A Blade Altering Toolbox for Automating Rotor Design Optimization

Abstract

The Blade Altering Toolbox (BAT) described in this paper is a tool designed for fast reconstruction of an altered blade geometry for design optimization purposes. The BAT algorithm is capable of twisting a given rotor’s angle of attack and stretching the chord length along the span of the rotor. Several test cases were run using the BAT’s algorithm. The BAT code’s twisting, stretching, and mesh reconstruction capabilities proved to be able to handle reasonably large geometric alterations to a provided input rotor geometry. The test examples showed that the toolbox’s algorithm could handle any stretching of the blade’s chord as long as the blade remained within the original bounds of the unaltered mesh. The algorithm appears to fail when the net twist angle applied the geometry exceeds approximately 30 degrees, however this limitation is dependent on the initial geometry and other input parameters. Overall, the algorithm is a very powerful tool for automating a design optimization procedure.

Keywords

Mesh reconstruction / Mesh alteration / Rotor alteration / Design optimization

References

[1.] Ahn, C.S., Kim, K.Y.: Aerodynamic design optimization of an axial flow compressor rotor. In: ASME Turbo Expo 2002. ASME, Amsterdam (2002)

[2.] Aqilah F, Islam M, Juretic F, Guerrero J, Wood D, Ani FN, et al.. Study of mesh quality improvement for CFD analysis of an airfoil. IIUM Eng. J., 2018, 19(2): 203-212,

[3.] Arora JS. . Introduction to optimum design, 2012 3 Waltham Academic Press 733-737

[4.] Ashcraft, S.W., Padron, A.S., Pascioni, K.A., Stout, G.W., Jr.: Huff, D.L.: Review of Propulsion Technologies for N+3 Subsonic Vehicle Concepts, NASA TM-2011-217239, Oct. (2011). https://doi.org/10.2514/6.2020-0131

[5.] Aziz, M.A., Owis, F.M., Abdelrahman, M.M.: Design optimization of a transonic-fan rotor using numerical computations of the full compressible Navier-Stokes equations and simplex algorithm. Int. J. Rotat. Mach. 1–16 (2014). https://doi.org/10.1155/2014/743154

[6.] Cadence Design Systems, Inc.: Pointwise: Meshing Software. Cadence Design Systems. Fort Worth, TX (2021)

[7.] Chen JP, Briley WR. . A Parallel Flow Solver for Unsteady Multiple Blade Row Turbomachinery Simulations, 2001 New Orlean ASME-2001-GT-0348,

[8.] Glover F. Tabu search - Part I. ORSA J. Comput., 1989, 1(3): 190-206,

[9.] Joshi, D.: Aerodynamic Shape Optimization of 3D Gas Turbine Blade Using Differential Evolution Method, M.S. Thesis, Dept. of Aerospace Engineering, University of Texas at Arlington, Arlington, TX, May (2010)

[10.] Juretić F, Gosman AD. Error analysis of the finite-volume method with respect to mesh type. Num. Heat Transf. Part B, 2010, 57(6): 414-439,

[11.] Mengistu T, Ghaly W. Aerodynamic optimization of turbomachinery blades using evolutionary methods and ANN-based surrogate models. Optim. Eng., 2008, 9(3): 239-255,

[12.] Nelder JA, Mead R. A simplex method for function minimization. Comput. J., 1965, 7(4): 308-313,

[13.] Spekreijse S.P.: Elleptic Generation Systems. Handbook of Grid Generation. Nationaal Lucht- en Ruimtevaartlaboratorium NLR, Netherlands (1997)

[14.] Storn, R., Price, K.: Differential evolution—a simple and efficient adaptive scheme for global optimization over continuous spaces. Technical Report TR-95-012, International Computer Science Institute (1995)

[15.] Wang, F.: Whole Aero-Engine Meshing and CFD Simulation, Ph.D. Dissertation, Mechanical Engineering Dept., Imperial College London, London, England (2013)

[16.] Wernick, A.R., Chen, J.P.: Rotor Blade Design Optimization for Boundary Layer Ingesting Inlet Fan. AIAA Technical Paper, AIAA SciTech Forum (2020)

[17.] Wernick, A.R., Chen, J.P., Giuliani, J.E.: Design Optimization of a Fan Blade under Boundary Layer Ingestion Flow. AIAA Technical Paper, AIAA SciTech Forum (2023)

[18.] Woodward, R.P., Hughes, C.E.: Noise Benefits of Increased Fan Bypass Nozzle Area, NASA Glenn Research Center, TM-2004-213396, Cleveland, Ohio (2004)

Funding

Glenn Research Center(GRT00060658); National Science Foundation(N/A)