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Thermo-Structural Investigation of Gas Turbine Blade Provided with Helicoidal Passages
By having helicoidal shape for the cooling passage, it is possible to provide more surface area for cooling per unit passage length. In addition to this, by providing turbulators within the helicoidal passages, it is possible to augment an increase in heat transfer from the blade surface to the cooling fluid. Since FSI is the objective of this analysis, the blade loading corresponding to the static pressure as well as temperature field on the blades surfaces are obtained using CFD run. The output results are then used as structural boundary condition to solve FSI, using finite element method. The present work brings out thermal and structural distortion of the HP stage gas turbine blade. A parametric approach is used for varying the cooling passage geometry to optimize the cooling process. It can be concluded from FSI analysis that circular helicoidal cooling passage (4 mm Φ) of pitch 6 mm with turbulators of size e/D = 0.08 with rib thickness 0.75mm effect in improved cooling properties and in turn reduce structural deformation.
Gas Turbine Blade Cooling, Helicoidal Passages, Turbulators, Thermo-Structural Investigation.
- Kini CR, Yalamarty SS, Mendonca RM, Yagnesh Sharma N, Satish Shenoy B. CHT Analysis of Trailing Edge Region Cooling In HP Stage Turbine Blade. Indian Journal of Science and Technology. 2016; 9(6):1–6.
- Chyu MK, Naturajan V. Surface heat transfer from a three- pass blade cooling passage simulator. J Heat Transfer. 1995; 117:650–6.
- Dutta S, Andrews MJ, Han JC. Prediction of turbulent flow and heat transfer in rotating square and rectangular smooth channels. International Gas Turbine and Aeroengine Congress and Exhibition, Birmingham, UK, 1996 Jun 10- 13 ASME Paper 96-GT-234.
- Han J, Ekkad S. Recent development in turbine blade film cooling. Int J of Rotating Machinery. 2001; 7:21–40.
- Horlock JH. Basic thermodynamics of turbine cooling. J Turbomachinery. 2001; 123:583–92.
- Sazonov IA, Mokhov MA. Design of Thermoelectric Generators for Oil and Gas Production Systems. Indian Journal of Science and Technology. 2015 Nov; 8(30). Doi: 10.17485/ijst/2015/v8i30/81878.
- Anita S, Chellamuthu C. Thermal Modeling of PMSG Generator for Gas Turbine Applications. Indian Journal of Science and Technology. 2015 Nov; 8(31):1–5.
- Kini CR, Satish Shenoy B, Yagnesh Sharma N. Computational conjugate heat transfer analysis of hp stage turbine blade cooling: effect of turbulator geometry in helicoidal cooling duct. Proceedings of World Academy of Science Engineering and Technology Special Journal Issue. 2012 Oct; 0070:645–52.
- Kini CR, Satish Shenoy B, Yagnesh Sharma N. Numerical analysis of gas turbine hp stage blade cooling with new cooling duct geometries. International Journal of Earth Sciences and Engineering. 2012 Aug; 05(04) (02):1057–62.
- Kini CR, Satish Shenoy B, Yagnesh Sharma N. A computational conjugate thermal analysis of HP stage turbine blade cooling with innovative cooling passage geometries. Journal of Lecture Notes in Engineering and Computer Science. 2011 Jul; 2192(1):2168–73.
- Kini CR, Satish Shenoy B, Yagnesh Sharma N. Thermo- structural analysis of HP stage gas turbine blades with helicoidal cooling ducts. International Journal of Advancements in Mechanical and Aeronautical Engineering. 2014; 1(2):57–60.
- Albeirutty MH, Alghamdi AS, Najjar YS. Heat transfer analysis for a multistage gas turbine using different bladecooling schemes. J Applied Thermal Engineering. 2004; 24:563–77.
- Kim KM, Park JS, Lee DH, Lee TW, Cho HH. Analysis of conjugated heat transfer, stress and failure in a gas turbine blade with circular cooling passages. J Engineering Failure Analysis. 2011; 18:1212–22.
- Available from: http://new.bibus.cz/pdf/Special_Metals/ Nikl/prehled/nimonicalloy_90_105.pdf, 11/08/2015
- ANSYS Fluent 6.3, Fluent Inc., Cavendish Court Lebanon, USA.
- ANSYS Workbench, ANSYS Workbench user’s guide, release 14.0, ANSYS Inc., Canonsburg, USA;2012, 11/08/2015
- CATIA V5R19, Dassault Systems, 1994–2011.
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