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INTERNATIONALMechanical Engineering and Technology (IJMET), ISSN 0976 –
 International Journal of JOURNAL OF MECHANICAL ENGINEERING
 6340(Print), ISSN 0976 – 6359(Online) Volume 4, Issue 2, March - April (2013) © IAEME
                         AND TECHNOLOGY (IJMET)
ISSN 0976 – 6340 (Print)
ISSN 0976 – 6359 (Online)
Volume 4, Issue 2, March - April (2013), pp. 39-46
                                                                            IJMET
© IAEME: www.iaeme.com/ijmet.asp
Journal Impact Factor (2013): 5.7731 (Calculated by GISI)
www.jifactor.com
                                                                        ©IAEME



  CFD ANALYSIS OF FLOW CHARACTERISTICS IN A GAS TURBINE-
      A VIABLE APPROACH TO PREDICT THE TURBULANCE

                                            a                      b
                             P.S. Jeyalaxmi , Dr.G.Kalivarathan
                    a
                     Research Scholar, CMJ University, Meghalaya, Shillong.
  b
      Principal/ PSN Institute of Technology and Science, Tirunelveli, Tamilnadu, Supervisor,
                                     CMJ University, Shillong.



  ABSTRACT

          The demands for best performance in gas turbine engines can be obtained by
  increasing combustion temperatures to increase thermal efficiency. Hot combustion
  temperatures create a harsh environment which leads to the consideration of the durability
  of the combustor and turbine sections. Improvements in durability can be achieved
  through understanding the interactions between the combustor and turbine. The flow field
  at a combustor exit shows non uniformities in pressure, temperature, and velocity in the
  pitch and radial directions. This inlet profile to the turbine can have a considerable effect
  on the development of the secondary flows through the vane passage. Presents a
  computational study of the flow field generated in a non-reacting gas turbine combustor
  and how that flow field convects through the downstream stator vane. Specifically, the
  effect that the combustor flow field had on the secondary flow pattern in the turbine was
  studied.

  1.0 INTRODUCTION

         The designs of aircraft gas turbine engines have improved and evolved
  tremendously. The first gas turbine powered aircraft reached top speeds of 435
  Kilometers per hour; only sixty years later aircraft powered by gas turbine engines are
  flying at speeds exceeding 2000 Kilometers per hour. The major contributions to the
  advances in gas turbine engine performance have been increased in terms of power
                                                39
International Journal of Mechanical Engineering and Technology (IJMET), ISSN 0976 –
6340(Print), ISSN 0976 – 6359(Online) Volume 4, Issue 2, March - April (2013) © IAEME

output, reliability and fuel efficiency. The existing demands for improving higher
performance while maintaining affordability and engine durability can only be reached
through the achievement of hot combustion temperatures and better cooling schemes. The
need for increasingly higher temperatures creates a critical ambiance environment for the
first stage turbine vane and combustor liner. The difficult ambiance in the engine pushes
the design holds for durability in both the combustor and turbine sections. Sincerely is
required for the flow field leaving the combustor and its impact on the heat transfer to the
turbine vane is also be investigated to the maximum possible extend.

2.0 COMBUSTOR MODEL TEST SECTION DESIGN

        The first stage of both the experimental and computational portions of the present
study involved the design of a non-reacting combustor test facility necessary to simulate
the geometry and flow conditions of a realistic gas turbine engine combustor. The specific
work done by the author of this thesis included the initial design of the combustor test
section geometry and the computational simulation of the wind tunnel model. The actual
wind tunnel design, including matching engine parameters and the liner panel design, was
primarily completed. Prior to describing the computational modeling, however, it is
important to describe the wind tunnel design and model. The computational combustor
model was based directly on the geometry and flow conditions of the experimental wind
tunnel test section, which was designed to match representative engine combustor
conditions. The combustor, which was simulated, is typical of an annular combustor in a
commercial gas turbine engine. The geometry is characterized by an impingement film
flow cooling scheme which consists of four panels of film-cooling holes and two rows of
dilution jets on both the inner and outer diameters with additional coolant provided by a
slot located at the combustor exit. The combustor has a constant area cross section for the
first half of its length followed by a contraction leading to the downstream turbine. The
first step in the design of the combustor test section was to thoroughly analyze the
combustor engine data provided by industry, and to then determine which engine
parameters needed to be matched in the simulation in order to accurately represent the
combustor flow field. The engine data was then scaled up within the size constraints of an
existing facility described in previous studies.

3.0 LINER PANEL DESIGN

        The design of the individual liner panels within the combustor test section was a
complicated task in itself involving several important compromises between the engine
and the model. It was desired to create panels that matched as closely as possible both the
geometric details of the combustor as well as the flow parameters of the film cooling,
dilution, and slot flows.




                                            40
International Journal of Mechanical Engineering and Technology (IJMET), ISSN 0976 –
6340(Print), ISSN 0976 – 6359(Online) Volume 4, Issue 2, March - April (2013) © IAEME




          Figure 1. Schematic of the wind tunnel facility with combustor simulator
                        test section in the open loop configuration




         Figure 2 Schematic of engine combustor geometry with dimensions in cm

The two most important goals in the process were to determine the necessary numbers of
film-cooling holes and the sizes of dilution to properly match the desired mass flow rate
distribution and momentum flux ratios, and then lay out the holes in the liner matching the
engine geometry as closely as possible. A third consideration was the ability to adapt the test
section to several geometries; with and without dilution flow, with and without slot flow, and
the possibility of a different liner geometry altogether.


                                              41
International Journal of Mechanical Engineering and Technology (IJMET), ISSN 0976 –
6340(Print), ISSN 0976 – 6359(Online) Volume 4, Issue 2, March - April (2013) © IAEME

                    Table1. Stator Vane Geometry in the Engine and Model

                                         Engine Wind                         Tunnel

         True Chord                         6.45 cm                         59.15 cm

         Pitch/Chord                          0.79                            0.79

        Span /Chord                           0.95                            0.95

       Flow inlet angle                        0°                               0°

       Flow exit angle                        77°                              77°



  Table 2 Mass Flow Distributions in Combustor Based on Percentage of Exit Mass Flow

                                           Engine                        Wind Tunnel
            Inlet                           37.6%                             42.6
      Panel 1 (ID/OD)                   1.43%/2.55%                      1.43%/1.45%
      Panel 2 (ID/OD)                    3.6%/4.65%                       3.4%/3.4%
      Panel 3 (ID/OD)                    3.3%/4.55%                       3.3%/3.3%
      Panel 4 (ID/OD)                    1.4%/2.65%                       1.4%/1.4%
       Dilution row 1                       16.5%                            16.5%
       Dilution row 2                       16.5%                            16.5%
            Slot                            1.38%                            1.38%

4.0 GAMBIT MESHING

        All of the models were meshed using GAMBIT, a program offered with the Fluent
software package. The mesh was a critical element of the problem setup since the accuracy of
the solution will certainly be limited by the quality of the mesh which is used to calculate it.
The process of mesh generation was quite involved and required several steps, which will be
outlined in detail in this section. First, the combustor and vane geometry was created using
Gambit’s solid modeling capabilities. Then, line and surface mesh spacing layouts were
attached to the geometry. Finally, the internal solid mesh was created from the line and
surface meshes and was refined to reduce cell skewness. The geometry and mesh was then
exported and read into Fluent. The basic geometry may be defined in Gambit in several ways.
For the combustor section, volumes were created corresponding to the cooling holes, dilution
holes, and main combustor geometry. Using Boolean operations, these were combined to
create the complete combustor geometry. In order to create the vane geometry, points were
defined along the contour of the vane and fitted with splines to create the vane surface.


                                              42
International Journal of Mechanical Engineering and Technology (IJMET), ISSN 0976 –
6340(Print), ISSN 0976 – 6359(Online) Volume 4, Issue 2, March - April (2013) © IAEME




           Figure 3. Schematics of computational domain for combustor model
             5.0 case 2 with no vane, no slot and (b) case 5 with vane and slot.




         Figure 4. Domain, mesh and boundary conditions for single hole Case I.




                                            43
International Journal of Mechanical Engineering and Technology (IJMET), ISSN 0976 –
6340(Print), ISSN 0976 – 6359(Online) Volume 4, Issue 2, March - April (2013) © IAEME




Figure 5. Velocity profile (U/Uave) at hole inlets for each of the four liner panel axial single
                                        hole cases.




Figure 6. Velocity profiles (U/U∞, ave) cooling hole diameter downstream of the hole trailing
                      edge for each of the four axial hole panel cases.


                                              44
International Journal of Mechanical Engineering and Technology (IJMET), ISSN 0976 –
6340(Print), ISSN 0976 – 6359(Online) Volume 4, Issue 2, March - April (2013) © IAEME




 Figure 7. Adiabatic effectiveness comparison for (a) axial and (b) compound angle cooling
                               holes at I = 13.1 and M = 3.6.

5.0 CONCLUSION

        In this investigation it is observed that the RNG k-ε turbulence model used in the
cases is viable and it is seen that the RSM model remarkably exhibits the turbulence level and
the dilution jet mixing at the combustor outlet. But still, It is easier to predict the variations
through CFD in the mean flow field results, In addition to this the turbulence levels of the
approaching flow may affect the secondary flow field in the vane passage. Because of these
reasons more efforts has to be made towards testing additional turbulence models to access
one more suitable means for predicting this type of swirling, highly turbulent and flow
situation in a generic manner through viable CFD tool.


                                               45
International Journal of Mechanical Engineering and Technology (IJMET), ISSN 0976 –
6340(Print), ISSN 0976 – 6359(Online) Volume 4, Issue 2, March - April (2013) © IAEME

REFERENCES

1. Goebel, S. G., Abauf, N., Lovett, J. A., and Lee, C.-P. (1993) “Measurements of Combustor
    Velocity and Turbulence Profiles,” ASME Paper No. 93-GT-228.
2. Crocker, S. C., Nickolaus, D., and Smith, C. E., (1998) “CFD Modeling of a Gas Turbine
    Combustor from Compressor Exit to Turbine Inlet,” ASME Paper No. 98-GT-184.Fluent
    Inc., Fluent User.s Guide, Version 5.0., 1998 (Fluent Inc.: New Hampshire). Fluent Inc.,
    Gambit I Modeling Guide, 1998 (Fluent Inc.: New Hampshire).
3. Butler, T. L., Sharma, O. P., Joslyn, H. D., and Dring, R. P. (1989) “Redistribution of and
    Inlet Temperature Distortion in an Axial Flow Turbine Stage,” AIAA J of Propulsion and
    Power, Vol. 5, No. 1, pp. 64-71.
4. Burd, S. W., Satterness, C. J. and Simon, T. W. (2000) “Effects of Slot Bleed Injection Over
    a Contoured Endwall on Nozzle Guide Vane Cooling Performance: Part II – Thermal
    Measurements,” ASME Paper No. 2000-GT-200.
5. Burd, S. W. and Simon, T. W. (2000) “Effects of Slot Bleed Injection Over a Contoured
    Endwall on Nozzle Guide Vane Cooling Performance: Part I – Flow Field Measurements,”
    ASME Paper No. 2000-GT-199.
6. Boyle, R. J. and Giel, P. W. (1997) “Prediction of Nonuniform Inlet Temperature Effects on
    Vane and Rotor Heat Transfer,” ASME Paper No. 97-GT-133.
7. Bicen, A. F., Tse, D. and Whitelaw, J. H. (1988) “Flow and Combustion Characteristics of an
    Annular Combustor,” Combustion and Flame 72: 175-192.
8. LA.Barringer, M.D (2001), “Flow Field Simulations of a Gas Turbine Combustor,” thesis,
    Mechanical Engineering Department, Virginia Polytechnic Institute and State University, to
    be completed May 2001.
9. Barringer, M.D., Richard, O.T., Stitzel, S.M., Walter, J.P. and Thole, K.A. (2001) “Flow
    FieldSimulations of a Gas Turbine Combustor,” to be presented at IGTI 2001, New Orleans,
10. Anand, M. S., Zhu, J., Connor, C., and Razdan, M. K. (1999) “Combustor Flow Analysis
    Using and Advanced Finite-Volume Design System,” ASME Paper No. 99-GT-273.
11. K. V. Chaudhari , D. B. Kulshreshtha and S. A. Channiwala, “Design and Experimental
    Investigations of Pressure Swirl Atomizer of Annular Type Combustion Chamber for 20 KW
    Gas Turbine Engine” International Journal of Advanced Research in Engineering &
    Technology (IJARET), Volume 3, Issue 2, 2012, pp. 311 - 321, ISSN Print: 0976-6480, ISSN
    Online: 0976-6499.
12. Tarun Singh Tanwar, Dharmendra Hariyani and Manish Dadhich, “Flow Simulation (CFD) &
    Static Structural Analysis (FEA) of a Radial Turbine” International Journal of Mechanical
    Engineering & Technology (IJMET), Volume 3, Issue 3, 2012, pp. 252 - 269, ISSN Print:
    0976 – 6340, ISSN Online: 0976 – 6359.
13. Ashok Tukaram Pise and Umesh Vandeorao Awasarmol, “Investigation of Enhancement of
    Natural Convection Heat Transfer from Engine Cylinder with Permeable Fins” International
    Journal of Mechanical Engineering & Technology (IJMET), Volume 1, Issue 1, 2010, pp. 238
    - 247, ISSN Print: 0976 – 6340, ISSN Online: 0976 – 6359.
14. Cherian Paul and Parvathy Venugopal, “Modelling of Interfacial Heat Transfer Coefficient
    and Experimental Verification for Gravity Die Casting of Aluminium Alloys” International
    Journal of Mechanical Engineering & Technology (IJMET), Volume 1, Issue 1, 2010, pp. 253
    - 274, ISSN Print: 0976 – 6340, ISSN Online: 0976 – 6359.
15. A.Saravanapandi Solairajan and Dr.G.Kalivarathan, “Investigation of Heat Transfer Through
    CNT Composites-Focusing on Conduction Mode” International Journal of Mechanical
    Engineering & Technology (IJMET), Volume 4, Issue 1, 2013, pp. 66 - 73, ISSN Print: 0976
    – 6340, ISSN Online: 0976 – 6359.

                                              46

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Cfd analysis of flow charateristics in a gas turbine a viable approach

  • 1. INTERNATIONALMechanical Engineering and Technology (IJMET), ISSN 0976 – International Journal of JOURNAL OF MECHANICAL ENGINEERING 6340(Print), ISSN 0976 – 6359(Online) Volume 4, Issue 2, March - April (2013) © IAEME AND TECHNOLOGY (IJMET) ISSN 0976 – 6340 (Print) ISSN 0976 – 6359 (Online) Volume 4, Issue 2, March - April (2013), pp. 39-46 IJMET © IAEME: www.iaeme.com/ijmet.asp Journal Impact Factor (2013): 5.7731 (Calculated by GISI) www.jifactor.com ©IAEME CFD ANALYSIS OF FLOW CHARACTERISTICS IN A GAS TURBINE- A VIABLE APPROACH TO PREDICT THE TURBULANCE a b P.S. Jeyalaxmi , Dr.G.Kalivarathan a Research Scholar, CMJ University, Meghalaya, Shillong. b Principal/ PSN Institute of Technology and Science, Tirunelveli, Tamilnadu, Supervisor, CMJ University, Shillong. ABSTRACT The demands for best performance in gas turbine engines can be obtained by increasing combustion temperatures to increase thermal efficiency. Hot combustion temperatures create a harsh environment which leads to the consideration of the durability of the combustor and turbine sections. Improvements in durability can be achieved through understanding the interactions between the combustor and turbine. The flow field at a combustor exit shows non uniformities in pressure, temperature, and velocity in the pitch and radial directions. This inlet profile to the turbine can have a considerable effect on the development of the secondary flows through the vane passage. Presents a computational study of the flow field generated in a non-reacting gas turbine combustor and how that flow field convects through the downstream stator vane. Specifically, the effect that the combustor flow field had on the secondary flow pattern in the turbine was studied. 1.0 INTRODUCTION The designs of aircraft gas turbine engines have improved and evolved tremendously. The first gas turbine powered aircraft reached top speeds of 435 Kilometers per hour; only sixty years later aircraft powered by gas turbine engines are flying at speeds exceeding 2000 Kilometers per hour. The major contributions to the advances in gas turbine engine performance have been increased in terms of power 39
  • 2. International Journal of Mechanical Engineering and Technology (IJMET), ISSN 0976 – 6340(Print), ISSN 0976 – 6359(Online) Volume 4, Issue 2, March - April (2013) © IAEME output, reliability and fuel efficiency. The existing demands for improving higher performance while maintaining affordability and engine durability can only be reached through the achievement of hot combustion temperatures and better cooling schemes. The need for increasingly higher temperatures creates a critical ambiance environment for the first stage turbine vane and combustor liner. The difficult ambiance in the engine pushes the design holds for durability in both the combustor and turbine sections. Sincerely is required for the flow field leaving the combustor and its impact on the heat transfer to the turbine vane is also be investigated to the maximum possible extend. 2.0 COMBUSTOR MODEL TEST SECTION DESIGN The first stage of both the experimental and computational portions of the present study involved the design of a non-reacting combustor test facility necessary to simulate the geometry and flow conditions of a realistic gas turbine engine combustor. The specific work done by the author of this thesis included the initial design of the combustor test section geometry and the computational simulation of the wind tunnel model. The actual wind tunnel design, including matching engine parameters and the liner panel design, was primarily completed. Prior to describing the computational modeling, however, it is important to describe the wind tunnel design and model. The computational combustor model was based directly on the geometry and flow conditions of the experimental wind tunnel test section, which was designed to match representative engine combustor conditions. The combustor, which was simulated, is typical of an annular combustor in a commercial gas turbine engine. The geometry is characterized by an impingement film flow cooling scheme which consists of four panels of film-cooling holes and two rows of dilution jets on both the inner and outer diameters with additional coolant provided by a slot located at the combustor exit. The combustor has a constant area cross section for the first half of its length followed by a contraction leading to the downstream turbine. The first step in the design of the combustor test section was to thoroughly analyze the combustor engine data provided by industry, and to then determine which engine parameters needed to be matched in the simulation in order to accurately represent the combustor flow field. The engine data was then scaled up within the size constraints of an existing facility described in previous studies. 3.0 LINER PANEL DESIGN The design of the individual liner panels within the combustor test section was a complicated task in itself involving several important compromises between the engine and the model. It was desired to create panels that matched as closely as possible both the geometric details of the combustor as well as the flow parameters of the film cooling, dilution, and slot flows. 40
  • 3. International Journal of Mechanical Engineering and Technology (IJMET), ISSN 0976 – 6340(Print), ISSN 0976 – 6359(Online) Volume 4, Issue 2, March - April (2013) © IAEME Figure 1. Schematic of the wind tunnel facility with combustor simulator test section in the open loop configuration Figure 2 Schematic of engine combustor geometry with dimensions in cm The two most important goals in the process were to determine the necessary numbers of film-cooling holes and the sizes of dilution to properly match the desired mass flow rate distribution and momentum flux ratios, and then lay out the holes in the liner matching the engine geometry as closely as possible. A third consideration was the ability to adapt the test section to several geometries; with and without dilution flow, with and without slot flow, and the possibility of a different liner geometry altogether. 41
  • 4. International Journal of Mechanical Engineering and Technology (IJMET), ISSN 0976 – 6340(Print), ISSN 0976 – 6359(Online) Volume 4, Issue 2, March - April (2013) © IAEME Table1. Stator Vane Geometry in the Engine and Model Engine Wind Tunnel True Chord 6.45 cm 59.15 cm Pitch/Chord 0.79 0.79 Span /Chord 0.95 0.95 Flow inlet angle 0° 0° Flow exit angle 77° 77° Table 2 Mass Flow Distributions in Combustor Based on Percentage of Exit Mass Flow Engine Wind Tunnel Inlet 37.6% 42.6 Panel 1 (ID/OD) 1.43%/2.55% 1.43%/1.45% Panel 2 (ID/OD) 3.6%/4.65% 3.4%/3.4% Panel 3 (ID/OD) 3.3%/4.55% 3.3%/3.3% Panel 4 (ID/OD) 1.4%/2.65% 1.4%/1.4% Dilution row 1 16.5% 16.5% Dilution row 2 16.5% 16.5% Slot 1.38% 1.38% 4.0 GAMBIT MESHING All of the models were meshed using GAMBIT, a program offered with the Fluent software package. The mesh was a critical element of the problem setup since the accuracy of the solution will certainly be limited by the quality of the mesh which is used to calculate it. The process of mesh generation was quite involved and required several steps, which will be outlined in detail in this section. First, the combustor and vane geometry was created using Gambit’s solid modeling capabilities. Then, line and surface mesh spacing layouts were attached to the geometry. Finally, the internal solid mesh was created from the line and surface meshes and was refined to reduce cell skewness. The geometry and mesh was then exported and read into Fluent. The basic geometry may be defined in Gambit in several ways. For the combustor section, volumes were created corresponding to the cooling holes, dilution holes, and main combustor geometry. Using Boolean operations, these were combined to create the complete combustor geometry. In order to create the vane geometry, points were defined along the contour of the vane and fitted with splines to create the vane surface. 42
  • 5. International Journal of Mechanical Engineering and Technology (IJMET), ISSN 0976 – 6340(Print), ISSN 0976 – 6359(Online) Volume 4, Issue 2, March - April (2013) © IAEME Figure 3. Schematics of computational domain for combustor model 5.0 case 2 with no vane, no slot and (b) case 5 with vane and slot. Figure 4. Domain, mesh and boundary conditions for single hole Case I. 43
  • 6. International Journal of Mechanical Engineering and Technology (IJMET), ISSN 0976 – 6340(Print), ISSN 0976 – 6359(Online) Volume 4, Issue 2, March - April (2013) © IAEME Figure 5. Velocity profile (U/Uave) at hole inlets for each of the four liner panel axial single hole cases. Figure 6. Velocity profiles (U/U∞, ave) cooling hole diameter downstream of the hole trailing edge for each of the four axial hole panel cases. 44
  • 7. International Journal of Mechanical Engineering and Technology (IJMET), ISSN 0976 – 6340(Print), ISSN 0976 – 6359(Online) Volume 4, Issue 2, March - April (2013) © IAEME Figure 7. Adiabatic effectiveness comparison for (a) axial and (b) compound angle cooling holes at I = 13.1 and M = 3.6. 5.0 CONCLUSION In this investigation it is observed that the RNG k-ε turbulence model used in the cases is viable and it is seen that the RSM model remarkably exhibits the turbulence level and the dilution jet mixing at the combustor outlet. But still, It is easier to predict the variations through CFD in the mean flow field results, In addition to this the turbulence levels of the approaching flow may affect the secondary flow field in the vane passage. Because of these reasons more efforts has to be made towards testing additional turbulence models to access one more suitable means for predicting this type of swirling, highly turbulent and flow situation in a generic manner through viable CFD tool. 45
  • 8. International Journal of Mechanical Engineering and Technology (IJMET), ISSN 0976 – 6340(Print), ISSN 0976 – 6359(Online) Volume 4, Issue 2, March - April (2013) © IAEME REFERENCES 1. Goebel, S. G., Abauf, N., Lovett, J. A., and Lee, C.-P. (1993) “Measurements of Combustor Velocity and Turbulence Profiles,” ASME Paper No. 93-GT-228. 2. Crocker, S. C., Nickolaus, D., and Smith, C. E., (1998) “CFD Modeling of a Gas Turbine Combustor from Compressor Exit to Turbine Inlet,” ASME Paper No. 98-GT-184.Fluent Inc., Fluent User.s Guide, Version 5.0., 1998 (Fluent Inc.: New Hampshire). Fluent Inc., Gambit I Modeling Guide, 1998 (Fluent Inc.: New Hampshire). 3. Butler, T. L., Sharma, O. P., Joslyn, H. D., and Dring, R. P. (1989) “Redistribution of and Inlet Temperature Distortion in an Axial Flow Turbine Stage,” AIAA J of Propulsion and Power, Vol. 5, No. 1, pp. 64-71. 4. Burd, S. W., Satterness, C. J. and Simon, T. W. (2000) “Effects of Slot Bleed Injection Over a Contoured Endwall on Nozzle Guide Vane Cooling Performance: Part II – Thermal Measurements,” ASME Paper No. 2000-GT-200. 5. Burd, S. W. and Simon, T. W. (2000) “Effects of Slot Bleed Injection Over a Contoured Endwall on Nozzle Guide Vane Cooling Performance: Part I – Flow Field Measurements,” ASME Paper No. 2000-GT-199. 6. Boyle, R. J. and Giel, P. W. (1997) “Prediction of Nonuniform Inlet Temperature Effects on Vane and Rotor Heat Transfer,” ASME Paper No. 97-GT-133. 7. Bicen, A. F., Tse, D. and Whitelaw, J. H. (1988) “Flow and Combustion Characteristics of an Annular Combustor,” Combustion and Flame 72: 175-192. 8. LA.Barringer, M.D (2001), “Flow Field Simulations of a Gas Turbine Combustor,” thesis, Mechanical Engineering Department, Virginia Polytechnic Institute and State University, to be completed May 2001. 9. Barringer, M.D., Richard, O.T., Stitzel, S.M., Walter, J.P. and Thole, K.A. (2001) “Flow FieldSimulations of a Gas Turbine Combustor,” to be presented at IGTI 2001, New Orleans, 10. Anand, M. S., Zhu, J., Connor, C., and Razdan, M. K. (1999) “Combustor Flow Analysis Using and Advanced Finite-Volume Design System,” ASME Paper No. 99-GT-273. 11. K. V. Chaudhari , D. B. Kulshreshtha and S. A. Channiwala, “Design and Experimental Investigations of Pressure Swirl Atomizer of Annular Type Combustion Chamber for 20 KW Gas Turbine Engine” International Journal of Advanced Research in Engineering & Technology (IJARET), Volume 3, Issue 2, 2012, pp. 311 - 321, ISSN Print: 0976-6480, ISSN Online: 0976-6499. 12. Tarun Singh Tanwar, Dharmendra Hariyani and Manish Dadhich, “Flow Simulation (CFD) & Static Structural Analysis (FEA) of a Radial Turbine” International Journal of Mechanical Engineering & Technology (IJMET), Volume 3, Issue 3, 2012, pp. 252 - 269, ISSN Print: 0976 – 6340, ISSN Online: 0976 – 6359. 13. Ashok Tukaram Pise and Umesh Vandeorao Awasarmol, “Investigation of Enhancement of Natural Convection Heat Transfer from Engine Cylinder with Permeable Fins” International Journal of Mechanical Engineering & Technology (IJMET), Volume 1, Issue 1, 2010, pp. 238 - 247, ISSN Print: 0976 – 6340, ISSN Online: 0976 – 6359. 14. Cherian Paul and Parvathy Venugopal, “Modelling of Interfacial Heat Transfer Coefficient and Experimental Verification for Gravity Die Casting of Aluminium Alloys” International Journal of Mechanical Engineering & Technology (IJMET), Volume 1, Issue 1, 2010, pp. 253 - 274, ISSN Print: 0976 – 6340, ISSN Online: 0976 – 6359. 15. A.Saravanapandi Solairajan and Dr.G.Kalivarathan, “Investigation of Heat Transfer Through CNT Composites-Focusing on Conduction Mode” International Journal of Mechanical Engineering & Technology (IJMET), Volume 4, Issue 1, 2013, pp. 66 - 73, ISSN Print: 0976 – 6340, ISSN Online: 0976 – 6359. 46