Skip to content
Licensed Unlicensed Requires Authentication Published by De Gruyter June 2, 2016

Investigation on the Film Cooling Performance of Diffuser Shaped Holes with Different Inclination Angles

  • Ying-Ni Zhai , Cun-Liang Liu EMAIL logo , Yi-Hong He and Zhi-Xiang Zhou

Abstract

Film cooling performances of laidback hole and laidback fan-shaped hole have been investigated using transient liquid crystal measurement technique. For film cooling of laidback hole, the increase of inclination angle reduces the film cooling effectiveness under small blowing ratio, while produces better film coverage and higher film cooling effectiveness under larger blowing ratios. Heat transfer coefficient is higher in the upstream region of laidback hole film cooling with large inclination angle, while laidback hole with small inclination angle has relatively higher heat transfer coefficient in the downstream region. The increase of inclination angle reduces the film cooling effectiveness and heat transfer coefficient of laidback fan-shaped hole film cooling, especially in the upstream region. Increase of inclination angle is beneficial to the thermal protection of laidback hole film cooling under large blowing ratio. Film hole with large inclination angle has larger discharge coefficient due to smaller aerodynamic loss in the hole.


Correction Note

Correction added after online publication June 2, 2016: The funding information was updated after ahead of print publication. “Natural Science Basic Research Plan in Shaanxi Province of China (Grant No. 2016JQ5056)” was supplied.


Funding statement: The authors acknowledge gratefully the financial support from Natural Science Basic Research Plan in Shaanxi Province of China (Grant No. 2016JQ5056), National Natural Science Foundation of China (Grant No. 51306152), Aeronautical Science Foundation of China (Grant No. 2014ZB53023), and Fok Ying Tung Education Foundation of China (Grant No. 141053).

Nomenclature

a

square root of thermal diffusivity

c

specific heat, [J/kgK]

Cd

discharge coefficient

D

film hole inlet diameter, [m]

h

heat transfer coefficient, [W/m2K]

M

momentum flux ratio (=ρcUc/ρgUg)

p

pressure, [Pa]

q

specific heat flux, [W/m2]

ReD

Reynolds number (=ρgUgD/μg)

t

time, [s]

T

temperature, [K]

U

velocity, [m/s]

X

streamwise coordinate, [m]

Y

spanwise coordinate, [m]

Z

normal coordinate, [m]

Greek symbols
α

inclination angle, []

η

film cooling effectiveness

ρ

density, [kg/m3]

μ

molecular viscosity, [Ns/m2]

λ

thermal conductivity, [W/mK]

Subscripts
aw

adiabatic wall

c

film ejection

g

mainstream

i

initial t=0

s

surface

w

wall

0

without film ejection

Abbreviation
LBH

Laid-back hole

LBFH

Laid-back fan-shaped hole

References

1. Bunker RS. A review of shaped hole turbine film cooling technology. ASME J Heat Transfer 2005;127:441–53.10.1115/1.1860562Search in Google Scholar

2. Goldstein RJ, Eckert ER, Burggraf F. Effects of hole geometry and density on three-dimensional film cooling. Int J Heat Mass Transfer 1974;17:595–607.10.1016/0017-9310(74)90007-6Search in Google Scholar

3. Thole K, Gritsch M, Schulz A, Witting S. Flowfield measurements for film cooling holes with expanded exits. ASME J Turbomach 1998;120:327–36.10.1115/96-GT-174Search in Google Scholar

4. Haven BA, Yamagata DK, Kurosaka M, Yamawaki S, Maya T. Anti-kidney pair of vortices in shaped holes and their influence on film cooling effectiveness. ASME Paper 97-GT-45, 1997.10.1115/97-GT-045Search in Google Scholar

5. Gritsch M, Schulz A, Witting S. Adiabatic wall effectiveness measurements of film cooling holes with expanded exits. ASME J Turbomach 1998;120:549–56.10.1115/97-GT-164Search in Google Scholar

6. Gritsch M, Schulz A, Witting S. Heat transfer coefficients measurements of film cooling holes with expanded exits. ASME Paper No. 98-GT-28, 1998.10.1115/98-GT-028Search in Google Scholar

7. Guo SM, Lai CC, Jones TV, Oldfield ML, Lock GD, Rawlinson AJ. The application of thin-film technology to measure turbine-vane heat transfer and effectiveness in a film-cooled, engine-simulated environment. Int J Heat Fluid Flow 1998;19:594–600.10.1016/S0142-727X(98)10034-6Search in Google Scholar

8. Zhang L, Baltz M, Pudupatty R, Fox M. Turbine nozzle film-cooling study using the pressure sensitive paint technique. ASME Paper 99-GT-196, 1999.10.1115/99-GT-196Search in Google Scholar

9. Zhang L, Pudupatty R. The effects of injection angle and hole exit shape on turbine nozzle pressure side film-cooling. ASME Paper 2000-GT-247, 2000.10.1115/2000-GT-0247Search in Google Scholar

10. Teng S, Han JC, Poinsatte PE. Effect of film-hole shape on turbine-blade film-cooling performance. AIAA J Thermophys Heat Transfer 2001;15:257–65.10.2514/2.6621Search in Google Scholar

11. Dittmar J, Schulz A, Wittig S, Effectiveness A. Heat transfer coefficient of shaped film-cooling holes on a scaled guide vane pressure side model. Int J Rotating Mach 2004;10:345–54.10.1155/S1023621X04000351Search in Google Scholar

12. Gao ZH, Narzary DP, Han JC. Film cooling on a gas turbine blade pressure side or suction side with axial shaped holes. Int J Heat Mass Transfer 2008;51:2139–52.10.1016/j.ijheatmasstransfer.2007.11.010Search in Google Scholar

13. Sargison JE, Guo SM, Oldfield ML, Lock GD. A converging slot hole film-cooling geometry—part 1: low-speed flat-plate heat transfer and loss. ASME J Turbomach 2002;124:453–60.10.1115/2001-GT-0126Search in Google Scholar

14. Liu CL, Zhu HR, Bai JT, et al. Experimental and numerical investigation on the film cooling of waist-shaped slot holes comparing with converging slot holes. ASME J Turbomach 2012;134:011021.10.1115/1.4003074Search in Google Scholar

15. Liu JS, Malak MF, Tapia LA, et al. Enhanced film cooling effectiveness with new shaped holes. ASME Paper GT-2010-22774, 2010.10.1115/GT2010-22774Search in Google Scholar

16. Kusterer K, Tekin N, Sugimoto T, Kazari M, Tanaka R, Bohn D. Experimental and numerical investigations of the NEKOMIMI film cooling technology. ASME Paper GT2012-68400, 2012.10.1115/GT2012-68400Search in Google Scholar

17. Khajehhasani S, Jubran B. Film cooling from novel sister shaped single-holes. ASME Paper GT2014-25971, 2014.10.1115/GT2014-25971Search in Google Scholar

18. Kohli A, Bogard D. Effects of hole shape on film cooling with large angle injection. ASME Paper 99-GT-165, 1999.10.1115/99-GT-165Search in Google Scholar

19. Baldauf S, Scheurlen M, Schulz A, Wittig S. Correlation of film-cooling effectiveness from thermographic measurements at engine like conditions. ASME J Turbomach 2002;124:686–98.10.1115/GT2002-30180Search in Google Scholar

20. Yuen CH, Martinez-Botas RF. Film cooling characteristics of a single hole at various streamwise angles: part I. Effectiveness. Int J Heat Mass Transfer 2003;46:221–35.10.1016/S0017-9310(02)00274-0Search in Google Scholar

21. Yuen CH, Martinez-Botas RF. Film cooling characteristics of a single hole at various streamwise angles: part II. Heat transfer coefficient. Int J Heat Mass Transfer 2003;46:237–49.10.1016/S0017-9310(02)00273-9Search in Google Scholar

22. Yuen CH, Martinez-Botas RF. Film cooling characteristics of rows of round holes at various streamwise angles in a crossflow: part I. Effectiveness. Int J Heat Mass Transfer 2005;48:4995–5016.10.1016/j.ijheatmasstransfer.2005.05.019Search in Google Scholar

23. Yuen CH, Martinez-Botas RF. Film cooling characteristics of rows of round holes at various streamwise angles in a crossflow: part II. Heat transfer coefficient. Int J Heat Mass Transfer 2005;48:5017–35.10.1016/j.ijheatmasstransfer.2005.05.020Search in Google Scholar

24. Bell CM, Hamakawa H, Ligrani PM. Film cooling from shaped holes. ASME J Heat Transfer 2000;122:224–32.10.1115/1.521484Search in Google Scholar

25. Gritsch M, Colban W, Schar H. Effect of hole geometry on the thermal performance of fan-shaped film cooling holes. ASME J Turbomach 2005;127:718–25.10.1115/1.2019315Search in Google Scholar

26. Saumweber C, Schulz A. Effect of geometry variations on the cooling performance of fan-shaped cooling holes. ASME Paper GT2008-51038, 2008.10.1115/GT2008-51038Search in Google Scholar

27. Bunker RS. Gas turbine film cooling: breaking the limits of diffusion shaped holes. Heat Transfer Res 2010;41:627–50.10.1615/HeatTransRes.v41.i6.40Search in Google Scholar

28. Vedula RJ, Metzger DE. A method for the simultaneous determination of local effectiveness and heat transfer distributions in three temperature convection situations. ASME paper No. 91-GT–345.Search in Google Scholar

29. Drost U, Bolcs A, Hoffs A. Utilization of the transient liquid crystal technique for film cooling effectiveness and heat transfer investigations on a flat plane and a turbine airfoil. ASME Paper No. 97-GT–026.Search in Google Scholar

30. Liu CL, Zhu HR, Bai JT, Zhang ZW, Zhang X. Investigation on the influence of nonuniform initial temperature on the transient heat transfer measurement of film cooling. Exp Therm Fluid Sci 2011;35:1151–61.10.1016/j.expthermflusci.2011.01.021Search in Google Scholar

31. Vedula RJ, Metzger DE, Bickford WB. Effects of lateral and anisotropic conduction on determination of local convection heat transfer characteristics with transient tests and surface coatings. Winter Annual Meeting of ASME, 1988, HTD-I, 21–7.Search in Google Scholar

32. Kline SJ, McClintock FA. Describing uncertainties in single-sample experiments. J Mech Eng 1953;75:3–8.Search in Google Scholar

33. Sen B, Schmidt DL, Bogard DG. Film cooling with compound angle holes: heat transfer. ASME J Turbomach 1996;118:800–6.10.1115/94-GT-311Search in Google Scholar

34. Yu Y, Yen C-H, Shih TI, Chyu MK, Gogineni S. Film cooling effectiveness and heat transfer coefficient distributions around diffusion shaped holes. ASME J Heat Transfer 2002;124:820–7.10.1115/99-GT-034Search in Google Scholar

Received: 2016-4-21
Accepted: 2016-5-18
Published Online: 2016-6-2
Published in Print: 2017-5-1

© 2017 Walter de Gruyter GmbH, Berlin/Boston

Downloaded on 28.4.2024 from https://www.degruyter.com/document/doi/10.1515/tjj-2016-0026/html
Scroll to top button