Numerical Study of Hydrogen enrichment and injector nozzle number
impacts on non-premixed turbulent combustion characteristics in a Gas
Turbine cannular Combustion Chamber
B.N. HAGANI 1, H. BOUSBAA 1, M. BENCHERIF 2
1 Mechanical Depertment, National Polytechnic school, LTE MA Oran, ALGERIA
2 Mechanical Depertment, USTO, LTE-ENPO MA, ALGERIA
Abstract: - A numerical study on non-premixed combustion methane/air mixture, Hydrogen enrichment and
injector nozzle number in swirl combustor is investigated using the Computational Fluid Dynamics CFD code.
The method is based on the solution of Navier-Stokes unsteady equations using unstructured grid due to the
complexity of geometry of the combustor. The turbulence modeling is carried out by RNG/k-ε) turbulence
model. The H2 amount in the fuel mixture varies under constant volumetric fuel flow between 0 and 40% and
the injector nozzle number is 4, 6 and 8. Results of this simulation show as the hydrogen rate increases, flame
temperature, CO increases and CO2 decreases. On the other hand, the injector nozzle number minimizes the
NOx and increases the CO level.
Key-Words: - Gas turbine, Combustion characteristics, hydrogen, nozzle number, non-premixed, emissions,
numerical simulation.
Received: March 23, 2024. Revised: August 17, 2024. Accepted: September 21, 2024. Published: October 17, 2024.
1. Introduction
In recent years, industrial gas turbines have played
an important role in power generation systems, such
as nuclear power plants, power plants and
hydrocarbon units, they are distinguished by their
adaptation to simple cycles, combined or highly
efficient cogeneration.
The power of a gas turbine is controlled by the heat
input, which is generated by the combustion of the
fuel/oxidant mixture in the combustion chamber one
of the components of the gas turbine which has
undergone several modifications and evolutions in
order to improve the performance of these machines
and also reduce the polluting gases generated at the
end of the combustion reaction [1].
There are several types of combustion such as
turbulent non-premixed combustion where there is
the interaction between two phenomena, that of
chemistry and the other of turbulence. Given the
complexity of the combustion phenomenon, their
experimental investigation poses a lot of questions,
difficulties, so this approach remains expensive and
limited to certain operating conditions, however,
numerical calculation may constitute the most
suitable solution given the progress made in the
field of computing and modeling [2].
Several numerical and experiment studies on the
combustion in chamber of gaz turbine have been
which showed that the combustion is influenced by
several parameters such as oxygen or hydrogen
enriched and velocities admission. The combustion
of methane-air mixture and oxygen enriched in gas
turbine combustion chamber was experimented
numerically by different studies: Habib et al. [3]
studied experimentaly the atmospheric diffusion
oxy-fuel combustion flame in a gas turbine
combustor alimented with CH4 and a mixture of
CO2 and O2. in this study different operating
parameters are considered as equivalence ratio (0.5–
1), ratio of mixture O2/CO2. The objectif of the
study focus to the percentages of O2 to get a stable
flame and the meseare of flame and exhaust gas
temperatures in combustion chamber. The results
indicate the flame is very stable at the mixture ratio
of 0.65 and flue gas temperatures are reduced with
the increase of the equivalence ratio. Zhang et al. [4]
studied the the effects natural gas combustion under
different oxygen concentrations on flame
characteristics NO production and flame kinetics.
the results indicate, With the addition of oxygen, the
flame temperature, the heat release rate and NO
emission are increased. On the contrary, and the
flame thickness decreases. Xu et al. [5] stidies
numerically the effect of oxygen concentrations
(19.5-36%) and velocities admission (47.16-261.18
m/s) on combustion and NO emission. Overall, the
results show that the non-premixed air/oxygen
combustion can provide low NO emission if
combustion air with low oxygen contents is
employed, while for highly oxygen-enriched
concentration, the together adition oxygen with high
velocity is suggested. Hussein and Salih [6] studied
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numerically, the effect of the oxygen ratio for
methane–air combustion and compared with
experiment study. From the results, its clear that was
an improvement in the combustion with the
increasing in oxygen ratio.
For the combustion of methane-air mixture and
hydrogen enriched in gas turbine combustion
chamber was experimented numerically by different
studies: Gregory et al [7] studied numericallycarried
out by on the influence of hydrogen addition on the
response of the methane lean premixed flame, where
they found that it increases the flame speed and
therefore subsequently its maximum stretch rate that
causes extinction.
Cozzi and Coghe [8] studied the influence of natural
gas mixed with hydrogen fuel n the non-premixed
burner. The results showed that adding hydrogen,
the soot, CO and NOx emissions increased.Park et
al. [9] studied the effect of hydrogen addition (0–
30%) in the methane/air lean-premixed flame. The
analysis showed that the doping of hydrogen to
methane/air mixtures will increase the flame
temperature also NO concentration.
Shin and Cho [10] studies the effect of Hydrogen
enrichement on temperature, flame speed and
emissions (NOx, CO) using CHEMKIN-Pro with
GRI 3.0 detailed chemistry in gas turbine fuelled
with GNL (Gas Naturan Liquid). The results
indicate the increase of flame temperature and the
flame speed. However, addition of Hydrogen
reduces CO emissions and increases NOx
emissions. Pignatelli et al. [11] studied numerically
the impact of pilot flame, Reynolds number and
hydrogen-enriched methane on the performance and
emissions in dry-low-emission (DLE) burner-based
gas turbine engines. From the results, its clear the
Reynolds number the positive impact on the pilot
flame and the NOx and CO emissions decrease
lower with increasing hydrogen ratio.Zhang et al.
[12] studied numerically the effect of hydrogen
addition (0–75%) for analyzing the effects of
blended fuel and thermal boundaries on the
combustor thermal environment on a dry-low-
emission combustor. The results show that when
the fuel hydrogen volume percentage increases, the
maximum gas temperature and H2O concentration
on the central axis of the combustor increase.
In the present work we will study in the first time
the effect of mixture CH4/H2 at different fractions in
non-premixed turbulent combustion chamber, also
the influence of introducing a quantity of air as
dilution air on the shape and temperature of the
flame and therefore the emissions of NOx and CO.
In the second time, the impacts of injector nozzle
number in combustion and emissons characteristics
in a Gas Turbine cannular Combustion Chamber,
where the design of the latter was carried out by the
Solidworks design software and the numerical
simulation by the ANSYS CFX16.2 software.
2. Numerical model setup
2.1 Governing equations:
Any modeling problem in combustion is based on
the equations of aerothermochemistry, a system
comprising the conservation equations of chemical
species, mass, momentum, energy and the equation
of state given as follows [13]:
Continuity equation for species m :

 



(1)
With :

Total mass equation :

 

(2)
Momentum equation for the fluid mixture:

 



(3)
Where the viscous stress tensor is defined by:
 󰇧

󰇨󰆒


Where, is fluid velocity, is density, is source
term, P is fluid pressure, is viscosity, ′ expansion
viscosity (set to zero),  is Kronecker delta.
With:  

Internal energy equation:

 

 

 


󰇗󰇗 (4)
Where󰇗 and 󰇗are terms due to spray interactions
and chemical heat, respectively.
The transport coefficients are given by the following
relations:
c
S
D
and
r
p
P
C
K
The air-fuel mixture introduced inside the cylinder
is assumed to be an ideal gas whose behavior
equations are:
󰇡
󰇢
(5)
󰇛󰇜󰇡
󰇢
󰇛󰇜 (6)
󰇛󰇜󰇡
󰇢
󰇛󰇜 (7)
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󰇛󰇜󰇛󰇜
(8)
2.2 Turbulence model
In this study, the determination of the residual stress
terms in the governing equations was carried out by
applying the RNGk-ε turbulence model as a closure
technique.
The standard RNG K-ε turbulence model is a
modeling approach that stems from the unsteady
Navier-stockes equations using a mathematical
technique called Re-normalization-Group. This
improved model incorporates a modification in the
dissipation equation “ε” to better account for
turbulent characteristics at finer scales [14].
The turbulent kinetic energy and dissipation
equations of the model are as follows:
Kinetic energy equation:
󰇛󰇜
 

 
 (9)
Dissipation rate equation:
󰇛󰇜
 

 


(10)
; Represents the production of turbulent kinetic
energy due to the average speed gradient
and ,  : are constants.
and are the inverses of the effective Prandtl
numbers for k and ε respectively.
2.3 Combustion model
In our study, the Probability Density Function
(PDF) Flamelet model has been selected for
modeling non-premixed combustion.
The term flamelets defines a one-dimensional thin
reactive-diffusive layer embedded in a non-reactive
turbulent flow.
The turbulent diffusion flame can be seen as a
collection of flat laminar flames stretched by
turbulence, but whose internal structure remains
little modified. This vision, introduced by Peters and
Kouznetsovo then widely discussed by [15, 16],
makes it possible to simplify the modeling of the
Chemistry Turbulence interaction. The resolution
method therefore boils down to knowledge of the
relationships that exist between chemistry and the
independent parameters on which it depends (Ζ, χ)
and their statistical distribution. For each species i,
the average mass fraction is written:
󰇛󰇜 󰇛󰇜
󰇛󰇜
(11)
With;
󰇧
󰇨
Or :
: designates the mass fraction of fuel in the fuel
flow.
: designates the mass fraction of oxidant in the
oxidant flow.
: denotes wealth
And : scalar dissipation; which is a structural
characteristic of diffusion flames.
3. Combustor geometry description
and simulation details
The basic combustor geometry (the injector and the
flame tube) of the Cannular type gas turbine is
shown in the figure below. The combustion chamber
size is 777.89 mm in Z direction, 300mm in Y
direction and 230mm in X direction.
Fig. 1 Solid model of combustor flow domain
The inlet primary air is guided by 8 vanes to give
the air a vortex velocity component, the total area of
the main primary air inlet is 57 cm2. Fuel is injected
through six fuel inlets into the swirling primary air
stream, each with an area of 0.14 cm2. Secondary air
is injected into the combustion chamber through
four side air inlets, each with an area of 2 cm2.
Following the study, the combustion chamber is
considered as a single control volume whose nature
is chosen as fluid to avoid the study at the edge of
the walls and therefore focus only on the flow inside
the burning.
3.1 The mesh
The geometric complexity of the configuration
studied prompted us to use an irregular mesh
because the flame can during the calculation be
located in any area of the chamber as well as the
unstructured mesh minimizes the dissipation of the
numerical schemes.
The mesh used is of the tetrahedral type in all the
calculation domain, it contains approximately 27948
nodes and 138351 elements with the areas where we
are interested in seeing the results such as the
injection areas and the dilution air inlet are meshed
finer with a mesh size of 5 mm and the rest of the
geometry with a mesh size of 10 mm, the mesh
geometry is shown in fig.2 below.
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Fig. 2 Mesh geometry of gas turbine can combustor
3.2 Simulation details
To close the aerothermochemical equations system
cited above, the RNG k-ɛ model was chosen to
model turbulence for its robustness and its good
ability to model free shear flows.
Also for the modeling of the non-premixed
combustion of methane, the FLAMLET PDF model
was chosen assuming that the combustion occurs in
thin sheets with an internal structure called a
flamelet, the turbulent flame in our case is then
treated as a set of flamelets. integrated in the flow
field, also the information on the laminar model is
pre-calculated and stored in a library to reduce the
calculation time (PDF table).
To simulate NOx emissions, the Zeldovitch model is
selected; thus the finite volume method and second-
order upwind are used to solve the Naiver-Stokes
equations acting on the flow.
The convergence criteria are 10-4 for mass,
momentum, kinetic energy and dissipation rate and
even species conservation equations, for energy
equations and pollutants the convergence criterion is
the order of 10-6.
3.3 Boundary conditions
The table below summarizes the boundary
conditions taken for our study:
Primary
air
Fuel
Secondary
air
Mass fraction of oxygen: YO2=
0.232.
Wall
Wall heat transfer was adiabatic;
Wall boundary condition was no
slip.
Wall roughness was Smooth.
4. Results and discussion
4.1 Aerodynamics characteristics
In order to validate the geometry, a non-reactive
flow is studied whose injected fluid is only air at
289 K and 1.013 atm. The figures below show the
evolution of the streamlines along the geometry and
the velocity fields for the non-reactive case:
Fig. 3: Streamlines (non-reactive case)
From Fig. 3, there are recirculation zones created in
the corners of the chamber due to the sudden
widening;these are the corner recirculation zones
"CRZ", these zones have a very important role, they
promote the attachment of the flame.
Fig. 4 : Velocity fields along the CC (non-reactive
case)
According to Fig.4; we see that the speed in the
combustion chamber is well distributed from the
moment of injection until the exhaust of the
combustion products. From these results we can
validate the aerodynamics of the geometry and
exploit it in the rest of our study.
4.2 Combustion evolution of Methane
This second case corresponds to a reactive flow,
with injection of CH4 fuel. The Fig. 5 below shows
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the current line which manifests itself along the
combustion chamber after fuel injection and the
start of combustion, the color code presented on the
left of the figure represents the values of the speed
axial.
In the primary zone, the low axial velocities at the
center of the combustion chamber indicate the
existence of an internal recirculation zone. The swirl
vanes around the fuel nozzle generate a strong
swirling flow in the combustion air inside the
combustion chamber.
Fig. 5 : Velocity streamline in meridian plan (OYZ)
Fig. 6; represents the contour of the temperature in
the combustion chamber, we notice that the flame
temperature increases along the combustion
chamber, the maximum combustion temperature is
very high, it reaches a value of 2211 K, with a core
offlame of a lower temperature than the flame front
which is at a temperature of about 1500 K, so the
flame is well stretched.
Fig. 6: Temperature distribution along the chamber
The velocity distribution along the combustion
chamber is shown below in fig.7; where it is noted
that the speed in the combustion chamber decreases
by the methane injection speed which is of the order
of 45 m/s at the exit of the chamber (the exhaust) is
this from the point where the mixture Air/Methane
is created and therefore the start of the reaction
between them (start of combustion).
Fig. 7 : Velocity distribution along the chamber
The figures below represent the axial distribution of
the different species such as CH4, O2, CO, NO and
NO2 along the combustion chamber:
Fig. 8 : Distribution of CH4 along the combustion
chamber
Fig.8 shows the axial distribution of CH4 at the start
of its injection, there is a concentration of the latter
at the outlet of the injector which begins to weaken
with the formation of the CH4/Air mixture.
Fig. 9 : Distribution of O2 along the combustion
chamber
The axial distribution of O2 is shown in figure Fig.
9, where there is a concentration of this species in
the injection zone of the two primary and secondary
airs and decreases from the zone where combustion
takes place.
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Fig. 10 : Axial distribution of CO
Fig.10; shows the variation of CO along the
combustion chamber, according to this figure we
observe a variation of the mass fraction of CO
inversely proportional to the flame temperature;
therefore the zones where the flame temperature is
high we observe a low concentration of CO and the
reverse for the zones where the flame temperature is
low.
Fig. 11 : Axial distribution of NO
Fig. 12 : Axial distribution of NO2
The main nitrogen oxides NOx produced during
combustion are nitrogen monoxides NO and
nitrogen dioxides NO2, the axial distribution of
these two species is shown in Fig. 11 and Fig. 12
respectively.
It can be seen that above 1825 K, there will be an
increase in the production of NOx, especially
thermal NOx. The level of NOx emissions from a
combustion chamber depends on the interaction
between physical and chemical processes and is
strongly dependent on temperature.
4.3 Impact of mixture CH4/H2
In this part we will study the effect of hydrogen
injection on the structure of the methane diffusion
flame and the products generated by the latter.
The same boundary conditions of the previous study
will be used to examine the effect of injecting
hydrogen into the central methane jet to fuel the
combustion for different percentage mixtures of
CH4 and H2.
The cases studied are summarized in the table
below:
The fuel
% CH4
% H2
Methane
100
0
Mixture N°1
80
20
Mixture N°2
70
30
MixtureN°3
60
40
Table. 1 : CH4-H2 mixtures
The temperature distribution for the four chosen fuel
configurations with these hydrogen doping (0, 20%,
30% and 40%) are shown in figures (13, a-d)
respectively.
(a)
(b)
(c)
(d)
Fig. 13: Temperature distribution along the chamber
for the four fuels
According to the results presented by the figures
above for the distribution of the temperature with
different fuels where the doping of hydrogen is
different, it is clearly noticed that the flame
temperature increases with the increase in the
quantities of hydrogen injected. The shape of the
diffusion flame changes with the amount of
hydrogen injected where we see that the stretch of
the flame decreases with the increase in the amount
of hydrogen injected into the chamber, so it is
shorter for the case of 40% hydrogen and 60%
Methane.
CO distribution
The figures (14, a-d) show the variation of CO along
the combustion chamber for the four chosen fuel
configurations with these doping hydrogenated (0,
20%, 30% and 40%) respectively.
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(a)
(b)
(c)
(d)
Fig. 14 : Distribution of CO for the four fuels
According to the results shown in the figures (14, a-
d), it can be seen that the addition of hydrogen has a
positive influence on the emissions of the CO where
we note that the addition of hydrogen decreases the
production of CO; for 40% of hydrogen injected we
have only 0.004403 as mass fraction of CO while
for 0% of hydrogen we have 0.006968 of CO (mass
fraction).
CO2 distribution
The figures (15, a-d) show the variation of CO2
along the combustion chamber for the four chosen
fuel configurations with these doping hydrogenated
(0, 20%, 30% and 40%) respectively.
(a)
(b)
(c)
(d)
Fig. 15 : Distribution of CO2 for the four fuels
According to the results of the simulation shown in
the figures above, we have been able to observe the
effect of hydrogen injection with different
concentrations on CO2 emissions, where we have an
inversely proportional relationship between the
addition of hydrogen and the amount of CO2
produced by combustion; we have for 0% of
hydrogen a mass fraction of CO2 of order of 0.1382
whereas for 40% of hydrogen only 0.005571 of
CO2; therefore, a 50% reduction in CO2 emissions.
4.4 Impact of the injector nozzle number
In this part of our study we will study the influence
of the number of fuel injection pores (located in
front of the injector), for this the same boundary
conditions (of temperature, injection speeds and
pressure), the turbulence model, the combustion
model as well as the convergence criteria as the
previous part, except that the geometry and the
mesh change in this part.
The geometries used in this part are shown in the
figures (16, a-c) with 4, 6 and 8 pores respectively.
(a)
(b)
(c)
(c)
Fig. 4 : The geometries used
The mesh: The 3-D modeling of the
combustor and deferent nozzles has been done using
the pre-processors ANSYS CFD (Fig. 17) . the
table 2 present the variation of nodes and elements
numbers with nozzles number.
Fig. 5 :The mesh
The combustion
chamber
Number of
nodes
Number of
elements
With 4 nozzles
26948
133394
With 6 nozzles
27948
138351
With 8 nozzles
27119
134395
Table. 2 : Mesh statistics
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The streamlines for the three injector
nozzle configurations: Figures (18, a-c) show the
streamlines created in the combustion chamber for
the injector configuration with 4, 6 and 8 pores
respectively.
(a)
(b)
(c)
Fig. 18 : The streamlines for the three injector
configurations
According to Fig. 18, we note that the lines of
currents for the three configurations are different,
where we have for the injector with 8 pores a high
speed compared to the two others, as we also note
for the internal recirculation zones which are
responsible for the stability of flame and burning
intensity are well structure with high pore count.
The temperature field for the three injector
nozzle configurations: In the figures (19, a-c) the
temperature distribution for the injector
configuration with 4, 6 and 8 pore is shown
respectively.
(a)
(b)
(c)
Fig. 19 : Temperature distribution for the three
injector configurations
From the figures above, it can be seen that the
number of injection pores influences the shape of
the Methane flame and also its temperature; where
we clearly see that the temperature is high for the
case where only 4 injection pores were used, while
it begins to decrease by increasing the number of
pores.
So by increasing the number of injection pores, the
flame temperature decreases and its shape becomes
more stable for the correct distribution of the fuel,
and this allows us to control the emissions generated
by combustion as we will see later.
The distribution of NO2: Figures (20, a-c)
show that the formation of nitrogen oxides NOx
more precisely NO2 is mainly a function of the
flame temperature of the fuel, the rate of formation
of NOx increases exponentially as the temperature
increases.
So our case where we played on the number of
pores of the injector we see that the increase in
pores decreases the flame temperature and this led
to a decrease in the production of NO2.
There was a decrease in NO2 from the mass fraction
of 1.566×10-3 with a 4 pores injector to a mass
fraction of order 1.516×10-3 with an 8 pores injector.
(a)
(b)
(c)
Fig. 20 : The distribution of NO2 for the three
injector configurations
The distribution of CO: In figures (21, a-c)
the CO distribution for the injector configuration
with 4, 6 and 8 pore is shown respectively.
(a)
(b)
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(c)
Fig. 21 : The CO distribution for the three injector
configurations
According to the results shown in the figure (21, a-
c), we notice that the variation of the numbers of
injection pores influences the formation of CO, we
see that by increasing the number of injection nozzle
from 4 to 8 pores led to an increase in the mass
fractions of this species from a value of 6.789×10-2
for a 4 pore injector to 6.968×10-2 for an 8 pore
injector.
5. Conclusion
This work aims to improve the knowledge and
understanding of the phenomena involved in a non-
premixed turbulent combustion process of Methane,
using the ANSYS CFD 16.2 code. Our first goal
was to characterize the behavior and the different
phenomena involved during the non-premixed
combustion of Methane, the temperature point and
the emissions.The other objective of this work was
to characterize the addition of hydrogen on the
turbulent combustion Methane / air.
In a first calculation, we considered the air
flow in the combustion chamber so the case
without flame, this allowed us to understand the
aerodynamic behavior of the geometry studied
and therefore continue our study.
After the aerodynamic study, the reactive
case was studied where we could see the
streamlines, the speed and temperature contours
and finally the mass fractions of species present
in the combustion chamber such as CH4, CO,
CO2, NO and NO2.
In the second part of our work, the study of
the influence of the addition of Hydrogen at
different concentrations to the non-premixed
flame of Methane was made; where we
characterized the evolution of the flame
temperature as well as the emissions produced by
this reaction, we found that the temperature of
the flame increases with the increase in the
doping by H2 this essentially reduces the CO2 but
we had a slight increase in CO.
In the third part of our work, we will study
the influence of the number of fuel injection
nozzle, its clear that the NOx decreased and the
CO increased with number of nuzzle.
In order to give good results it is necessary
to make a combination between the two
techniques.
References
[1] Boukens Mohamed Walid et GuennounSefiane;
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DOI: 10.37394/232024.2024.4.9
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