Skip to main content
SpringerLink
Log in

Improvement of Film Cooling Design for Turbine Vane Leading Edge Considering Combustor Outflow

  • Published:
Journal of Thermal Science Aims and scope Submit manuscript

Abstract

As the interaction between the combustor and the turbine in the aero-engine continues to increase, the film cooling design considering the combustor swirling outflow has become the research focus. The swirling inflow and high-temperature gas first affect the vane leading edge (LE). However, no practical improved solution for the LE cooling design has been proposed considering the combustor swirling outflow. In this paper, the improved scheme of showerhead cooling is carried out around the two ways of adopting the laid-back-fan-shaped hole and reducing the coolant outflow angle. The film cooling effectiveness (η) and the coolant flow state are obtained by PSP (pressure-sensitive-paint) and numerical simulation methods, respectively. The research results show that the swirling inflow increases the film distribution inhomogeneity by imposing the radial pressure gradient on the vane to make the film excessively gather in some positions. The showerhead film cooling adopts the laid-back-fan-shaped hole to reduce the momentum when the coolant flows out. Although this cooling scheme improves the film attachment and increases the surface-averaged film cooling effectiveness (ηsur) by as much as 15.4%, the film distribution inhomogeneity increases. After reducing the coolant outlet angle, the wall-tangential velocity of the coolant increases, and the wall-normal velocity decreases. Under the swirl intake condition, both η and the film distribution uniformity are significantly increased, and the growth of ηsur is up to 16.5%. This paper investigates two improved schemes to improve the showerhead cooling under the swirl intake condition to provide a reference for the vane cooling design.

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

Similar content being viewed by others

Abbreviations

C :

Chord length of the vane/mm

C O2 :

Oxygen concentration/mol·L−1

D :

Diameter/mm

d :

Mass diffusivity/m2·s−1

H :

Height of vane/mm

h :

Distance from the hub/mm

I :

Luminous intensity

LE:

Leading edge

Le :

Lewis number

M :

Molar mass

m :

Mass flow/kg·s−1

MFR:

Coolant mass flow ratio

P :

Film hole spacing/mm

P O2 :

Oxygen pressure/Pa

PS:

Pressure surface

PSP:

Pressure-sensitive paint

Re :

Reynolds number

SN:

Swirl number

SS:

Suction surface

T :

Temperature/K

TR:

Trailing edge

V :

The velocity of the inlet/m·s−1

α :

Thermal diffusivity/m2·s−1

η :

Film cooling effectiveness

μ :

Dynamic viscosity/Pa·s

ρ :

Density/kg·m−3

φ :

The axial angle of the swirl generator vane/(°)

aw:

Wall adjacent value

c:

Coolant or secondary flow

Fg:

Foreign gas

g:

Mainstream

in:

Inner diameter

out:

Outer diameter

sur:

Surface-averaged value

References

  1. Commission E., Flightpath 2050: Europe’s vision for aviation. University of Munich, 2011.

  2. Bauer H.J., New low emission strategies and combustion designs for civil aeroengine applications. Progress in Computational Fluid Dynamics, 2004, 4: 130–142.

    Article  Google Scholar 

  3. Correa S.M., Power generation and aeropropulsion gas turbines: from combustion science to combustion technology. Symposium (International) on Combustion, 1998, 27(2): 1793–1807.

    Article  Google Scholar 

  4. Bunker R.S., Gas turbine heat transfer: 10 remaining hot gas path challenges. Turbo Expo: Power for Land, Sea, and Air, 2006, 4238: 1–14.

    Google Scholar 

  5. Pyliouras S., Schiffer H.P., Janke E., et al., Effects of non-uniform combustor exit flow on turbine aerodynamics. Turbo Expo: Power for Land, Sea, and Air, 2012, 44748: 1691–1701.

    Google Scholar 

  6. Qureshi I., Smith A.D., Povey T., HP vane aerodynamics and heat transfer in the presence of aggressive inlet swirl. Journal of Turbomachinery, 2013, 135(2): 021040.

    Article  Google Scholar 

  7. Qureshi I., Beretta A., Chana K., et al., Effect of aggressive inlet swirl on heat transfer and aerodynamics in an unshrouded transonic HP turbine. Journal of Turbomachinery, 2012, 134(6): 61023–61021.

    Article  Google Scholar 

  8. Wang Z., Wang Z., Zhang W., et al., Numerical study on unsteady film cooling performance of turbine rotor considering influences of inlet non-uniformities and upstream coolant. Aerospace Science and Technology, 2021, 119: 107089.

    Article  Google Scholar 

  9. Wang Z., Wang D., Wang Z., et al., Heat transfer analyses of film-cooled HP turbine vane considering effects of swirl and hot streak. Applied Thermal Engineering, 2018, 142: 815–829.

    Article  Google Scholar 

  10. Bacci T., Becchi R., Picchi A., et al., Adiabatic effectiveness on high-pressure turbine nozzle guide vanes under realistic swirling conditions. Journal of Turbomachinery, 2019, 141(1): 011009.

    Article  Google Scholar 

  11. Griffini D., Insinna M., Salvadori S., et al., On the effects of inlet swirl on adiabatic film cooling effectiveness and net heat flux reduction of a heavily film-cooled vane. The 22nd International Symposium on Air Breathing Engines, 2015.

  12. Insinna M., Griffini D., Salvadori S., et al., On the effect of an aggressive inlet swirl profile on the aero-thermal performance of a cooled vane. Energy Procedia, 2015, 81: 1113–1120.

    Article  Google Scholar 

  13. Yin H., Qin Y., Ren J., et al., Effect of inlet swirl on the model leading edge of turbine vane. Turbo Expo: Power for Land, Sea, and Air, 2013, 55232: V06BT38A004.

    Google Scholar 

  14. Yin H., Liu S., Feng Y., et al., Experimental test rig for combustor-turbine interaction research and test results analysis. Turbo Expo: Power for Land, Sea, and Air, 2015, 56635: V02AT38A001.

    Google Scholar 

  15. Yin H., Ren J., Jiang H.D., Effects of inlet swirl condition on the flow and heat transfer performance of gas turbine vane. Journal of Engineering Thermophysics, 2012, 33(11): 1868–1871.

    Google Scholar 

  16. Giller L., Schiffer H.P., Interactions between the combustor swirl and the high pressure stator of a turbine. ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, 2012.

  17. Wu Z., Zhu H., Liu C., et al., Showerhead film cooling injection orientation design on the turbine vane leading edge considering representative lean burn combustor outflow. Proceedings of the Institution of Mechanical Engineers Part G. Journal of Aerospace Engineering, 2021, 235(15): 2342–2356.

    Google Scholar 

  18. Wu Z., Zhu H., Liu C., et al., Superposition effect of the leading edge film on the downstream film cooling of a turbine vane under combustor swirling outflow. Journal of Engineering for Gas Turbines and Power, 2022, 144(3): 031022.

    Article  Google Scholar 

  19. Reiss H., Bolcs A., Experimental study of showerhead cooling on a cylinder comparing several configurations using cylindrical and shaped holes. Journal of Turbomachinery, 2000, 122(1): 161–169.

    Article  Google Scholar 

  20. Liu C., Zhang F., Zhang S., et al., Experimental investigation of the full coverage film cooling effectiveness of a turbine blade with shaped holes. Chinese Journal of Aeronautics, 2022, 35(3): 297–308.

    Article  Google Scholar 

  21. Zhang L., Qian B., Zhang C., et al., Numerical study on the cooling characteristics of cat-ear-shaped film-cooling holes on turbine blades. Case Studies in Thermal Engineering, 2022, 36: 102050.

    Article  Google Scholar 

  22. Wang B., Wang F., Zhang X., et al., Numerical analysis of cooling efficiency for turboshaft engines with converging-diverging film cooling holes. International Journal of Thermal Sciences, 2023, 185: 108044.

    Article  Google Scholar 

  23. Li Y., Xu H., Wang J., et al., Large eddy simulation of trenched cylindrical film hole with backward compound angles. International Journal of Thermal Sciences, 2023, 184: 107910.

    Article  Google Scholar 

  24. Huang Y., Zhang J., Wang C., Multi-objective optimization of round-to-slot film cooling holes on a flat surface. Aerospace Science and Technology, 2020, 100: 105737.

    Article  Google Scholar 

  25. Wagner G., Ott P., Vogel G., et al., Leading edge film cooling and the influence of shaped holes at design and off-design conditions. Turbo Expo: Power for Land, Sea, and Air, 2007, 47934: 577–587.

    Google Scholar 

  26. Saumweber C., Schulz A., Wittig S., et al., Effects of entrance crossflow directions to film cooling holes. Annals of the New York Academy of Sciences, 2001, 934(1): 401–408.

    Article  ADS  Google Scholar 

  27. Albert J.E., Bogard D.G., Measurements of adiabatic film and overall cooling effectiveness on a turbine vane pressure side with a trench. Journal of Turbomachinery, 2013, 135(5): 051007.

    Article  Google Scholar 

  28. Nathan M.L., Dyson T.E., Bogard D.G., et al., Adiabatic and overall effectiveness for the showerhead film cooling of a turbine vane. Journal of Turbomachinery, 2014, 136(3): 031005.

    Article  Google Scholar 

  29. Williams R.P., Dyson T.E., Bogard D.G., et al., Sensitivity of the overall effectiveness to film cooling and internal cooling on a turbine vane suction side. Journal of Turbomachinery, 2014, 136(3): 031006.

    Article  Google Scholar 

  30. Han J.C., Rallabandi A.P., Turbine blade film cooling using PSP technique. Frontiers in Heat and Mass Transfer, 2010, 1(1): 013001.

    Article  Google Scholar 

  31. Chen D., Zhu H., Liu C., et al., Combined effects of unsteady wake and free-stream turbulence on turbine blade film cooling with laid-back fan-shaped holes using PSP technique. International Journal of Heat and Mass Transfer, 2019, 133: 382–392.

    Article  Google Scholar 

  32. Zhang B., Zhu H., Yao C., et al., Investigation on aerothermal performance of a rib-slot scheme on the multi-cavity tip of a gas turbine blade. International Journal of Heat and Mass Transfer, 2021, 176: 121408.

    Article  Google Scholar 

  33. Ye L., Liu C., Chen L., et al., Influences of groove configuration and density ratio on grooved leading-edge showerhead film cooling using the pressure sensitive paint measurement technique. International Journal of Heat and Mass Transfer, 2022, 190: 122641.

    Article  Google Scholar 

  34. Li J., Experimental and theoretical research on gas turbine film cooling. Tsinghua University, Beijing, China, 2011.

    Google Scholar 

  35. Schroeder R.P., Thole K.A., Adiabatic effectiveness measurements for a baseline shaped film cooling hole. Turbo Expo: Power for Land, Sea, and Air, 2014, 45721: V05BT13A036.

    Google Scholar 

  36. Huang Y., Yang V., Dynamics and stability of lean-premixed swirl-stabilized combustion. Progress in Energy and Combustion Science, 2009, 35(4): 293–364.

    Article  Google Scholar 

  37. Kim I., Kim J., Choe Y., et al., Effect of vane angle on combustion characteristics of premixed H2/air in swirl micro-combustors with straight vane or twisted vane. Applied Thermal Engineering, 2023, 228: 120528.

    Article  Google Scholar 

  38. Yang X., Li M., Yin Z., et al., Effect of swirler vane angle on the combustion characteristics of premixed lean hydrogen-air mixture in a swirl micro-combustor. Chemical Engineering and Processing-Process Intensification, 2023, 183: 109238.

    Article  Google Scholar 

  39. Gao W., Yan Y., Huang L., et al., Numerical investigation on combustion characteristics of premixed hydrogen/air in a swirl micro combustor with twisted vanes. International Journal of Hydrogen Energy, 2021, 46(80): 40105–40119.

    Article  Google Scholar 

  40. Wu S., Laurent T.D.C., Abubakar S., et al., Thermal performance characteristics of a micro-combustor with swirl rib fueled with premixed hydrogen/air. International Journal of Hydrogen Energy, 2021, 46(73): 36503–36514.

    Article  Google Scholar 

  41. Benabed M., Computational optimization of Coanda effect on film-cooling performance. Journal of Thermophysics and Heat Transfer, 2015, 29(4): 757–765.

    Article  Google Scholar 

Download references

Acknowledgement

The authors acknowledge gratefully the financial support from the National Natural Science Foundation of China (Grant No. U2241268), the Natural Science Foundation of Hunan Province (Grant No. 2021JJ40646), the National Science and Technology Major Project (Grant No. J2019-III-0019-0063), and the Innovation Capacity Support Plan in Shaanxi Province of China (Grant No. 2023-CX-TD-19).

Author information

Authors and Affiliations

  1. School of Power and Energy, Northwestern Polytechnical University, Xi’an, 710072, China

    Xinyu Wang, Cunliang Liu & Huiren Zhu

  2. AECC Hunan Aviation Powerplant Research Institute, Zhuzhou, 412002, China

    Zhongyi Fu & Yang Li

Authors
  1. Xinyu Wang
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. Cunliang Liu
    View author publications

    You can also search for this author in PubMed Google Scholar

  3. Zhongyi Fu
    View author publications

    You can also search for this author in PubMed Google Scholar

  4. Yang Li
    View author publications

    You can also search for this author in PubMed Google Scholar

  5. Huiren Zhu
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to Cunliang Liu.

Ethics declarations

On behalf of all authors, the corresponding author states that there is no conflict of interest.

Rights and permissions

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Wang, X., Liu, C., Fu, Z. et al. Improvement of Film Cooling Design for Turbine Vane Leading Edge Considering Combustor Outflow. J. Therm. Sci. 33, 311–327 (2024). https://doi.org/10.1007/s11630-023-1878-8

Download citation

  • Received:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s11630-023-1878-8

Keywords

Search

Navigation