cfd analysis of combustor

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fluid flow and combustion analysis using cfd tool

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cfd analysis of combustor

  1. 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. 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
  3. 3. 36/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA Introduction Brayton Cycle with P-V and T-S diagram
  4. 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. 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. 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. 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.
  8. 8. Literature Review 86/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA 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.
  9. 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.
  10. 10. 10 Literature Review 6/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA 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.
  11. 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. 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. 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. 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. 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. 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. 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. 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. 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. 196/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
  20. 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 6/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
  21. 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]
  22. 22. 226/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA 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
  23. 23. 236/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA 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
  24. 24. Modelling 246/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
  25. 25. Modelling (Continues…) 256/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
  26. 26. Modelling (Continues…) 266/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
  27. 27. Modelling (Continues…) 276/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
  28. 28. Modelling (Continues…) 286/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
  29. 29. Meshing (Ansys R15.0) 296/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA Create mesh Type of mesh: - 3D Type of Element: -Tetrahedral Fig. types of cell shapes
  30. 30. Meshing (Ansys R15.0) Continues… 306/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA 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.
  31. 31. Meshing Result (Ansys R15.0) Continues… 316/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA 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
  32. 32. Meshing for 45 degree (Ansys R15.0)Continues… 326/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
  33. 33. Meshing for 50 degree (Ansys R15.0)Continues… 336/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
  34. 34. Meshing for 60 degree (Ansys R15.0) 346/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
  35. 35. Boundary Selection (Ansys R15.0) 356/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
  36. 36. 366/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA  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)
  37. 37. 376/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA 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
  38. 38. 386/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA 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. 39.  Species model : Non Premixed combustion 6/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA 39 CFDAnalysis for combustor (Ansys Fluent) continues…
  40. 40.  Species model : Non Premixed combustion 6/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA 40 CFDAnalysis for combustor (Ansys Fluent) continues…
  41. 41.  Species model : Non Premixed combustion 6/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA 41 CFDAnalysis for combustor (Ansys Fluent) continues…
  42. 42. 426/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA 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
  43. 43. 436/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA  Run calculation for 1000 iterations for reactive case and isothermal case  Get the result CFDAnalysis for combustor (Ansys Fluent) continues…
  44. 44. 446/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA  Total Pressure CFDAnalysis for combustor (Ansys Fluent) reactive cases 45°- case 1 45°- case 2
  45. 45. 456/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA  Total Pressure CFDAnalysis for combustor (Ansys Fluent) reactive cases 50°- case 250°- case 1
  46. 46. 466/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA  Total Pressure CFDAnalysis for combustor (Ansys Fluent) reactive cases 60°- case 1 60°- case 2
  47. 47. 476/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA  Velocity Magnitude CFDAnalysis for combustor (Ansys Fluent) reactive cases 45°- case 1 45°- case 2
  48. 48. 486/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA  Velocity Magnitude CFDAnalysis for combustor (Ansys Fluent) reactive cases 50°- case 1 50°- case 2
  49. 49. 496/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA  Velocity Magnitude CFDAnalysis for combustor (Ansys Fluent) reactive cases 60°- case 1 60°- case 2
  50. 50. 506/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA  Static Temperature CFDAnalysis for combustor (Ansys Fluent) reactive cases 45°- case 1 45°- case 2
  51. 51. 516/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA  Static Temperature CFDAnalysis for combustor (Ansys Fluent) reactive cases 50°- case 1 50°- case 2
  52. 52. 526/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA  Static Temperature CFDAnalysis for combustor (Ansys Fluent) reactive cases 60°- case 1 60°- case 2
  53. 53. 536/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA  Total pressure CFDAnalysis for combustor (Ansys Fluent) isothermal cases 45°- case 1 45°- case 2 50°- case 1 50°- case 2
  54. 54. 546/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA  Total pressure CFDAnalysis for combustor (Ansys Fluent) isothermal cases 60°- case 1 60°- case 2
  55. 55. 556/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA  Velocity magnitude (m/s) CFDAnalysis for combustor (Ansys Fluent) isothermal cases 45°- case 1 45°- case 2 50°- case 1 50°- case 2
  56. 56. 566/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA  Velocity magnitude (m/s) CFDAnalysis for combustor (Ansys Fluent) isothermal cases 60°- case 1 60°- case 2
  57. 57. 576/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA 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
  58. 58. 586/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA Pressure bar chart
  59. 59. 596/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA 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
  60. 60. 606/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA Velocity bar chart
  61. 61. 616/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA 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 -
  62. 62. 626/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA 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. 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
  64. 64. 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 646/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA
  65. 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. 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. 67. Thank you… Man at work … … Work at Progress 676/7/2015 MERCHANT INSTITUTE OF TECHNOLOGY, PILUDRA

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