Total views : 328

Effect of Twisted Tape Inserts and Stacks on Internal Cooling of Gas Turbine Blades

Affiliations

  • Department of Mechanical and Manufacturing Engineering, Manipal Institute of Technology, Manipal University, Manipal – 576104, Karnataka, India
  • Department of Aeronautical and Automobile Engineering, Manipal Institute of Technology, Manipal University, Manipal – 576104, Karnataka, India

Abstract


Objectives: In gas turbine blades, heat transfer can be enhanced by using twisted tape inserts and stacks. In the present paper, we proposed cooling effect of a gas turbine blade can be improved by using suitable twisted tape inserts and stack configurations. A Comparative study between this type and the twisted tape without stack configurations was performed. Methods/Statistical Analysis: Simulations are carried out for different width ratios of twisted tape with and without using stack configurations. Computation results showed that by using twisted tape inserts of width ratio (W) = 0.3 with stack configurations, provides better cooling effect compared to the others. Findings: Without using the stack Configurations, blade temperature is decreased by 34% at the leading edge and 21.2% at the trailing edge for W = 0.3. By using stack configurations, the blade temperature is decreased by 50.7% at the leading edge and 48% at the trailing edge for W = 0.3. Application/Improvements: All these demonstrated that cooling effect of gas turbine blade especially at the trailing edge can be enhanced with suitable twisted tape and insert and stack configurations.

Keywords

Leading Edge, Numerical Analysis, Stacks, Trailing Edge, Turbine Blade Cooling, Twisted Tape Inserts.

Full Text:

 |  (PDF views: 207)

References


  • Telisinghe JC, Ireland PT, Jones TV, Barrett D, Son C. Comparative study between a cut-back and conventional trailing edge film cooling system. ASME. 2006; 3:983–94.
  • Holloway DS, Leylek JH, Buck FA. Pressure side bleed film cooling: Part 1 - Steady framework for experimental and computational results. ASME; 2002. p. 835–43.
  • Holloway DS, Leylek JH, Buck FA. Pressure side bleed film cooling: Part 2 - Unsteady framework for experimental and computational results. ASME; 2002. p. 835–43.
  • Cunha FJ, Dahmer FT, Chyu MK. Analysis of airfoil trailing edge heat transfer and its significance in thermal-mechanical design and durability. ASME. J. Turbomach. 2006; 128(4):738–46.
  • Kini CR, Satish Shenoy B, Sharma NY. 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, Sharma NY. 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; UK. 2011. p. 645–52.
  • Kini CR, Satish Shenoy B, Sharma NY. Numerical analysis of gas turbine HP stage blade cooling with new cooling duct geometries. International Journal of Earth Sciences and Engineering. 2012; 5(2):1057–62.
  • Kini CR, Yalamarty SS, Mendonca RM, Sharma NY, Shenoy BS. CHT analysis of trailing edge region cooling in hp stage turbine blade. Indian Journal of Science and Technology. 2016; 9(6):1–6.
  • Kini CR, Shenoy BS, Sharma NY. Thermo-structural analysis of HP stage gas turbine blades having helicoidal cooling ducts. International Journal of Advancements in Mechanical and Aeronautical Engineering. 2014; 1(2):57– 60.
  • Kini CR, Sharma NY, Satish Shenoy B. Thermo-structural investigation of gas turbine blade provided with helicoidal passages. Indian Journal of Science and Technology. 2006; 9(6):1–6.
  • Kini CR, Shenoy BS, Sharma NY. (in press). Effect of grooved cooling passage near the trailing edge region for HP stage gas turbine blade - A numerical investigation. Progress in Computational Fluid Dynamics. An International Journal; 2016.
  • Choi J, Mhetras S, Han J. Film cooling and heat transfer on two cutback trailing edge models with internal perforated blockages. Journal of Heat Transfer by ASME. 2008; 130(1):13.
  • Li X, Wang T. Two phase flow simulation of mist film cooling on turbine blades with conjugate internal cooling. Journal of Heat Transfer. 2008 Oct; 130(10):13.

Refbacks

  • »
  • »
  • »
  • »
  • »
  • »
  • »
  • »
  • »
  • »
  • »


Creative Commons License
This work is licensed under a Creative Commons Attribution 3.0 License.