Skip to main content

Advertisement

SpringerLink
Log in

Aerodynamic optimization of the tangential stacking line of a transonic axial flow compressor rotor using genetic algorithm

  • Technical Paper
  • Published:
Journal of the Brazilian Society of Mechanical Sciences and Engineering Aims and scope Submit manuscript

Abstract

In this paper, aerodynamic optimization of the tangential stacking line of the NASA Rotor 37 as a transonic axial flow compressor rotor is carried out using computational fluid dynamics and genetic algorithm. To cover a wide range of curves with a minimum number of design parameters, a B-spline curve with three control points at 33, 66 and 100% of the blade span is used to define the blade stacking lines. Firstly, by rotating the tangential position of the control points, different rotors have been created and are simulated using the Navier–Stokes governing equations. Then, using genetic algorithm operators, based on the adiabatic efficiency as an objective function, new blades are created and numerically simulated. This process is repeated to achieve maximum adiabatic efficiency. The comparison of the optimum blade and the original blade indicates that optimal tangential stacking line causes the shock wave to move downstream and reduce the secondary flow which has led to an improvement of about 1.7% of the adiabatic efficiency.

This is a preview of subscription content, log in via an institution to check access.

Access this article

Log in via an institution

Price excludes VAT (USA)
Tax calculation will be finalised during checkout.

Instant access to the full article PDF.

Institutional subscriptions

Fig. 1
Fig. 2
Fig. 3
Fig. 4
Fig. 5
Fig. 6
Fig. 7
Fig. 8
Fig. 9
Fig. 10
Fig. 11
Fig. 12
Fig. 13
Fig. 14
Fig. 15
Fig. 16

Similar content being viewed by others

Abbreviations

C P :

Pressure coefficient

Exp.:

Experimental

LE:

Leading edge

M tip :

Rotor tip relative Mach number

PRPeak :

Pressure ratio at max efficiency

P :

Static pressure

P 0 :

Total pressure

T 0 :

Total temperature

y + :

Non-dimensional wall distance

η :

Adiabatic efficiency

θ 1 :

Lean angle at 33% span

θ 2 :

Lean angle at 66% span

θ 3 :

Lean angle at 100% span

ACM:

Additive correction multi-grid

CFD:

Computational fluid dynamics

GA:

Genetic algorithm

MCA:

Multi-circular arc

SST:

Shear Stress Transport

References

  1. Gallimore SJ, Bolger JJ, Cumpsty NA et al (2002) The use of sweep and dihedral in multistage axial flow compressor blading-part II: low and high-speed designs and test verification. J Turbomach 124:531–541

    Google Scholar 

  2. Gallimore SJ, Bolger JJ, Cumpsty NA et al (2002) The use of sweep and dihedral in multistage axial flow compressor blading-part I: university research and methods development. J Turbomach 124:521–532

    Article  Google Scholar 

  3. Bergner J, Hennecke DK, Hoeger M et al (2003) Darmstadt rotor no.2- part II: design of lean rotor blades. Int J Rotat Mach 9:385–391

    Google Scholar 

  4. Ahn CS, Kim KY (2003) Aerodynamic design optimization of a compressor rotor with Navier–Stokes analysis. Proc Inst Mech Eng Part A J Power Energy 217:179–183

    Article  Google Scholar 

  5. Denton,J D, Xu L (2002) The effects of lean and sweep on transonic fan performance. In: Proceeding of ASME TURBO EXPO 2002, Amsterdam, 3–6 June 2002, paper no. GT-2002-30327

  6. Oyama A, Liou MS, Obayashi SH (2003) High-fidelity swept and leaned rotor blade design optimization using evolutionary algorithm. In: 16th AIAA computational fluid dynamics conference, Orlando, Florida, 23–26 June 2003, paper no. AIAA 2003-4091

  7. Jang CM, Samad A, Kim KY (2006) Optimal design of swept, leaned and skewed blades in a transonic axial compressor. In: Proceedings of GT2006 ASME turbo expo 2006: power for Land Sea and air, Barcelona, 8–11 May 2006, paper no. GT-2006-90384

  8. Yang L, Hua O, Zhao-Hui D (2007) Optimization design and experimental study of low-pressure axial fan with forward-skewed blades. Int J Rotat Mach Article ID 85275

  9. Benini E (2004) Three-dimensional multi-objective design optimization of a transonic compressor rotor. AIAA J Propuls Power 20(3):559–565

    Article  Google Scholar 

  10. Benini E, Biollo R (2007) Aerodynamics of swept and leaned transonic compressor-rotors. J Appl Energy 84:1012–1027

    Article  Google Scholar 

  11. Razavi SR, Boroomand M (2014) Optimal design and aerodynamics Study of leaned transonic axial flow fan rotors. In: ASME 2014 international mechanical engineering congress and exposition, Montreal, 14–20 Nov 2014, Paper no. IMECE 2014-39796

  12. Piegl L, Tilles W (1997) The NURBS book, 2nd edn. Springer, Berlin

    Book  Google Scholar 

  13. Moore RD, Reid L (1980) Performance of single-stage axial flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26, respectively, and with design pressure ratio of 2.05, NASA-TP-1659

  14. Dunham J (1998) CFD validation for propulsion system components. AGARD-AR-355

  15. ANSYS-CFX (2016) Release 17.0, ANSYS Inc.

  16. Hutchinson BR, Raithby GD (1986) A multigrid method based on additive correction strategy. J Numer Heat Transf 9(5):511–537

    Google Scholar 

  17. Launder BE, Spalding DB (1974) The numerical computation of turbulent flows. J Comput Methods Appl Mech Eng 3:269–289

    Article  Google Scholar 

  18. ANSYS CFX (2016) Release 17.0, Solver theory guide, ANSYS Inc.

  19. Haupt RL, Haupt SE (2004) Practical genetic algorithms, 2nd edn. Willy, Hoboken

    MATH  Google Scholar 

Download references

Author information

Authors and Affiliations

  1. Department of Mechanical and Aerospace Engineering, Malek Ashtar University of Technology, Isfahan, Iran

    M. Asghari, M. Agha Seyed Mirzabozorg & M. Adami

Authors
  1. M. Asghari
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. M. Agha Seyed Mirzabozorg
    View author publications

    You can also search for this author in PubMed Google Scholar

  3. M. Adami
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to M. Asghari.

Additional information

Technical Editor: André Cavalieri.

Rights and permissions

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Asghari, M., Agha Seyed Mirzabozorg, M. & Adami, M. Aerodynamic optimization of the tangential stacking line of a transonic axial flow compressor rotor using genetic algorithm. J Braz. Soc. Mech. Sci. Eng. 41, 37 (2019). https://doi.org/10.1007/s40430-018-1500-2

Download citation

  • Received:

  • Accepted:

  • Published:

  • DOI: https://doi.org/10.1007/s40430-018-1500-2

Keywords

Search

Navigation