Effect of Injection Angle on Performance of Full Coverage Film Cooling with Opposite Injection Holes
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Mukesh Prakash Mishra
Abstract
Characteristics of full coverage film cooling of an adiabatic flat plate are studied for opposite injection of coolant at different angles. Two in-line adjacent rows of cooling holes injecting in opposite directions are considered in this study. The cooling performance is compared with the configurations having forward and reverse injecting holes at similar injection angles. The holes are arranged in an array of 20 rows with equal spacing both span-wise and stream-wise. Computational analyses are carried out over a wide range of velocity ratios (VR) of practical importance ranging from 0.5 to 2.0 at density ratio of about 1.0. Injection angle and velocity ratio are found to have strong influence on film cooling effectiveness of opposite injection. At low velocity ratio of VR=0.5, film cooling performance of opposite injection at 45° is found better than at other angles, i. e. 30° and 60°. At higher velocity ratios, injection at 30° is found superior. Film cooling effectiveness becomes insensitive to velocity ratios at higher range for 45° and 60° injections. Evolution of effusion film layer and interaction between coolant and primary flow is also studied in this paper.
References
1. Cohen H, Rogers GF, Saravanamuttoo HI. Gas turbine theory, 5th ed. New Delhi: John Wiley & Sons, Dorling Kinderslay (India) Pvt Ltd, Licensees of Pearson Education in South Asia, 2001.Search in Google Scholar
2. Goldstein RJ. Film cooling. Adv heat transfer. 1971;7:321–79.10.1016/S0065-2717(08)70020-0Search in Google Scholar
3. Bogard DG. Airfoil Film Cooling. Gas Turbine Handb. National Energy Technology Laboratory. 2006;4:309–21.Search in Google Scholar
4. Bunker RS. A review of shaped hole turbine film-cooling technology. J Heat Transfer. 2005;127:441–53.10.1115/1.1860562Search in Google Scholar
5. Haven BA, Kurosaka M. Kidney and anti-kidney vortices in cross flow jets. J Fluid Mech. 1997;352:27–64.10.1017/S0022112097007271Search in Google Scholar
6. Goldstein RJ, Jin P. Film cooling downstream of a row of discrete holes with compound angle. In: ASME turbo expo 2000: power for land, sea, and air. Munich, Germany, Paper No. 2000-GT-0248, pp. V003 to 1A054; doi:10.1115/2000-GT-0248, published by American Society of Mechanical Engineers, 2000.Search in Google Scholar
7. Andrews GE, Gupta ML, Mkpadi MC. Full coverage discrete hole film cooling: cooling effectiveness. Int J Turbo Jet Engines. 1985;2:199–212.10.1515/TJJ.1985.2.3.199Search in Google Scholar
8. Andrews GE, Alikhanizadeh M, Tehrani FB, Hussain CI, Azari MK. Small diameter film cooling holes: the influence of hole size and pitch. Int J Turbo Jet Engines. 1988;5:61–72.10.1515/TJJ.1988.5.1-4.61Search in Google Scholar
9. Yuen CHN, Martinez-Botas RF. Film cooling characteristics of rows of round holes at various streamwise angles in a cross flow: part I. effectiveness. Int J Heat Mass Transf. 2005;48:4995–5016.10.1016/j.ijheatmasstransfer.2005.05.019Search in Google Scholar
10. Scrittore JJ, Thole KA, Burd SW. Investigation of velocity profiles for effusion cooling of a combustor liner. J Turbomach. 2007;129:518–26.10.1115/GT2006-90532Search in Google Scholar
11. Chengfeng Y, Jingzhou ZHANG. Influence of multi-hole arrangement on cooling film development. Chin J Aeronautics. 2012;25:182–88.10.1016/S1000-9361(11)60377-4Search in Google Scholar
12. Hasan R, Puthukkudi A. Numerical study of effusion cooling on an adiabatic flat plate. Propul Power Res. 2013;2:269–75.10.1016/j.jppr.2013.11.002Search in Google Scholar
13. Mukesh Prakash MA, Sahani K, Chandel S. Improved film cooling with hybrid arrangement of cooling holes. Recent Trends Fluid Mech. 2017;4:1–6.Search in Google Scholar
14. Oguntade HI, Andrews GE, Burns AD, Ingham DB, Pourkashanian M. Conjugate heat transfer predictions of effusion cooling: the influence of the coolant jet-flow direction on the cooling effectiveness. In: ASME turbo expo 2012: turbine technical conference and exposition. American Society of Mechanical Engineers, 2012. Paper No. GT2012-68517, pp. 1333–1343; doi:10.1115/GT2012-68517, Copenhagen, Denmark, June 11–15, 2012.Search in Google Scholar
15. Chen AF, Shiou-Jiuan L, Han J-C. Film cooling with forward and backward injection for cylindrical and fan-shaped holes using PSP measurement technique. In: ASME turbo expo 2014: turbine technical conference and exposition. American Society of Mechanical Engineers, 2014.10.1115/GT2014-26232Search in Google Scholar
16. Andrews GE, Khalifa IM, Asere AA, Bazdidi-Tehrani F. Full coverage effusion film cooling with inclined holes, ASME paper 95-GT-274. Proc. ASME IGTI International gas turbine congress. Houston, 1995.10.1115/95-GT-274Search in Google Scholar
17. Singh K, Premachandran B, Ravi MR Experimental and numerical studies on film cooling with reverse/backward coolant injection. Int J Thermal Sci. 2017;111:390–408.10.1016/j.ijthermalsci.2016.09.027Search in Google Scholar
18. Park S, Jung EY, Kim SH, Sohn HS, Cho HH. Enhancement of film cooling effectiveness using backward injection holes. Int J Thermal Sci. 2016;110:314–24.10.1115/GT2015-43853Search in Google Scholar
19. Tarchi L, Facchini B, Maiuolo F, Coutandin D. Experimental investigation on the effects of a large recirculating area on the performance of an effusion cooled combustor liner. J Eng Gas Turbines Power. 2012;134:041505–13.10.1115/1.4004729Search in Google Scholar
20. Versteeg HK, Malalasekera W. An introduction to computational fluid dynamics: the finite volume method. Pearson Education, London, UK, 2007.Search in Google Scholar
21. Sinha AK, Bogard DG, Crawford ME. Film-cooling effectiveness downstream of a single row of holes with variable density ratio. J Turbomach. 1991;113:442–49.10.1115/1.2927894Search in Google Scholar
22. El-Gabry LA, Heidmann JD. Numerical study on the sensitivity of film cooling CFD results to experimental and numerical uncertainties. Int J Comput Methods Eng Sci Mech. 2013;14:317–28.10.1080/15502287.2012.756953Search in Google Scholar
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Articles in the same Issue
- Frontmatter
- Effect of orifice spacing on twin circular parallel compressible jets
- Design and Experiment of Casing Treatment for a Centrifugal Compressor
- An Integrated Throughflow Method for the Performance Analysis of Variable Cycle Compression Systems
- Aerodynamic Performance Characteristics of NACA 0010 Cascade with Gurney Flaps
- Study on a Quasi-Two-Dimensional Fan Model for Variant Bypass-Ratio Condition
- Co-Flowing Jet Control Using Lip Thickness Variation
- Investigation on the Effect of Different Lands on Trailing Edge Slot Film Cooling
- Installation Characteristics of Variable Cycle Engine Based on Inlet Flow Matching
- Supersonic Jet Control by Tabs with Slanted Perforation
- Effect of Injection Angle on Performance of Full Coverage Film Cooling with Opposite Injection Holes
Articles in the same Issue
- Frontmatter
- Effect of orifice spacing on twin circular parallel compressible jets
- Design and Experiment of Casing Treatment for a Centrifugal Compressor
- An Integrated Throughflow Method for the Performance Analysis of Variable Cycle Compression Systems
- Aerodynamic Performance Characteristics of NACA 0010 Cascade with Gurney Flaps
- Study on a Quasi-Two-Dimensional Fan Model for Variant Bypass-Ratio Condition
- Co-Flowing Jet Control Using Lip Thickness Variation
- Investigation on the Effect of Different Lands on Trailing Edge Slot Film Cooling
- Installation Characteristics of Variable Cycle Engine Based on Inlet Flow Matching
- Supersonic Jet Control by Tabs with Slanted Perforation
- Effect of Injection Angle on Performance of Full Coverage Film Cooling with Opposite Injection Holes
