cfd analysis of combustor

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

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

36/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
Introduction
Brayton Cycle with P-V and T-S diagram

Introduction (Continues…)
The following are the important components of the gas turbine combustor:
 Diffuser
 Swirler
 Fuel Injector
 Spark Plug
 Liner
 Casing
Annular combustor

Literature Review
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.

Literature Review
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.

Literature Review
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.

Literature Review
Title Combustor aerodynamic using radial Swirler[4]
Author /
Publication
M. N. Mohd Jaafar et al, / International Journal of the Physical Sciences Vol.
6(13), pp. 3091-3098, ISSN 1992 - 1950 ©2011 Academic Journals
Conclusion 1. In this paper two types of vanes (flat vane and curved vane) are used for
experimental works and 40⁰,50⁰ and 60⁰ vane angle were tested for both
types of vanes.
2. The 40° vane angle Swirler produced a none or very small volume of
recirculation zone while 50° and 60° vane angle Swirler produced larger
recirculation zone size.
3. Flat vane generates 46 mm length of CRZ while for the curved vane generates
45 mm length. So flat vane is better than curved vane for numerical
simulation and experimental works.

Literature Review
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.

10
Literature Review
Title Design and experimental investigation of 60⁰ pressure swirl nozzle for penetration
length and cone angle at different pressure[6]
Author /
Publication
Salim Channiwala et al. / International Journal of Advances in Engineering &
Technology, Jan. 2013. ©IJAET ISSN: 2231-1963
Conclusion 1. In the experiment penetration length and spray cone angle are carried out with the
injection pressure from 3 bar to 18 bar. at 3 bar penetration length and spray cone
angle are minimum and also that at 3 bar liquid film is not breaking into small
droplets.
2. From 3 bar to 18 bar as injection pressure increases the cone angle also increases
and penetration length decreases but except from 6 bar to 12 bar penetration length
increases due to liquid film starts breaking in small droplets.
3. The maximum angle achieved is nearly 60⁰ and minimum penetration length is
achieved nearly 62mm at designed injection pressure of 18 bars.

Literature Review
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.

Literature Review
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.

Literature Review
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.

Literature Review
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.

Literature Review
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.

Literature Review
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.

Literature Review
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.

Literature Review
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

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.

 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

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]

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

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
cooling holes
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
primary secondary dilution primary secondary dilution
45 diameter 1.4 mm 5 mm 6 mm 7 mm 4 mm 5 mm 6 mm
cooling holes
1.5 mm diameter in 3 row°s

Modelling

Modelling (Continues…)

Meshing (Ansys R15.0)
Create mesh
Type of mesh: - 3D
Type of Element: -Tetrahedral
Fig. types of cell shapes

Meshing (Ansys R15.0)
Continues…
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.

Meshing Result (Ansys R15.0)
Continues…
SR. NO CASE NODES ELEMENTS
1 45°-1 mm-case 1 471580 2445664
2 45°-1.4 mm-case 2 538651 2817738
3 50°-1 mm-case 1 464378 2410559
4 50°-1.4 mm-case 2 532950 2786147
5 60°-1 mm-case 1 463136 2393210
6 60°-1.4 mm-case 2 489517 2599496
0
500000
1000000
1500000
2000000
2500000
3000000
45°-1 mm-case 1 45°-1.4 mm-case 2 50°-1 mm-case 1 50°-1.4 mm-case 2 60°-1 mm-case 1 60°-1.4 mm-case 2
NODES
ELEMENTS

Meshing for 45 degree (Ansys
R15.0)Continues…

R15.0)Continues…

R15.0)

Boundary Selection (Ansys
R15.0)

 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)

The k-ε model introduces two new variables into the system of equations.
CONTINUTITY EQUATION :
(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

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.

 Species model : Non Premixed combustion

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
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

 Run calculation for 1000 iterations for reactive case and isothermal case
 Get the result

 Total Pressure
(Ansys Fluent) reactive cases
45°- case 1 45°- case 2

 Total Pressure
50°- case 250°- case 1

 Total Pressure
60°- case 1 60°- case 2

 Velocity Magnitude
45°- case 1 45°- case 2

50°- case 1 50°- case 2

60°- case 1 60°- case 2

 Static Temperature
45°- case 1 45°- case 2

50°- case 1 50°- case 2

60°- case 1 60°- case 2

 Total pressure
(Ansys Fluent) isothermal
cases
45°- case 1 45°- case 2
50°- case 1 50°- case 2

 Total pressure
cases
60°- case 1 60°- case 2

 Velocity magnitude (m/s)
cases
45°- case 1 45°- case 2
50°- case 1 50°- case 2

 Velocity magnitude (m/s)
cases
60°- case 1 60°- case 2

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

Pressure bar chart

Comparison ofVelocity for
different cases
Sr
no
Parameters
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

Velocity bar chart

Comparison of temperature
for different cases
Sr
no
Parameters
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 -

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
Work Plan
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

References
[1] Yehia A. Eldrainy et al. “Investigation of Radial Swirler Effect on Flow Pattern inside a
Gas Turbine Combustor” Modern Applied Science Vol.3 No. 5 2009
[2] M. N. Mohd Jaafar et al, “Combustor aerodynamic using radial Swirler” International
Journal of the Physical Sciences Vol. 6(13), pp. 3091-3098, ISSN 1992 - 1950 ©2011
Academic Journals
[3] Daniel Crunteanu, Robert Isac “Investigation of low emission combustors using
hydrogen lean direct injection” INCAS BULLETIN, Volume 3, Issue 3/ 2011, pp. 45 – 52 ISSN
2066 – 8201 DOI: 10.13111/2066-8201.2011.3.3.5
[4] Salim Channiwala et al. “Design and experimental investigation of 60⁰ pressure swirl
nozzle for penetration length and cone angle at different pressure” International Journal
of Advances in Engineering & Technology, Jan. 2013. ©IJAET ISSN: 2231-1963
[5] K. V. Chaudhari et al. “Design and CFD Simulation of Annular Combustion Chamber
with Kerosene as Fuel for 20 kW Gas Turbine Engine” International Journal of Engineering
Research and Applications (IJERA) ISSN: 2248-9622, Vol. 2, Issue 6, November- December
2012, pp.1641-1645
[6] M. K. Jayakumar, Eusebious T. Chullai “Numerical Investigation of Effect of Swirl Flow in
Subsonic Nozzle” The International Journal Of Science & Technology (ISSN 2321 – 919X)
Vol. 2, issue. 4 2014

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

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

Thank
you…
Man at work …
… Work at Progress

cfd analysis of combustor

Empfohlen

Empfohlen

Weitere ähnliche Inhalte

Was ist angesagt?

Was ist angesagt? (20)

Andere mochten auch

Andere mochten auch (20)

Ähnlich wie cfd analysis of combustor

Ähnlich wie cfd analysis of combustor (20)

Kürzlich hochgeladen

Kürzlich hochgeladen (20)

cfd analysis of combustor