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Film cooling performance in a low speed 1.5-stage turbine: effects of mainstream Reynolds number and turbulence

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Abstract

The effects of mainstream Reynolds number and turbulence to film cooling performance were investigated experimentally and computationally under rotating conditions in a 1.5-stage turbine. The rotor of the turbine included 18 blades with chord of 124.3 mm and height of 99 mm. A film hole was set in the middle span of the rotor blade surface with injection angles of 28° on the pressure side and 36° on the suction side respectively. The Reynolds number based on the mainstream velocity of the turbine outlet and the chord length of the rotor blade varied from 1.9 × 105 to 2.1 × 105. Measurements were made at three different rotation speeds of 702, 737 and 800 rpm to keep the rotating number consistent at 0.0280 while the blowing ratio varied from 0.5 to 2.0. Air and CO2 worked as coolant to achieve the density ratio of 1.03 and 1.57, respectively. Computational investigation was performed using the hexahedral structured grids and k-ε turbulence model. Results showed that the film coverage and cooling effectiveness are enlarged while the film deflection is weakened as the mainstream Reynolds number increases. Furthermore, the mainstream turbulence plays a negative role in the film coverage and cooling effectiveness at lower blowing ratio on both the pressure side and suction side while it promotes the film reattachment at higher blowing ratio on the suction side.

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Abbreviations

C :

Chord length of the turbine blade (mm)

D :

The diameter of the film hole (mm)

DR :

Coolant-to-mainstream density ratio

H :

Blade height (mm)

L S :

The length of the film coverage in streamwise (mm)

L H :

The length of the film coverage in spanwise (mm)

M :

Blowing ratio, M = ρ c v c/ρ g v g

Re g :

Reynolds number, Re g = ρ out v out C r/μ

Rt :

Rotating number, Rt = ΩD/v g

S :

Surface distance from the film hole (mm)

T :

Temperature (K)

Tu g :

Turbulence

v :

Velocity (m/s)

ρ :

Density (kg/m3)

η :

Lateral-averaged adiabatic film cooling effectiveness, η = (T g − T aw)/(T g − T c)

κ :

Gradient of the film trajectory centerline

μ :

Dynamic viscosity of the mainstream (kg/m·s)

Ω :

Rotating speed (rpm)

aw:

Adiabatic

c:

Coolant

g:

Mainstream

out:

Outlet of the turbine

r:

Rotor blade

References

  1. Han JC, Dutta S, Ekkad S (2001) Gas turbine heat transfer and cooling technology (chapter 3). Taylor & Francis, New York, pp 87–163

    Google Scholar 

  2. Suryanarayanan A, Mhetras SP, Schobeiri MT, Han JC (2009) Film-cooling effectiveness on a rotating blade platform. J Turbomach 13(1):011014-1-12

    Google Scholar 

  3. Takeishi K, Aoki S, Sato T, Tsukagoshi K (1992) Film cooling on a gas turbine rotor blade. J Turbomach 114:828–834

    Article  Google Scholar 

  4. Tao Z, Li GQ, Deng HW, Xiao J, Xu GQ, Luo X (2011) Film cooling performance in a low speed 1.5-stage turbine: effects of blowing ratio and rotation. J Enhanc Heat Transf 18(5):419–432

    Article  Google Scholar 

  5. Li GQ, Zhu JQ, Deng HW, Tao Z, Li HW (2013) Experimental investigation of rotating film cooling performance in a low speed 1.5-stage turbine. Int J Heat Mass Transf 61:18–27

    Article  Google Scholar 

  6. Mehendale AB, Han JC (1993) Reynolds number effect on leading edge film effectiveness and heat transfer coefficient. Int J Heat Mass Transf 36(15):2723–2730

    Google Scholar 

  7. Li GQ, Deng HW (2011) Experimental investigation on film cooling performance of pressure side in annular cascades. J Therm Sci 20(2):119–126

    Article  Google Scholar 

  8. Ou S, Rivir RB (2001) Leading edge film cooling heat transfer with high free stream turbulence using a transient liquid crystal image method. Int J Heat Fluid Flow 22:614–623

    Article  Google Scholar 

  9. Choi JH, Teng SY, Han JC, Ladeinde F (2004) Effect of free-stream turbulence on turbine blade heat transfer and pressure coefficients in low Reynolds number flows. Int J Heat Mass Transf 47:3441–3452

    Article  Google Scholar 

  10. Mayhew JE, Baughn JW, Byerley AR (2003) The effect of freestream turbulence on film cooling adiabatic effectiveness. Int J Heat Fluid Flow 24:669–679

    Article  Google Scholar 

  11. Lebedev VP, Lemanov VV, Terekhov VI (2006) Film-cooling efficiency in a Laval Nozzle under conditions of high freestream turbulence. J Heat Transf 128:571–579

    Article  Google Scholar 

  12. Funazaki K, Kawabata H, Takahashi D, Okita Y (2012) Experimental and numerical studies on leading edge film cooling performance: effects of hole exit shape and freestream turbulence. ASME Paper, No. GT2012-68217

  13. Bons JP, MacArthur CD, Rivir RB (1994) The effect of high freestream turbulence on film cooling effectiveness. ASME Paper, No. 94-GT-51

  14. Schmidt DL, Bogard DG (1996) Effects of free-stream turbulence and surface roughness on film cooling. ASME Paper, No. 96-GT-462

  15. Hassan JS, Yavuzkurt S (2006) Comparison of four different two-equation models of turbulence in predicting film cooling performance. ASME Paper, No. GT2006-90860

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Acknowledgments

This work was supported by the National Natural Science Foundation of China (Grant No. 51106156).

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Authors and Affiliations

  1. Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing, 100190, China

    Guoqing Li, Junqiang Zhu & Kai Wang

  2. National Key Laboratory of Science and Technology on Aero-Engines, Beijing University of Aeronautics and Astronautics, Beijing, 100191, China

    Haiwang Li

  3. Research Institute of Petroleum Exploration and Development, Beijing, 100083, China

    Qian Zhang

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  1. Guoqing Li
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  2. Junqiang Zhu
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  3. Kai Wang
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Correspondence to Guoqing Li.

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Li, G., Zhu, J., Wang, K. et al. Film cooling performance in a low speed 1.5-stage turbine: effects of mainstream Reynolds number and turbulence. Heat Mass Transfer 51, 795–805 (2015). https://doi.org/10.1007/s00231-014-1446-6

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  • DOI: https://doi.org/10.1007/s00231-014-1446-6

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