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A study on an axial-type 2-D turbine blade shape for reducing the blade profile loss


Losses on the turbine consist of the mechanical loss, tip clearance loss, secondary flow loss and blade profile loss etc.,. More than 60 % of total losses on the turbine is generated by the two latter loss mechanisms. These losses are directly related with the reduction of turbine efficiency. In order to provide a new design methodology for reducing losses and increasing turbine efficiency, a two-dimensional axial-type turbine blade shape is modified by the optimization process with two-dimensional compressible flow analysis codes, which are validated by the experimental results on the VKI turbine blade. A turbine blade profile is selected at the mean radius of turbine rotor using on a heavy duty gas turbine, and optimized at the operating condition. Shape parameters, which are employed to change the blade shape, are applied as design variables in the optimization process. Aerodynamic, mechanical and geometric constraints are imposed to ensure that the optimized profile meets all engineering restrict conditions. The objective function is the pitchwise area averaged total pressure at the 30 % axial chord downstream from the trailing edge. 13 design variables are chosen for blade shape modification. A 10.8 % reduction of total pressure loss on the turbine rotor is achieved by this process, which is same as a more than 1 % total-to-total efficiency increase. The computed results are compared with those using 11 design variables, and show that optimized results depend heavily on the accuracy of blade design.

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A :

Blade sectional area

Cl :

Blade loading coefficient (lift/dynamic pressure)

C p :

Pressure coefficient


Axial chord length


Tangential chord length

ds :

Length between the inflection points

h :


k :

Turbulence kinetic energy

P :



Total pressure normalized by double of dynamic pressure

Re :

Reynolds number

T :


v :

Absolute velocity

w :

Relative velocity

x :

Axial length from the leading edge on a blade

xl :

Violating length by the inflection point

X :

Design variables

Y :

Total pressure loss coefficient


Flow angle


Turbulence dissipation rate


Angle on the blade surface




Standard deviation


Enthalpy loss coefficient


Initial value


Inlet flow condition


Outlet flow condition










Value at reference location


Nozzle inlet, nozzle exit, rotor exit


  1. Anderson, D. A., Tannehill, J. C. and Pletcher R. H., 1984,Computational Fluid Mechanics and Heat Transfer, McGraw-Hill, pp. 181–197.

  2. Chen, Y. S., 1989, “Compressible and Incompressible Flow Computations with a Pressure Based Method,”AIAA-89-0286, 27th Aerospace Science Meeting.

  3. Chen, Y. S. and Kim, S.W., 1987, “Computation of Turbulence Flows using a Extended k-ε Turbulence Closure Model,”NASA CR-179204.

  4. Cho, S. Y., Oh, K. S. and Choi, B. S., 2000, “A Study of Design Parameters for Designing an Axial Turbine Blade Geometry,” InProceedings of the 8 th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, Hawaii, Vol. 1, pp. 222–228.

  5. Cho, S. Y., Oh, K. S., Yoon, E. S. and Choi, B. S., 2000, “Study on the Minimization of Shape Parameters for Reverse Designing Axial Turbine Blade Geometry,” InThe International Symposium on Energy, Environment, and Cold Region. Kitami, No. 109.

  6. Cofer, J. I., Reinher, J. K. and Summer, W. J., 1993, “Advances in Steam Path Technology,” GER-3713D, pp. 1–25.

  7. Demeulenare, A. and Braembussche, R., 1998, “Three-Dimensional Inverse Method for Turbomachinery Blading Design,”J. of Turbomachinery, Vol. 120, pp. 247–254.

  8. Engeli, M., Zollinger, H. J. and Allemann, J. C, 1978, “A Computer program for the design of Turbomachinery Blades,”ASME 78-GT-36.

  9. Goel, S., Cofer IV, J. I. and Singh, H., 1996, “Turbine Airfoil Design Optimization,”ASME 96-GT-158.

  10. Horlock, J.H., 1973, “Axial Flow Turbine, Robert Krieger Publishing Co.,” pp. 60–66.

  11. Kiock, R., Lehthaus, F., Baines, N. C. and Sieverding, C. H., 1986, “The Transonic Flow Through a Plane Turbine Cascade as Measured in Four European Wind Tunnels,”J. of Eng. for Gas Turbines and Power, Vol. 108, pp. 277–284.

  12. Korakianitis, T., 1993, “Hierarchical Development of Three Direct-Design Methods for Two-Dimensional Axial-Turbomachinery. Cascades,”J. of Turbomachinery, Vol. 115, pp. 314–324.

  13. Lee, S. Y. and Kim, K. Y., 2000, “Design Optimization of Axial Flow Compressor Blades with Three-Dimensional Navier-Stokes Solver,”KSME Int. J., Vol. 14, No. 9, pp. 1005–1012.

  14. Pierret, S., 1999, “Three-Dimensional Blade Design by Means of an Artificial Neural Network and Navier-Stokes Solver,” InTurbomachinery Design Blade Design Systems. Von Karman Institute Lecture Series 1999–02.

  15. Pritchard, L. J., 1985, “An Eleven Parameter Axial Turbine Airfoil Geometry Model,”ASME GT-85-219.

  16. VisualDOC, 1998, “VisualDOC Reference Manual Version 1.0,”Vanderplaats R&D Inc.

  17. Yoon, E. S., Choi, B. S., Park, M. Y. and Park, B. K., 2001, “Development of Design and Manufacturing Technology for Cooled Turbine Blades,” KIMM Report, UNC331-883M, pp. 14–57.

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Correspondence to Soo-Yong Cho or Eui-Soo Yoon or Bum-Seog Choi.

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Cho, S., Yoon, E. & Choi, B. A study on an axial-type 2-D turbine blade shape for reducing the blade profile loss. KSME International Journal 16, 1154–1164 (2002).

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Key Words

  • Turbine Blade Design
  • Turbine Blade Optimization
  • Axial-Type Turbine
  • Shape Parameters
  • 2-D Turbine Blade
  • Compressible Flow Analysis
  • Heavy Duty Gas Turbine