Standard vs Custom Battery Packs - Decoding the Power Play
cfd analysis of combustor
1. GUJARAT TECHNOLOGICAL UNIVERSITY, AHMEDABAD
Dissertation entitled
“CFD approach to study the effect of various geometric parameters
on performance of annular type gas turbine combustion chamber”
Prepared By:
Rasaniya Vishal R.
(130680721012)
M.E. – Thermal Engg.
Guided By:
Mr. Deepu Dinesan
Assistant Professor
Mechanical Department
A Dissertation Mid Semester Review
Gujarat Technological University
March-2015
Merchant Institute of Technology, Piludra6/7/2015 1
MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
2. Contents
Introduction
Literature review and It°s Summary
Proposed methodology
Specification of Gas turbine Engine
Existing dimension°s (annular chamber, Swirler, air admission & wall cooling holes)
Modeling
Meshing
CFD Analysis for combustor
Comparisons for combustor
Future work
Work plan
References
6/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA 2
4. Introduction (Continues…)
The following are the important components of the gas turbine combustor:
Diffuser
Swirler
Fuel Injector
Spark Plug
Liner
Casing
46/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
Annular combustor
5. Literature Review
56/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
Title CFD modeling of an Experimental scaled of a trapped vortex combustor[1]
Author /
Publication
A.Di Nardo et al. / Italian national agency for new technology, energy and the
environment-ITALY
Conclusion 1. TVC represent an efficient and compact technique for flame stability.
2. They concluded hydrogen is certainly more reactive and produce less
intermediate specie during combustion. It burns more rapidly than methane
also outside the cavity.
3. Only if a stoichiometric amount of primary air is supplied at lower velocities,
methane TVC performances approach to that of hydrogen and propane.
6. Literature Review
66/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
Title Large Eddy Simulation of turbulent flames in a Trapped Vortex
Combustor(TVC) – A flamelet presumed-pdf closure preserving
laminar flame speed[2]
Author /
Publication
C. Merlin et al. / C. R. Mecanique 340 (2012) 917–932
Conclusion 1. TVC analysing results from Large Eddy Simulation compared against
measurements. The Navier–Stokes equations are solved in their fully
compressible flow.
2. Three cavity flow modes have been reported, which controls the
feeding of the cavity with reactants along with its flushing. The
impact of varying the main flow rate, the cavity geometry and
adding a swirl have been examined.
3. swirling case is found to be the best candidate for practical use of
such burner, since it avoids strong pressure fluctuations resulting
from the interaction of combustion with the cavity flushing modes.
7. Literature Review
76/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
Title Investigation of Radial Swirler Effect on Flow Pattern inside a Gas Turbine
Combustor[3]
Author /
Publication
Yehia A. Eldrainy et al. / Modern Applied Science Vol.3 No. 5 2009
Conclusion 1. They achieved flow pattern inside the combustor using three radian Swirler.
2. Numerical simulation was done using fluent 6.3 and based on standard k-e
model.
3. The 40° vane angle Swirler produced a small volume of recirculation zone
while 50° and 60° vane angle Swirler produced larger recirculation zone size.
4. From the parametric study it is found that 50⁰ Swirler is the best for
producing appropriate recirculation zone with reasonable pressure drop.
9. Literature Review
96/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
Title Investigation of low emission combustors using hydrogen lean direct
injection[5]
Author /
Publication
Daniel Crunteanu, Robert Isac / INCAS BULLETIN, Volume 3, Issue 3/ 2011, pp.
45 – 52 ISSN 2066 – 8201 DOI: 10.13111/2066-8201.2011.3.3.5
Conclusion 1. In this paper all injectors are based on LDI (lean direct injection) technology
with multiple injection point with quick mixing.
2. Two observation were tested. At constant pressure combustor equipped with
N1 injector, p3=0.7 MPa & T3= ranging between 600 and 800 K, results
obtained with hyd. injection are until 3 times lower than using only Jet-A.
3. At constant temperature, pressures ranging between 0.7 and 1 MPa a small
difference of the NOx emissions increase with p3 pressure can be observed.
11. Literature Review
116/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
Title Design and CFD Simulation of Annular Combustion Chamber with Kerosene as
Fuel for 20 kW Gas Turbine Engine[7]
Author /
Publication
K. V. Chaudhari et al. / International Journal of Engineering Research and
Applications (IJERA) ISSN: 2248-9622, Vol. 2, Issue 6, November- December 2012,
pp.1641-1645
Conclusion 1. Numerical investigation and design are carried out of annular type combustor
and k-e model are used for analysis. Wall cooling holes are provided not properly
so suggested redesign for good velocity streamlines.
2. Temperature profile is not uniform at exist of the combustor but dilution holes
achieved better so not uniform distribution of air take place.
3. All fuel injectors in primary zone which suggest primary holes are taken twice
the number of injector so uniform air distribution near each injectors and
uniform temperature distribution at exit of the combustor is achieved.
12. Literature Review
126/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
Title Numerical Investigation of Effect of Swirl Flow in Subsonic Nozzle[8]
Author /
Publication
M. K. Jayakumar, Eusebious T. Chullai / The International Journal Of Science &
Technology (ISSN 2321 – 919X) Vol. 2, issue. 4 2014
Conclusion 1. Investigated the converge section of nozzle at three different angles and
concluded that effect of swirl flow can be reduced by decreasing the
contraction ratio of the nozzle.
2. A three dimensional flow field analysis is carried out using FLUENT. Two
different model is analyzed and compare with each other.
3. From the comparison it observed that axial velocity, tangential velocity and
exit velocity of swirl with nozzle is higher than regular nozzle at 25 m/s and
30 m/s and lower at 35 m/s.
13. Literature Review
136/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
Title A Multiple Inlet Swirler for Gas Turbine Combustors[9]
Author /
Publication
Yehia A. Eldrainy et al. / World Academy of Science, Engineering and Technology
Vol:3 2009-05-26
Conclusion 1. In this paper multiple inlet swirl number at the same air inlet mass flow rate.
2. The performance and main characteristics of the new Swirler was examined
through four numerical simulations. These simulations evidently proved that
the Swirler number changes with the variation of tangential to axial flow rate
ratio, enabling the tuning of swirl number according to turbine load.
3. This concept is to increase the combustion efficiency because of its ability to
produce high swirl number at low turbine load.
14. Literature Review
146/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
Title Large Turbulence Creation Inside A Gas Turbine Combustion Chamber
Using Perforated Plate[10]
Author /
Publication
S.R. Dhineshkumar, B. Prakash, S. R. Balakrishnan / International Journal of
Engineering Research & Technology (IJERT) Vol. 2 Issue 5, May - 2013
Conclusion 1. Two Perforated plates concept are used in the place of Swirlers in gas turbine
combustion chamber.
2. Researcher shows effect on the flow pattern within the combustor model, the
1st perforated plate produced a small volume of recirculation zone while 2nd
perforated plate produces a large recirculation zone size.
3. From the parametric studies various angle of holes in perforated plate, it is
found that 30° holed perforated plate is the best for producing appropriate
recirculation zone with reasonable pressure drop.
15. Literature Review
156/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
Title Reference Area Investigation in a Gas Turbine Combustion Chamber Using
CFD[11]
Author /
Publication
Fagner Luis Goular Dias et al. / Journal of Mechanical Engineering and
Automation 2014, 4(2): 73-82 DOI: 10.5923/j.jmea.20140402.04
Conclusion 1. K-e model and P1 model was used for turbulent flow and radiation heat
transfer. In case 1 temperature was increased 1028.17 K to 1123 K.
2. In case 2 some improvements in the original geometry to reduce the velocity
inside the combustion chamber and improve the burning process, NO
emission level will be lower because of distribution of temperature.
3. In case 3 the velocity profile after the modifications. the Swirler outlet flow
was improved. The increasing of reference area, to reduce the burning rate in
the region and improving the combustion process.
16. Literature Review
166/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
Title Designing, Modeling and Fabrication of Micro Gas turbine Combustion
Chamber[12]
Author /
Publication
P.Anand et al. / Internationl Journal of Current Research and Academic Review
ISSN: 2347-3215 Volume 2 Number 9 (September-2014) pp. 99-107
Conclusion 1. All fabricated assembly of combustion chamber is done as per design data. Before
testing of the complete system they passed air to check any leakage in the system.
2. Three experiments are done, in 1st experiment fuel pressure and air pressure 3 bar
and 4 bar exit temperature is 502 k. In 2nd and 3rd experiment fuel and air pressure
is gradually increased 4 bar, 5.8 bar and 5 bar, 6 bar corresponding exit
temperature noted 585 k, 695 k.
3. As with the increase in pressure of the working fluid, exit temperature of the
combustion chamber is also increases. These experimental evaluations have major
role in the entire selection of the material.
17. Literature Review
176/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
Title The CFD Analysis of Turbulence Characteristics in Combustion Chamber with
Non Circular Co-Axial Jets[13]
Author /
Publication
N L Narasimha Reddy et al. / IOSR Journal of Mechanical and Civil Engineering
(IOSR-JMCE) e-ISSN: 2278-1684,p-ISSN: 2320-334X, Volume 6, Issue 2 (Mar. - Apr.
2013), PP 01-10
Conclusion 1. This paper is shows the Modeling of co–axial fuel injector (circular and non-
circular). Analysis on these modeled shapes has been done based on mass flow
rate. Obtained results shown a good turbulence kinetic energy in non – circular
shape compared to circular shape except circle – square one.
2. The main drawback in this paper is it°s not providing good turbulence kinetic
energy and turbulence eddy dissipation in Circle – Square shape as compare with
circular coaxial jet used as fuel injector. Where else Circle – Hexagonal shape
produce 20.3% and 17.6% more turbulence K.E and turbulence eddy dissipation
respectively than circular coaxial jet.
18. Literature Review
186/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
Title Computational study of an aerodynamic flow through a micro-turbine
engine combustor[14]
Author /
Publication
Marian Gieras, Tomasz Sta´nkowski / Open Access Journal Journal of Power
Technologies 92 (2) (2012) 68–79 Warsaw University of Technology, Poland
Conclusion 1. The total pressure loss in the combustor (cold flow) is approximately 10%, the
increase in the mass flow of air through the combustor causes a sharp increase
in the total loss of total pressure.
2. In this paper to obtain a smaller loss of pressure it is necessary to optimize the
geometry of the whole combustion chamber.
3. the Reynolds averaged Navier-Stokes turbulence model (RANS) seems to be
a relatively good, simplified engineering tool which can be used for
preliminary numerical simulations of an aerodynamic flow and combustion
problems
19. Literature Summary
On the basis of literature review it can be concluded that the fluid flow has
very complex and essential to observe it for proper combustion of fuel.
The estimation of pressure drop is very much required for effective
combustion of fuel inside the combustor.
The air distribution through different zone holes has very much effect on
the mixing the fuel and its combustion.
The velocity in all directions is also gives the information of mixing and
burning of fuel. For stability of flame the flow pattern of air and fuel is very
essential.
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20. Geometrical Data collection from SVNIT LABORATORY
Prepare 3D Model based on Geometrical Data using solid works 2013.
Prepare Cavity Model of Annular Type Gas Combustion Chamber.
Mesh Generation in ANSYS Workbench Mesh Module.
Perform k-e model for turbulence flow, PDF model for non-premixed as for combustion
in the ANSYS Fluent.
Perform CFD Analysis in ANSYS Fluent.
Optimize performance by changing location of swirl angle, location and diameter of fuel
nozzle hole, primary, secondary and dilution zone holes and fuel mixture etc.
20
Proposed Methodology
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21. 216/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
For annular chamber design
Outer casing Radius = 92.5 mm
Outer Liner Radius = 85 mm
Inner Liner Radius = 27.5 mm
Inner casing Radius = 15 mm
Number of Nozzles = 8
Equation for annular chamber design[13]
Ldome = (Dliner – Dswirl)/2 * tanөdome
Dref,1 = 0.6 Dref
Ltot = LPZ + LDZ
Q = TMAX – T4/T4-T3
LDZ = 0.2Dliner
LPZ = 0.9Dliner
Existing Dimension’s
Dome region[13]
Primary and dilution zone length[13]
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For Swirler design
Injector diameter = 12 mm
Hub and Ring thickness = 1.5 mm
Hub diameter = 15 mm
Vanes thickness = 2 mm
Swirler axial width = 5.5 mm
Typical ranges values for design[13]
Vane angle, θ = 30°–60°
Vane thickness, tυ = 0.7–1.5 mm
Number of vanes, nυ = 8–16
ΔPsw = 3%–4% of P3
Ksw = 1.3 for flat vanes, and 1.15 for curved vanes
Existing Dimension’s
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case 1
degree fuel nozzle hole size air admission holes
outer liner (40 no°s) inner liner (24 no°s)
primary secondary dilution primary secondary dilution
45 diameter 1mm 5 mm 6 mm 6 mm 3 mm 4 mm 4 mm
50 diameter 1mm 5 mm 6 mm 6 mm 3 mm 4 mm 4 mm
60 diameter 1mm 5 mm 6 mm 6 mm 3 mm 4 mm 4 mm
cooling holes
outer liner (80 no°s) inner liner (48 no°s)
2 mm diameter in 4 row°s
Dimension’s for vane angle,
air admission and cooling
holes
case 2
degree fuel nozzle hole size air admission holes
outer liner (40 no°s) inner liner (24 no°s)
primary secondary dilution primary secondary dilution
45 diameter 1.4 mm 5 mm 6 mm 7 mm 4 mm 5 mm 6 mm
50 diameter 1.4 mm 5 mm 6 mm 7 mm 4 mm 5 mm 6 mm
60 diameter 1.4 mm 5 mm 6 mm 7 mm 4 mm 5 mm 6 mm
cooling holes
outer liner (80 no°s) inner liner (48 no°s)
1.5 mm diameter in 3 row°s
29. Meshing (Ansys R15.0)
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Create mesh
Type of mesh: - 3D
Type of Element: -Tetrahedral
Fig. types of cell shapes
30. Meshing (Ansys R15.0)
Continues…
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Fig. Terminology
TERMINOLOGY
Cell = control volume into
which domain is broken up.
Node = grid point.
Cell centre = centre of a cell.
Edge = boundary of a face.
Face = boundary of a cell.
Zone = grouping of nodes, faces,
and cells:
Wall boundary zone.
Fluid cell zone.
Domain = group of node, face
and cell zones.
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Define turbulence model and Species model for CFD analysis
Turbulence model : K-epsilon model
Where,
k is the turbulence kinetic energy and is defined as the variance of the fluctuations in
velocity. It has dimensions of (L2 T-2); for example, m2/s2.
ε is the turbulence eddy dissipation (the rate at which the velocity fluctuations dissipate),
as well as dimensions of k per unit time (L2 T-3) (e.g., m2/s3).
The general transport equation for mass, momentum, energy.
CFDAnalysis for combustor
(Ansys Fluent)
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The k-ε model introduces two new variables into the system of equations.
CONTINUTITY EQUATION :
CFDAnalysis for combustor
(Ansys Fluent) continues…
∂ρ/∂t + ▼. (ρV) = 0
where ρ is the fluid density and V is fluid velocity given by
V = ui + vj + wk
MOMENTUM EQUATIONS :
The equation for the Newton°s second law or momentum equations for viscous flow are
given by
∂ (ρu)/∂t + ▼. (ρuV) = -∂p/∂x + ∂τxx/∂x + ∂τyx/∂y + ∂τzx/∂z +ρfx
∂ (ρv)/∂t + ▼. (ρvV) = -∂p/∂y + ∂τxy/∂x + ∂τyy/∂y + ∂τzy/∂z +ρfy
∂ (ρw)/∂t + ▼. (ρwV) = -∂p/∂z + ∂τxz/∂x + ∂τyz/∂y + ∂τzz/∂z +ρfz
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CFDAnalysis for combustor
(Ansys Fluent) continues…
FLUENT SOLVER
• The pressure-based solver is applicable for a
wide range of flow regimes from low speed
incompressible flow to high-speed
compressible flow.
Requires less memory (storage).
Allows flexibility in the solution
procedure.
• Choosing k-epsilon for turbulent flow and
non- premixed combustion for species
model.
39. Species model : Non Premixed combustion
6/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA 39
CFDAnalysis for combustor
(Ansys Fluent) continues…
40. Species model : Non Premixed combustion
6/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA 40
CFDAnalysis for combustor
(Ansys Fluent) continues…
41. Species model : Non Premixed combustion
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CFDAnalysis for combustor
(Ansys Fluent) continues…
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Inlet boundary condition for CFD analysis
Material selection = Mixture
Air fuel ratio = 30
Fuel air ratio = 8.64*10^-3
Air mass flow rate = 0.4433 kg/s
Fuel flow rate = 3.83*10^-3 kg/s
Calculated values
Mass flow rate of primary air inlet = 0.1149 kg/s
Mass flow rate of secondary air inlet = 0.3283 kg/s
CFDAnalysis for combustor
(Ansys Fluent) continues…
Calculation
ma/mf = 30
(ma)p = mf * 30
= 3.83*10-3
= 0.1149 kg/s
(ma)T = (ma)p + (ma)s
(ma)s = 0.4432 – 0.1149
= 0.3283 kg/s
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Run calculation for 1000 iterations for reactive case and isothermal case
Get the result
CFDAnalysis for combustor
(Ansys Fluent) continues…
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Total Pressure
CFDAnalysis for combustor
(Ansys Fluent) reactive cases
45°- case 1 45°- case 2
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Total Pressure
CFDAnalysis for combustor
(Ansys Fluent) reactive cases
50°- case 250°- case 1
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Total Pressure
CFDAnalysis for combustor
(Ansys Fluent) reactive cases
60°- case 1 60°- case 2
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Velocity Magnitude
CFDAnalysis for combustor
(Ansys Fluent) reactive cases
45°- case 1 45°- case 2
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Velocity Magnitude
CFDAnalysis for combustor
(Ansys Fluent) reactive cases
50°- case 1 50°- case 2
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Velocity Magnitude
CFDAnalysis for combustor
(Ansys Fluent) reactive cases
60°- case 1 60°- case 2
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Static Temperature
CFDAnalysis for combustor
(Ansys Fluent) reactive cases
45°- case 1 45°- case 2
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Static Temperature
CFDAnalysis for combustor
(Ansys Fluent) reactive cases
50°- case 1 50°- case 2
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Static Temperature
CFDAnalysis for combustor
(Ansys Fluent) reactive cases
60°- case 1 60°- case 2
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Total pressure
CFDAnalysis for combustor
(Ansys Fluent) isothermal
cases
45°- case 1 45°- case 2
50°- case 1 50°- case 2
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Total pressure
CFDAnalysis for combustor
(Ansys Fluent) isothermal
cases
60°- case 1 60°- case 2
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Velocity magnitude (m/s)
CFDAnalysis for combustor
(Ansys Fluent) isothermal
cases
45°- case 1 45°- case 2
50°- case 1 50°- case 2
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Velocity magnitude (m/s)
CFDAnalysis for combustor
(Ansys Fluent) isothermal
cases
60°- case 1 60°- case 2
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Comparison of Pressure for
different cases
Sr
no
Parameters
45 degree 50 degree 60 degree
45 degree-1mm-
case 1
45 degree-1.4 mm-
case 2
50 degree-1mm-
case 1
50 degree-1.4 mm-
case 2
60 degree-1mm-
case 1
60 degree-1.4 mm-
case 2
Reactive
case
Isotherma
l case
Reactive
case
Isotherma
l case
Reactive
case
Isotherma
l case
Reactive
case
Isotherma
l case
Reactive
case
Isotherma
l case
Reactive
case
Isotherma
l case
1 static pressure (pa) 26000 23200 27900 25400 18100 18200 26600 24300 37300 33500 40200 37600
2
dynamic pressure
(pa)
16400 18800 11400 11500 14500 14500 11700 11300 14100 16200 12100 12100
3 total pressure (pa) 27300 24400 29300 26900 20500 20400 28200 25800 38200 34300 41400 38700
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Comparison ofVelocity for
different cases
Sr
no
Parameters
45 degree 50 degree 60 degree
45 degree-1mm-
case 1
45 degree-1.4 mm-
case 2
50 degree-1mm-
case 1
50 degree-1.4 mm-
case 2
60 degree-1mm-
case 1
60 degree-1.4 mm-
case 2
Reactive
case
Isotherma
l case
Reactive
case
Isotherma
l case
Reactive
case
Isotherma
l case
Reactive
case
Isotherma
l case
Reactive
case
Isotherma
l case
Reactive
case
Isotherma
l case
1
velocity magnitude
(m/s)
221 193 189 140 207 208 186 139 204 184 183 140
2 x velocity (m/s) 104 104 110 109 87.1 84.2 131 130 127 127 133 128
3 y velocity (m/s) 150 148 124 123 150 150 127 122 148 146 129 129
5 z velocity (m/s) 61.3 59.1 71.5 69.3 62.2 62.9 83.9 79.9 62.5 61.5 71.3 66.6
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Comparison of temperature
for different cases
Sr
no
Parameters
45 degree 50 degree 60 degree
45 degree-1mm-
case 1
45 degree-1.4 mm-
case 2
50 degree-1mm-
case 1
50 degree-1.4 mm-
case 2
60 degree-1mm-
case 1
60 degree-1.4 mm-
case 2
Reactive
case
Isotherma
l case
Reactive
case
Isotherma
l case
Reactive
case
Isotherma
l case
Reactive
case
Isotherma
l case
Reactive
case
Isotherma
l case
Reactive
case
Isotherma
l case
1
static temperature
(K)
2130 - 2230 - 2220 - 2230 - 1980 - 2220 -
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FutureWork
• COMPUTATIONAL FLUID DYNAMICS ANALYSIS USING ANSYS
(FLUENT)
Gas temperature distribution
Liner wall temperature prediction
Emission prediction
• FINAL DESIGN DETAILS
2D and 3D view of combustion chamber
Two dimensional model of modified diffusion section
Cut Section of Three dimensional model of modified combustion
chamber
• CONCLUSION AND RECOMMENDATION
63. 63
Work Plan
6/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
Work plan Phase I Phase II
Sr. No.
Stage June-14 Jul-14 Aug-14 Sep-14 Oct-14 Nov-14 Dec-14 Jan-15 Feb-15 Mar-15 Apr-15 May-15
1
Selection of
Work Area
2
Literature
Review
3
Problem
Identification
4
Further
Literature
Review
5
Design data and
testing report
collection
6
Modelling of
Annular
combustor
Preparation
7
Performance
Testing on
CFD (ANSYS)
8
Results and
Discussion
9 Report Writing
65. References
[7] Yehia A. Eldrainy et al. “A Multiple Inlet Swirler for Gas Turbine Combustors” World
Academy of Science, Engineering and Technology Vol:3 2009-05-26
[8] S.R. Dhineshkumar, B. Prakash, S. R. Balakrishnan “Large Turbulence Creation Inside A
Gas Turbine Combustion Chamber Using Perforated Plate” International Journal of
Engineering Research & Technology (IJERT) Vol. 2 Issue 5, May - 2013
[9] Fagner Luis Goular Dias et al. “Reference Area Investigation in a Gas Turbine
Combustion Chamber Using CFD” Journal of Mechanical Engineering and Automation
2014, 4(2): 73-82 DOI: 10.5923/j.jmea.20140402.04
[10] P.Anand et al. “Designing, Modeling and Fabrication of Micro Gas turbine Combustion
Chamber” Internationl Journal of Current Research and Academic Review ISSN: 2347-3215
Volume 2 Number 9 (September-2014) pp. 99-107
[11] N L Narasimha Reddy et al. “The CFD Analysis of Turbulence Characteristics in
Combustion Chamber with Non Circular Co-Axial Jets” IOSR Journal of Mechanical and Civil
Engineering (IOSR-JMCE) e-ISSN: 2278-1684,p-ISSN: 2320-334X, Volume 6, Issue 2 (Mar. -
Apr. 2013), PP 01-10
[12] Marian Gieras, Tomasz Sta´nkowski “Computational study of an aerodynamic flow
through a micro-turbine engine combustor ” Open Access Journal Journal of Power
Technologies 92 (2) (2012) 68–79 Warsaw University of Technology, Poland
656/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
66. References
Reference Books
[13] Arthur H. Lefebvre and Dilip R. Ballal, GAS TURBINE COMBUSTION: ALTERNATIVE
FUELS AND EMISSIONS, 3rd Ed.
[14] John D. Anderson Jr. : COMPUTATIONAL FLUID DYNAMICS.
Web
[15] cfd2012.com/gasturbine-combustion-chambers.html
666/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
67. Thank
you…
Man at work …
… Work at Progress
676/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA