cfd analysis of combustor

04/15/2023 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 DinesanAssistant ProfessorMechanical Department

A Dissertation Mid Semester ReviewGujarat Technological University

March-2015

Merchant Institute of Technology, PiludraMERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA

04/15/2023 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


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 ReviewTitle

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 ReviewTitle Large Eddy Simulation of turbulent flames in a Trapped Vortex

Combustor(TVC) – A flamelet presumed-pdf closure preserving laminar flame speed[2]


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.



Investigation of Radial Swirler Effect on Flow Pattern inside a Gas Turbine

Combustor[3]


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.



Combustor aerodynamic using radial Swirler[4]


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.



Investigation of low emission combustors using hydrogen lean direct

injection[5]


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.



Design and experimental investigation of 60 pressure swirl nozzle for penetration ⁰

length and cone angle at different pressure[6]


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 60 and minimum penetration length is ⁰

achieved nearly 62mm at designed injection pressure of 18 bars.



Design and CFD Simulation of Annular Combustion Chamber with Kerosene as

Fuel for 20 kW Gas Turbine Engine[7]


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.



Numerical Investigation of Effect of Swirl Flow in Subsonic Nozzle[8]


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.



A Multiple Inlet Swirler for Gas Turbine Combustors[9]


Yehia A. Eldrainy et al. / World Academy of Science, Engineering and TechnologyVol: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.



Large Turbulence Creation Inside A Gas Turbine Combustion Chamber

Using Perforated Plate[10]


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.



Reference Area Investigation in a Gas Turbine Combustion Chamber Using

CFD[11]


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.



Designing, Modeling and Fabrication of Micro Gas turbine Combustion

Chamber[12]


P.Anand et al. / Internationl Journal of Current Research and Academic ReviewISSN: 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.



The CFD Analysis of Turbulence Characteristics in Combustion Chamber with

Non Circular Co-Axial Jets[13]


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.



Computational study of an aerodynamic flow through a micro-turbine

engine combustor[14]


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.

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 mmNumber of vanes, nυ = 8–16ΔPsw = 3%–4% of P3Ksw = 1.3 for flat vanes, and 1.15 for curved vanes

Existing Dimension’s


case 1degree 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 mm50 diameter 1mm 5 mm 6 mm 6 mm 3 mm 4 mm 4 mm60 diameter 1mm 5 mm 6 mm 6 mm 3 mm 4 mm 4 mm

cooling holesouter 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 2degree 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 mm50 diameter 1.4 mm 5 mm 6 mm 7 mm 4 mm 5 mm 6 mm60 diameter 1.4 mm 5 mm 6 mm 7 mm 4 mm 5 mm 6 mm

cooling holesouter liner (80 no°s) inner liner (48 no°s)

1.5 mm diameter in 3 row°s


Modelling


Modelling (Continues…)


Meshing (Ansys R15.0)Create meshType of mesh: - 3DType 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

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 20

500000

1000000

1500000

2000000

2500000

3000000

NODESELEMENTS


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


Meshing for 50 degree (Ansys R15.0) Continues…


Meshing for 60 degree (Ansys 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.

CFD Analysis for combustor (Ansys Fluent)


The k-ε model introduces two new variables into the system of equations.

CONTINUTITY EQUATION :

CFD Analysis 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



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


Calculationma/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

CFD Analysis for combustor (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


Velocity Magnitude


50°- case 1 50°- case 2


Velocity Magnitude


60°- case 1 60°- case 2


Static Temperature


45°- case 1 45°- case 2


Static Temperature


50°- case 1 50°- case 2


Static Temperature


60°- case 1 60°- case 2


Total pressure

CFD Analysis for combustor (Ansys Fluent) isothermal cases

45°- case 1 45°- case 2

50°- case 1 50°- case 2


Total pressure


60°- case 1 60°- case 2


Velocity magnitude (m/s)


45°- case 1 45°- case 2

50°- case 1 50°- case 2


Velocity magnitude (m/s)


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





Reactive case

Isothermal case

Reactive case

Isothermal case

Reactive case

Isothermal case

Reactive case

Isothermal case

Reactive case

Isothermal case

Reactive case

Isothermal case

1 static pressure (pa) 26000 23200 27900 25400 18100 18200 26600 24300 37300 33500 40200 37600

2dynamic 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 of Velocity for different cases

Sr no

Parameters








Reactive case

Isothermal case

Reactive case

Isothermal case

Reactive case

Isothermal case

Reactive case

Isothermal case

Reactive case

Isothermal case

Reactive case

Isothermal case

1velocity 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








Reactive case

Isothermal case

Reactive case

Isothermal case

Reactive case

Isothermal case

Reactive case

Isothermal case

Reactive case

Isothermal case

Reactive case

Isothermal case

1static temperature

(K)2130 - 2230 - 2220 - 2230 - 1980 - 2220 -


Future Work• 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


Work PlanWork 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

1Selection of Work Area

2Literature Review

3Problem

Identification

4Further

Literature Review

5Design data and

testing report collection

6

Modelling of Annular

combustor Preparation

7Performance Testing on

CFD (ANSYS)

8Results 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

Engineering

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