2 b a r
p = 1 .5 b a r
p = 1 b a r
( a )
0 .0 0 0 0 .0 0 5 0 . 0 1 0 0 .0 1 5 0 .0 2 0 0 . 0 2 5 0 .0 3 0 0 . 0 3 5
R a d iu s ( m )
1 .0
1 .5
2 .0
2 .5
3 .0
3 .5
4 .0
4 .5
5 .0
5 .5
6 .0
Sn(m/s)
p = 3 b a r
p = 2 .5 b a r
p = 2 b a r
p = 1 .5 b a r
p = 1 b a r
( b )
0 .0 0 0 0 .0 0 5 0 .0 1 0 0 .0 1 5 0 .0 2 0 0 .0 2 5 0 .0 3 0 0 .0 3 5
R a d iu s ( m )
1 .0
1 .5
2 .0
2 .5
3 .0
3 .5
4 .0
4 .5
5 .0
5 .5
6 .0
Sn(m/s)
p = 3 b a r
p = 2 .5 b a r
p = 2 b a r
p = 1 .5 b a r
p = 1 b a r
( c )
100% LPG 20 % H2 60 % H2 80 % H2
34. 1 . 0 1 . 5 2 .0 2 . 5 3 . 0
I n it ia l P r e s s u r e ( b a r )
1 .0
1 .5
2 .0
2 .5
3 .0
3 .5
4 .0
4 .5
5 .0
5 .5
6 .0
Sn(m/s)
1 0 0 % L P G
2 0 % H 2
4 0 % H 2
6 0 % H 2
8 0 % H 2
Variation of Sn with Initial
Pressures for LPG with Various
Hydrogen Blends at ( =1).ϕ
0 .8 0 0 . 9 0 1 .0 0 1 . 1 0 1 .2 0 1 . 3 0
E q u iv a le n c e R a tio
1 .0
1 .5
2 .0
2 .5
3 .0
3 .5
4 .0
4 .5
5 .0
5 .5
6 .0
Sn(m/s)
1 0 0 % L P G
2 0 % H 2
4 0 % H 2
6 0 % H 2
8 0 % H 2
Variation of Sn with Equivalence
Ratios for LPG with Various
Hydrogen blend.
0 2 0 4 0 6 0 8 0 1 0 0
H y d r o g e n B le n d ( % )
1 .0
1 .5
2 .0
2 .5
3 .0
3 .5
4 .0
4 .5
5 .0
5 .5
6 .0
Sn(m/s)
P = 3 b a r
P = 2 . 5 b a r
P = 2 b a r
P = 1 . 5 b a r
P = 1 b a r
Variation of Sn with Hydrogen
blend with different initial
Pressure.
Factors Effect on Stretched Laminar Flame Speed
Hydrogen Blend at
Atmospheric Pressure
Stoichiometry at
Atmospheric Pressure
Initial Pressure
All Data at Flame Radius of 20 mm 01:12 PM
35. Φ=0.8
Φ=1
Φ=1.3
Stretched rate
100% LPG 20 % H2 60 % H2 80 % H2
0 1 0 0 2 0 0 3 0 0 4 0 0 5 0 0
S t r e t c h R a t e ( 1 / s )
1 .0
1 . 5
2 .0
2 .5
3 . 0
3 .5
4 .0
4 . 5
5 .0
5 .5
Sn(m/s)
P = 3 b a r
p = 2 . 5 b a r
p = 2 b a r
p = 1 . 5 b a r
p = 1 b a r
( a )
1 0 0 2 0 0 3 0 0 4 0 0 5 0 0 6 0 0 7 0 0 8 0 0 9 0 0
S t r e t c h R a t e ( 1 / s )
1 .0
1 . 5
2 .0
2 .5
3 . 0
3 .5
4 .0
4 . 5
5 .0
5 .5
Sn(m/s)
P = 3 b a r
p = 2 . 5 b a r
p = 2 b a r
p = 1 . 5 b a r
p = 1 b a r
( b )
1 0 0 2 0 0 3 0 0 4 0 0 5 0 0 6 0 0
S tr e tc h R a te ( 1 /s )
1 . 0
1 . 5
2 . 0
2 . 5
3 . 0
3 . 5
4 . 0
4 . 5
5 . 0
5 . 5
Sn(m/s)
P = 3 b a r
p = 2 .5 b a r
p = 2 b a r
p = 1 .5 b a r
p = 1 b a r
( c )
0 1 0 0 2 0 0 3 0 0 4 0 0 5 0 0 6 0 0
S t r e t c h R a t e ( 1 / s )
1 . 0
1 . 5
2 . 0
2 . 5
3 . 0
3 . 5
4 . 0
4 . 5
5 . 0
5 . 5
Sn(m/s)
p = 3 b a r
p = 2 . 5 b a r
p = 2 b a r
p = 1 . 5 b a r
p = 1 b a r
( a )
0 1 0 0 2 0 0 3 0 0 4 0 0 5 0 0 6 0 0 7 0 0
S t r e t c h R a t e ( 1 / s )
1 . 0
1 . 5
2 . 0
2 . 5
3 . 0
3 . 5
4 . 0
4 . 5
5 . 0
5 . 5
Sn(m/s)
p = 3 b a r
p = 2 . 5 b a r
p = 2 b a r
p = 1 . 5 b a r
p = 1 b a r
( b )
0 1 0 0 2 0 0 3 0 0 4 0 0 5 0 0 6 0 0
S t r e t c h R a t e ( 1 / s )
1 . 0
1 . 5
2 . 0
2 . 5
3 . 0
3 . 5
4 . 0
4 . 5
5 . 0
5 . 5
Sn(m/s)
p = 3 b a r
p = 2 . 5 b a r
p = 2 b a r
p = 1 . 5 b a r
p = 1 b a r
( c )
0 2 0 0 4 0 0 6 0 0 8 0 0 1 0 0 0 1 2 0 0
S t r e t c h R a t e ( 1 / s )
1 . 0
1 . 5
2 . 0
2 . 5
3 . 0
3 . 5
4 . 0
4 . 5
5 . 0
5 . 5
Sn(m/s)
p = 3 b a r
p = 2 .5 b a r
p = 2 b a r
p = 1 .5 b a r
p = 1 b a r
( a )
0 2 0 0 4 0 0 6 0 0 8 0 0 1 0 0 0 1 2 0 0
S t r e t c h R a t e ( 1 / s )
1 . 0
1 . 5
2 . 0
2 . 5
3 . 0
3 . 5
4 . 0
4 . 5
5 . 0
5 . 5
Sn(m/s)
p = 3 b a r
p = 2 . 5 b a r
p = 2 b a r
p = 1 . 5 b a r
p = 1 b a r
( b )
0 2 0 0 4 0 0 6 0 0 8 0 0 1 0 0 0
s tr e tc h r a t e ( 1 /s )
1 . 0
1 . 5
2 . 0
2 . 5
3 . 0
3 . 5
4 . 0
4 . 5
5 . 0
5 . 5
Sn(m/s) p = 3 b a r
p = 2 . 5 b a r
p = 2 b a r
p = 1 . 5 b a r
p = 1 b a r
( c )
0 2 5 0 5 0 0 7 5 0 1 0 0 0 1 2 5 0 1 5 0 0 1 7 5 0
S tr e t c h R a t e ( 1 / s )
1 . 0
1 . 5
2 . 0
2 . 5
3 . 0
3 . 5
4 . 0
4 . 5
5 . 0
5 . 5
Sn(m/s)
p = 3 b a r
p = 2 . 5 b a r
p = 2 b a r
p = 1 . 5 b a r
p = 1 b a r
( a )
0 2 5 0 5 0 0 7 5 0 1 0 0 0 1 2 5 0 1 5 0 0
S tr e tc h R a te ( 1 /s )
1 .0
1 .5
2 .0
2 .5
3 .0
3 .5
4 .0
4 .5
5 .0
5 .5
Sn(m/s)
p = 3 b a r
p = 2 .5 b a r
p = 2 b a r
p = 1 .5 b a r
p = 1 b a r
( b )
0 2 5 0 5 0 0 7 5 0 1 0 0 0
S tr e tc h R a te ( 1 / s e c )
1 .0
1 .5
2 .0
2 .5
3 .0
3 .5
4 .0
4 .5
5 .0
5 .5
Sn(m/s)
p = 3 b a r
p = 2 .5 b a r
p = 2 b a r
p = 1 .5 b a r
p = 1 b a r
( c )
36. Unstretched Flame
Propagation Speed Versus
Different Initial Pressure for
Stoichiometric Mixtures
Unstretched Flame
Propagation Speed Versus
Equivalence Ratios with
Different Hydrogen Blends.
Unstretched Flame Propagation
Speed Versus Hydrogen Blends
for Stoichiometric Mixtures
Factors Effect on Unstretched Laminar Flame Speed
Hydrogen Blend at
Atmospheric Pressure
Stoichiometry at
Atmospheric Pressure
Initial Pressure
1 . 0 1 .5 2 .0 2 .5 3 .0
I n it ia l P r e s s u r e ( b a r )
1 .0
1 .5
2 .0
2 .5
3 .0
3 .5
4 .0
4 .5
5 .0
5 .5
6 .0
Sl(m/s)
1 0 0 % L P G
2 0 % H 2
4 0 % H 2
6 0 % H 2
8 0 % H 2
0 .7 0 .8 0 .9 1 . 0 1 .1 1 .2 1 . 3 1 .4
E q u iv a le n c e R a tio
1 .0
1 .5
2 .0
2 .5
3 .0
3 .5
4 .0
4 .5
5 .0
5 .5
6 .0
Sl(m/s)
L P G
2 0 % H 2
4 0 % H 2
6 0 % H 2
8 0 % H 2
0 2 0 4 0 6 0 8 0
H y d r o g e n B le n d ( % )
1 . 0
1 . 5
2 . 0
2 . 5
3 . 0
3 . 5
4 . 0
4 . 5
5 . 0
5 . 5
6 . 0
Sl(m/s)
p = 3 b a r
p = 2 . 5 b a r
p = 2 b a r
p = 1 . 5 b a r
p = 1 b a r
01:12 PM
37. Laminar Burning Velocity Versus
Initial Pressure for Different
Hydrogen Blend at Stoichiometric
Mixture
Laminar burning velocity
versus equivalence ratio for
different hydrogen blend at
atmosphere pressure
Laminar burning velocity
versus hydrogen blend for
different equivalence ratio
at atmosphere pressure
Factors Effect on Unstretched Laminar Burning Velocity
Hydrogen Blend at
Atmospheric Pressure
Stoichiometry at
Atmospheric Pressure
Initial Pressure
1 . 0 1 . 5 2 . 0 2 . 5 3 . 0
I n it ia l P r e s s u r e ( b a r )
2 0
3 0
4 0
5 0
6 0
ul(cm/s)
1 0 0 % L P G
2 0 % H 2
4 0 % H 2
6 0 % H 2
8 0 % H 2
0 . 8 0 .9 1 . 0 1 . 1 1 .2 1 . 3
E q u a v a la n c e R a t io
2 0
3 0
4 0
5 0
6 0
ul(cm/s)
L P G
2 0 % H 2
4 0 % H 2
6 0 % H 2
8 0 % H 2
0 2 0 4 0 6 0 8 0
H y d r o g e n B le n d ( % )
2 0
3 0
4 0
5 0
6 0
ul(cm/s)
φ = 0 .8
φ = 1
φ = 1 .3
01:12 PM
39. Flame Thickness Versus Equivalence
Ratio for different Hydrogen Blend at
Initial Pressure of 1.0 bar
Maximum Combustion Pressure Versus
Hydrogen blend for different Initial
Pressure at Equivalence Ratio =1.3.
Flame Thickness and Combustion Pressure
Combustion PressureFlame Thickness
0 .8 0 .9 1 .0 1 .1 1 .2 1 .3
φ
0 .0
0 .1
0 .2
0 .3
0 .4
0 .5
δ(mm)
L P G
2 0 % H 2
4 0 % H 2
6 0 % H 2
8 0 % H 2
0 2 0 4 0 6 0 8 0
H y d r o g e n B le n d ( % )
0
5
1 0
1 5
2 0
2 5
3 0
3 5
4 0
MaximumPressure(bar)
p = 3 b a r
p = 2 . 5 b a r
p = 2 b a r
p = 1 . 5 b a r
p = 1 b a r
01:12 PM
41. Conclusions
• A new experimental apparatus has been built for the
measurement of laminar flame speed and burning
velocity of the fuel-air mixture.
• Experiments are conducted to study LBV of LPG at
different H2 blends under varying initial pressure of 0.1-
0.3 MPa and temperature of 308 K.
• H2 addition accelerates LBV of LPG flames for all
equivalence ratios and pressures. The effectiveness is
more evident when H2 blend is larger than 60%.
01:12 PM
42. Conclusions
• Increasing the initial pressure, decreases LBV.
• Increasing H2 blend decreases the flame thickness while
increases with increasing the initial pressure.
• H2 addition increases thermal diffusivity of reacting
mixtures, the density ratio and adiabatic flame
temperature.
• Combustion pressure increases with increasing the
equivalence ratio, H2 blends and initial pressure.
• Correlations between variables are derived for H2-LPG-air
mixtures.
01:12 PM
43. Suggestions for Future Work
• Using the experimental apparatus to study LBV for other
types of gaseous fuels.
• Modifying the rig to study LBV for other types of liquid
fuels.
• Studying the effect of initial temperature on LBV.
• Improving the capturing unit by replacing the current unit
by Z-type schlieren photography or using another two
perpendicular windows with two high-speed cameras to
perform the capturing measurements.
01:12 PM
44. Suggestions for Future Work
• Developing the CVC to derive burning velocity
measurements from the pressure history record.
• Increasing the diameter of the glass window to detect
cellularity.
• Modifying ignition unit to study the effect of ignition energy
and spark gap.
• Extending the theoretical part to study the laminar burning
velocity of blended fuel theoretically.
01:12 PM
