Skip to main content

Advertisement

SpringerLink
Log in

Optimization of pre-swirl nozzle shape and radial location to increase discharge coefficient and temperature drop

  • Published:
Journal of Mechanical Science and Technology Aims and scope Submit manuscript

Abstract

Hole-type pre-swirl nozzle was optimized using CFD analysis and experiments. CFD methodologies were validated by comparing the CFD results with experiments. Four design variables were considered in the optimization process: Nozzle inlet length (L), outlet length (l), inlet diameter (D), and radial location (rp). The optimization process included the optimal Latin hypercube design sampling method with the Kriging surrogate model and genetic algorithm. The single-objective optimization was performed to maximize the discharge coefficient. Results showed that the optimized nozzle reduced total pressure losses and increased mass flow rate. Total temperature drop effectiveness was increased from 0.07 to 0.29. The total temperature in pre-swirl system could be characterized as the reduction in temperature by nozzle acceleration and elevation by aerodynamic losses due to friction and viscous effects in the system. The optimized model showed a discharge coefficient of 0.846, which was 31.7 % higher than the baseline condition. By improving the discharge coefficient the pre-swirl system reduced aerodynamic losses, and the mass flow rate was increased at certain pressure ratios or satisfied the pressure margin for blade cooling.

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

Access this article

Log in via an institution

Subscribe and save

Springer+ Basic
$34.99 /Month
  • Get 10 units per month
  • Download Article/Chapter or eBook
  • 1 Unit = 1 Article or 1 Chapter
  • Cancel anytime
Subscribe now

Buy Now

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

Instant access to the full article PDF.

Institutional subscriptions

Similar content being viewed by others

Abbreviations

A :

Cross-sectional area, m2

a :

Pitch radius of inner cavity, m

a 1 :

Model constant of turbulence model

B :

Model constant of turbulence model

b :

Pitch radius of outer cavity, m

C D :

Discharge coefficient

C W :

Non-dimensional mass flow rate

c :

Cavity gap, m

D :

Nozzle inlet diameter, m

d :

Nozzle exit diameter, m

F :

Blending function

h :

Enthalpy, kJ/kg

k :

Turbulence kinetic energy

l p :

Pre-swirler axial length, m

ṁ :

Mass flow rate, kg/s

p :

Pressure, N/m2

r :

Radius, m

r p :

Pitch radius of nozzle exit, m

r r :

Pitch radius of receiver hole, m

R :

Specific gas constant, J/(kg K)

Re :

Reynolds number = (Vpd)/v

Re Φ :

Rotational Reynolds number = (Ω rp2)/v

S E :

Source due to heat production

S M :

Body force, N

T :

Temperature, K

V :

Velocity, m/s

W :

Relative velocity, m/s

y + :

Dimensionless wall distance

α :

Pre-swirl angle, deg

α’:

Model constant of turbulence model

β :

Swirl ratio

γ :

Fraction

η :

Temperature drop effectiveness

κ :

Isentropic exponent

ν :

Kinematic viscosity, m2/s

ρ :

Density, m3/kg

σ :

Model constant of turbulence model

τ :

Viscous stress, N/m2

π :

Pressure ratio = (p0t/p2s)

Ω:

Angular velocity of rotor, 1/s

Ωij :

Mean rate of rotation tensor

ω :

Specific rate of dissipation

abs:

Absolute

ax:

Axial

i:

Ideal

p:

Pre-swirler

R:

Receiver hole

s:

Static

t:

Total, tangential, temperature

Φ:

Rotational, circumferential

0:

Stage 0

1:

Stage 1

2:

Stage 2

References

  1. H. I. H. Saravanamuttoo, G. F. C. Rogers, H. Cohen and P. V. Straznicky, Gas Turbine Theory, 6th Edition, Prentice Hall, London (2009) 366–376.

    Google Scholar 

  2. Rolls-Royce, The JET ENGINE, Rolls-Royce plc, 5th Edition (1996) 85–88.

  3. M. Dittmann, T. Geis, V. Schramm, S. Kim and S. Wittig, Discharge coefficients of a preswirl system in secondary air systems, ASME J. Turbomach., 124 (1) (2002) 119–124.

    Article  Google Scholar 

  4. U. Javiya, J. Chew and N. Hills, A comparative study of cascade vanes and drilled nozzle design for pre-swirl, ASME Turbo Expo (2011) No. GT2011–46006.

  5. C. Bricaud, T. Geis, K. Dullenkopf and H. J. Bauer, Measurement and analysis of aerodynamic and thermodynamic losses in pre-swirl system arrangements, ASME Turbo Expo, Montreal, Canada (2007) GT-2007–27191.

    Google Scholar 

  6. F. Ciampoli, F. W. Chew, S. Shahpar and E. Willocq, Automatic optimisation of pre-swirl nozzle design, ASME Turbo Expo, Barcelona, Spain (2006) GT-2006–90249.

  7. A. V. Mirzamoghadam, A. Riahi and M. C. Morris, High pressure turbine low radius radial TOBI discharge coefficient validation process, ASME. J. Fluids Eng. (2013) 135 (7) 071103–071103–9.

    Article  Google Scholar 

  8. V. Laurello, M. Yuri, K. Fujii, K. Ishizaka, T. Nakamura and H. Nishimura, Measurement and analysis of an efficient turbine rotor pump work reduction system incorporating pre-swirl nozzles and a free vortex pressure augmentation chamber, ASME Turbo Expo, Vienna, Austria (2004) GT-2004–53090.

  9. H. Lee, J. Lee, S. Kim, J. Cho and D. Kim, Pre-swirl system design including inlet duct shape by using CFD analysis, Proceedings of the ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. Volume 5B: Heat Transfer, Oslo, Norway, June 11–15 (2018) V05BT15A029.

  10. Y. Liu, G. Liu, X. Kong and Q. Feng, Design and numerical analysis of a new type of pre-swirl nozzle, Proceedings of the ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. Volume 5A: Heat Transfer, Seoul, South Korea, June 13–17 (2016) V05AT15A013.

  11. D. Kim, J. Kim, H. Lee and J. Cho, Effect of splitter location on the characteristics of a vane-type pre-swirl system, Journal of Mechanical Science and Technology, 31 (3) (2017) 1267–1274.

    Article  Google Scholar 

  12. Y. Yan, M. F. Gord, G. D. Lock, M. Wilson and J. M. Owen, Fluid dynamics of a pre-swirl rotor-stator system, Journal of Turbomachinery, 125 (2003) 641–647.

    Article  Google Scholar 

  13. P. Lewis, Pre-swirl rotor-stator systems: Flow and heat transfer, Ph.D. Thesis, Department of Mechanical Engineering, University of Bath (2008).

  14. H. Wu, G. Liu, Z. Wu, Q. Feng and Y. Wang, Measurement of pressures and temperatures in a cover-plate pre-swirl system, ASME Turbo Expo (2018) No. GT2018–75671.

  15. E. Kwak, N. Lee and S. Lee, Performance evaluation of two-equation turbulence models for 3D wing-body configuration, IJASS, 13 (3) (2012) 307–316.

    Article  Google Scholar 

  16. F. Mentor, Improved Two-equation k-ω Turbulence Models for Aerodynamic Flows, NASA (1992).

  17. J. F. Wendt, Computational fluid dynamics. An introduction, 3. Ed., Germany, Doi: https://doi.org/10.1007/978-3-540-85056-4.

    MATH  Google Scholar 

  18. U. Javiya, J. W. Chew, N. J. Hills, L. Zhou, M. Wilson and G. D. Lock, CFD analysis of flow and heat transfer in a direct transfer preswirl system, ASME. J. Turbomach., 134 (3) (2011) 031017–031017–9.

    Article  Google Scholar 

  19. J. S. Park, Optimal Latin-hypercuve designs for computer experiments, Journal of Statistical Planning and Inference, 39 (1994) 95–111.

    Article  MathSciNet  Google Scholar 

  20. F. A. C. Viana, G. Venter and V. Balabanov, An algorithm for fast optimal Latin hypercube design of experiments, International Journal for Numerical Methods in Engineering, 82 (2) (2010) 135–156.

    MathSciNet  MATH  Google Scholar 

  21. S. Jeong, M. Murayama and K. Yamamoto, Efficient optimization design method using kriging model, Journal of Aircraft, 42 (2) (2005) 413–420.

    Article  Google Scholar 

  22. T. W. Simpson, T. M. Mauery, J. J. Korte and F. Mistree, Kriging models for global approximation in simulation-based multidisciplinary design optimization, AIAA Journal, 39 (12) (2001) 2233–2241.

    Article  Google Scholar 

  23. P. R. Kukutla and B. V. S. S. S. Prasad, Secondary air performance optimization of a combined impingement and film cooled gas turbine nozzle guide vane, Proceedings of ASME 2017 Gas Turbine India Conference, Bangalore, India, December 7–8 (2017).

  24. P. R. Childs, Rotating Flow, Oxford: Elsevier Inc. (2011).

    Google Scholar 

Download references

Author information

Authors and Affiliations

  1. Department of Mechanical Engineering, Hanyang University, Seoul, Korea

    Hyungyu Lee & Jinsoo Cho

  2. Department of Convergence Mechanical Engineering, Hanyang University, Seoul, Korea

    Jungsoo Lee

  3. 5th Directorate, 4th R&D Institute, Agency for Defense Development, Daejeon, Korea

    Donghwa Kim

Authors
  1. Hyungyu Lee
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. Jungsoo Lee
    View author publications

    You can also search for this author in PubMed Google Scholar

  3. Donghwa Kim
    View author publications

    You can also search for this author in PubMed Google Scholar

  4. Jinsoo Cho
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to Jinsoo Cho.

Additional information

Recommended by Associate Editor Donghyun You

Hyungyu Lee is a Ph.D. student in the Department of Mechanical Engineering at Hanyang University in Seoul, Korea. He is a member of the Applied Aerodynamics Laboratory. He is majoring in aerodynamics and turbomachinery. He has conducted studies on the aerodynamic with heat transfer analysis of gas turbine secondary air system.

Jinsoo Cho is a Professor in the Department of Mechanical Engineering at Hanyang University in Seoul, Korea. He is in-charge of the Applied Aerodynamics Laboratory. In 1988, he received a doctorate in philosophy from Purdue University, USA. His doctoral research topic was the steady/unsteady aerodynamic analysis of aircraft, including propellers and ducted fans. He studied aerodynamics and turbomachinery.

Rights and permissions

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Lee, H., Lee, J., Kim, D. et al. Optimization of pre-swirl nozzle shape and radial location to increase discharge coefficient and temperature drop. J Mech Sci Technol 33, 4855–4866 (2019). https://doi.org/10.1007/s12206-019-0926-5

Download citation

  • Received:

  • Revised:

  • Accepted:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s12206-019-0926-5

Keywords

Search

Navigation