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Influence of coolant injector configuration on film cooling effectiveness for gaseous and liquid film coolants

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Abstract

An experimental investigation is conducted to bring out the effects of coolant injector configuration on film cooling effectiveness, film cooled length and film uniformity associated with gaseous and liquid coolants. A series of measurements are performed using hot air as the core gas and gaseous nitrogen and water as the film coolants in a cylindrical test section simulating a thrust chamber. Straight and compound angle injection at two different configurations of 30°–10° and 45°–10° are investigated for the gaseous coolant. Tangential injection at 30° and compound angle injection at 30°–10° are examined for the liquid coolant. The analysis is based on measurements of the film-cooling effectiveness and film uniformity downstream of the injection location at different blowing ratios. Measured results showed that compound angle configuration leads to lower far-field effectiveness and shorter film length compared to tangential injection in the case of liquid film cooling. For similar injector configurations, effectiveness along the stream wise direction showed flat characteristics initially for the liquid coolant, while it was continuously dropping for the gaseous coolant. For liquid coolant, deviations in temperature around the circumference are very low near the injection point, but increases to higher values for regions away from the coolant injection locations. The study brings out the existance of an optimum gaseous film coolant injector configuration for which the effectiveness is maximum.

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Abbreviations

D:

Pipe diameter (m)

I:

Momentum flux ratio between the coolant and mainstream

M:

Blowing ratio

Pinj :

Coolant injection pressure (bar)

Tg :

Core gas temperature (K)

x:

Axial distance from the coolant injection point (m)

α:

Azimuthal injection angle (°)

β:

Tangential injection angle (°)

\( \bar{\eta } \) :

Circumferentially averaged effectiveness

\( \bar{\bar{\eta }} \) :

Spatially averaged effectiveness

References

  1. Goldstein RJ, Rask RB, Eckert ERG (1966) Film cooling with helium injection into an incompressible air flow. Int J Heat Mass Transf 9:1341–1350

    Article  Google Scholar 

  2. Ligrani PM, Wigle J, Ciriello S, Jackson SW (1994) Film cooling from holes with compound angle orientations: Part 1. Results downstream of two staggered rows of holes with 3d span wise spacing. ASME J Heat Transf 116:341–352

    Article  Google Scholar 

  3. Sen B, Schmidt DL, Bogard DG (1996) Film cooling with compound angle holes: heat transfer. ASME J. Turbomech 118:801–807

    Google Scholar 

  4. Schmidt DL, Sen B, Bogard DG (1996) Film cooling with compound angle holes: adiabatic effectiveness. ASME J Turbomech 118:807–813

    Article  Google Scholar 

  5. Ekkad SV, Zapata D, Han JC (1997) Heat transfer coefficients over a flat surface with air and CO2 injection through compound angle holes using transient liquid crystal image method. ASME J. Turbomech 119:580–587

    Article  Google Scholar 

  6. Lee HW, Park JJ, Lee JS (2002) Flow visualization and film cooling effectiveness measurements around shaped holes with compound angle orientations. Int J Heat Mass Transf 45:142–156

    Google Scholar 

  7. McGrath EL, Leylek JH (1998) Physics of hot flow ingestion in film cooling. ASME Paper No. 98-GT-191

  8. Baheri S, Tabrizi SPA, Jubran BA (2008) Film cooling effectiveness from trenched shaped and compound holes. Heat Mass Transf 44:989–998

    Article  Google Scholar 

  9. Nasir H, Srinath SV, Acharya S (2001) Effect of compound angle injection on flat surface film cooling with large stream wise injection angle. Exp Therm Fluid Sci 25:23–29

    Article  Google Scholar 

  10. Cho HH, Rhee DH, Kim BG (1999) Film cooling effectiveness and heat/mass transfer coefficient measurement around a conical-shaped hole with a compound angle injection. ASME Paper No. 99-GT-38

  11. Bell CM, Hamakawa H, Ligrani PM (2000) Film cooling from shaped holes. ASME J Heat Transf 122:224–232

    Article  Google Scholar 

  12. Brittingham RA, Leylek JH (2000) A detailed analysis of film cooling physics: Part iv-compound-angle injection with shaped holes. ASME J Turbomach 122:133–145

    Article  Google Scholar 

  13. Maiteh BY, Jubran B (1999) Effect of compound angle injection on flat surface film cooling with large stream wise injection angle. Int J Heat Fluid flow 20:158–165

    Article  Google Scholar 

  14. Jubran BA, Al-Hamadi AK, Theodoridis G (1997) Film cooling and heat transfer with air injection through two sets of compound angle holes. Heat Mass Transf 33:93–100

    Article  Google Scholar 

  15. Dittmar J, Schulz A, Wittig S (2003) Assessment of various film-cooling configurations including shaped and compound angle holes based on large-scale experiments. ASME J Turbomach 125:57–64

    Article  Google Scholar 

  16. Taslim ME, Khanicheh A (2005) Film effectiveness downstream of a row of compound angle film holes. ASME J Heat Transf 127:434–440

    Article  Google Scholar 

  17. Hung M, Ding P, Chen P (2009) Effects of injection angle orientation on concave and convex surfaces film cooling. Exp Therm Fluid Sci 33:292–305

    Article  Google Scholar 

  18. Michel B, Gajan P, Strzelecki A, Savary N, Kourta A, Boisson H (2009) Full coverage film cooling using compound angle. C R Mecanique 337:562–572

    Article  Google Scholar 

  19. Sivrioglu M (1991) An analysis of the effects of pressure gradient and streamline curvature on film cooling effectiveness. Heat Mass Transf 26:103–107

    Google Scholar 

  20. Boden RH (1951) Heat transfer in rocket motors and application of film and sweat cooling. ASME Trans 73:385–390

    Google Scholar 

  21. Welsh JWE (1961) Review of results of an early rocket engine film-cooling investigation at the Jet Propulsion laboratory. Technical Report TM-32-58, Jet Propusion Center, California Institute of Technology

  22. Morrell G (1951) Investigation of internal film cooling of a 1000-pound thrust liquid ammonia liquid oxygen rocket. Technical Report, NACA RME51E04

  23. Kinney GR, Abramson AE, Sloop JL (1952) Internal film cooling experiments with 2 and 4 inch smooth surface tubes and gas temperatures to 2000- F in 2 and 4 inch diameter horizontal tubes. Technical Report, NACA report 1087

  24. Abramson AE (1952) Investigation of internal film cooling of exhaust nozzle of a 1000-pound thrust liquid ammonia-liquid oxygen rocket. Technical Report, NACA RME52C26

  25. Knuth EL (1954) The mechanism of film cooling. Dissertation, California Institute of Technology

  26. Warner CF, Emmons DL (1964) Effects of selected gas stream parameters and coolant properties on liquid film cooling. Trans ASME J Heat Transf 1:271–278

    Article  Google Scholar 

  27. Stechman RC, Oberstone J, Howell JC (1969) Design criteria for film cooling for small liquid-propellant rocket engines. J Spacecr Rockets 6:97–102

    Article  Google Scholar 

  28. Kesselring RC, Knight RM, McFarland BL, Gurnitz RN (1972) Boundary cooled rocket engines for space storable proplellants. Technical Report, Rocketdyne Report No. R-8766

  29. Moffat RJ (1985) Describing the uncertainties in experimental results. Exp Therm Fluid Sci 1:3–17

    Article  Google Scholar 

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Authors and Affiliations

  1. Department of Aerospace Engineering, Indian Institute of Space Science and Technology, Thiruvananthapuram, 695547, India

    S. R. Shine

  2. Liquid Propulsion Systems Centre, Indian Space Research Organization, Thiruvananthapuram, 695547, India

    S. Sunil Kumar

  3. Indian Space Research Organisation, ISRO Hqs, Bangalore, 560231, India

    B. N. Suresh

Authors
  1. S. R. Shine
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  2. S. Sunil Kumar
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  3. B. N. Suresh
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Correspondence to S. R. Shine.

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Shine, S.R., Sunil Kumar, S. & Suresh, B.N. Influence of coolant injector configuration on film cooling effectiveness for gaseous and liquid film coolants. Heat Mass Transfer 48, 849–861 (2012). https://doi.org/10.1007/s00231-011-0936-z

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  • DOI: https://doi.org/10.1007/s00231-011-0936-z

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