Investigating Cooling Effect with Compound Angle on the Combustion Chamber Wall Temperature

ADMT Journal

مقاله 7، دوره 11، شماره 3، آذر 2018، صفحه 63-73   

نوع مقاله: Original Article

نویسندگان

Mohamad Reza Nazari¹؛ Behrooz Shahriari^{* 2}؛ Farhad Sebghatollahi²

¹Department of Mechanical and Aerospace Engineering, Malek Ashtar University of Technology, shiraz, Iran

²Department of Mechanical and Aerospace Engineering, Malek Ashtar University of Technology, 84145-115, Isfahan, Iran.

چکیده

Increasing the temperature of the turbine entrance gases increases the efficiency of the gas turbine cycle. Under these conditions, the combustion chamber wall temperature also increases, while there is no high temperature resistance alloy fitted with air motors. Therefore, it is necessary to use cooling methods to reduce the wall temperature. In this study, the cooling effect with compound angles investigated on the combustion chamber wall temperature. The three-dimensional combustion chamber k-ɛ is modelled under the conditions of the input speed and the turbulence model in the ANSYS Fluent software. Inlet air is injected from the cooled holes to the mainstream with compound angle, where the cooling flow angle is constant with the 30° horizontally, and the lateral angle changes from Beta =0 up to Beta=60 degrees. The combustion chamber has two flat planes and two sloping plates, in which the arrangement of cooling holes is different. The results show that this method better distributes the cooling air on the wall surface and covers the space between the cooling holes, especially on flat plates. With this method, the number of cooling holes and the amount of air used to cooling can be reduced. 

کلیدواژه‌ها

Combustion Chamber؛ Compound Angle؛ Film Cooling؛ Wall Temperature

مراجع

[1]    Lefebvre, Arthur, H., Gas Turbine Combustion, 3rd ed. CRC press, New York, 2010.

[2]    Atul, K., Bogard, D. G., Adiabatic Effectiveness, Thermal Fields, and Velocity Fields for Film Cooling with Large Angle Injection, Journal of Turbomachinery, Vol. 119, No. 2, 1997, pp. 352-358.

[3]    Foster, N. W., Lampard, D., The Flow and Film Cooling Effectiveness Following Injection through a Row of Holes, Journal of Engineering for Power, Vol. 102, No. 3, 1980, pp. 584-588.

[4]    Xiao, L., Zheng, H., Influence of Deflection Hole Angle on Effusion Cooling in a Real Combustion Chamber Condition, Thermal Science, Vol. 19, No. 2, 2015, pp. 645-656.

[5]    Koc, I., Parmaksızoglu, C., and Cakan, M., Numerical Investigation of Film Cooling Effectiveness on the Curved Surface, Energy Conversion and Management, Vol. 47, No. 9-10, 2006, pp. 1231-1246.

[6]    Goldstein, R. J., Jin, P., Film Cooling Downstream of a Row of Discrete Holes with Compound Angle, Journal of Turbomachinery, Vol. 123 No. 2, 2001, pp. 222-230.

[7]    Gustafsson, K. M., Johansson, T. G., An Experimental Study of Surface Temperature Distribution on Effusion-Cooled Plates, Journal of Engineering for Gas Turbines and Power, Vol. 123, No. 2, 2001, pp. 308-316.

[8]    Hay, N., Lampard, D., and Saluja, C. L., Effects of Cooling Films on the Heat Transfer Coefficient on a Flat Plate with Zero Mainstream Pressure Gradient, Journal of Engineering for Gas Turbines and Power, Vol. 107, No. 1, 1985, pp. 105-110.

[9]    Ammari, H. D., Hay, N., and Lampard, D., The Effect of Density Ratio on the Heat Transfer Coefficient from a Film-Cooled Flat Plate, Journal of Turbomachinery, Vol. 112, No. 3, 1990, pp. 444-450.

[10] Hale, C. A., Plesniak, M. W., and Ramadhyani, S., Film Cooling Effectiveness for Short Film Cooling Holes Fed by a Narrow Plenum, Journal of Turbomachinery, Vol. 122, No. 3, 2000, pp. 553-557.

[11] Maiteh, B. Y., Jubran, B. A., Effect of Pressure Gradient on Film Cooling Effectiveness from Two Rows of Simple and Compound angle holes in combination, Energy Conversion and Management, Vol. 45, No. 9-10, 2004, pp. 1457-1469.

[12] Jubran, B., Brown, A., Film Cooling from Two Rows of Holes Inclined in the Streamwise and Spanwise Directions, Journal of Engineering for Gas Turbines and Power, Vol. 107, No. 1 1985, pp. 84-91.

[13] Ligrani, P. M., Wigle, J. M., Ciriello, S., and Jackson, S. M., Film-Cooling from Holes with Compound Angle Orientations: Part 1-Results Downstream of Two Staggered Rows of Holes with 3d Spanwise Spacing, Journal of Heat Transfer, Vol. 116, No. 2, 1994, pp. 341-352.

[14] Schmidt, D. L., Sen, B., and Bogard, D. G., Film Cooling with Compound Angle Holes: Adiabatic Effectiveness, Journal of Turbomachinery, Vol. 118, No. 4 1996, pp. 807-813.

[15] Baldauf, S. A., Scheurlen, M., Schulz, A., and Wittig, S., Correlation of Film Cooling Effectiveness from Thermographic Measurements at Engine Like Conditions, ASME Turbo Expo 2002: Power for Land, Sea, and Air, pp. 149-162. American Society of Mechanical Engineers, 2002.

[16] Vakil, Suresh, S., and Thole, K. A., Flow and Thermal Field Measurements in a Combustor Simulator Relevant to a Gas Turbine Aero-Engine”, ASME Turbo Expo 2003, Collocated with the 2003 International Joint Power Generation Conference, American Society of Mechanical Engineers, 2003, pp. 215-224.

[17] E. Kianpour, Nor Azwadi, E., Sidik, C. S., and Agha Seyyed Mirza Bozorg, M., Thermodynamic Analysis of Flow Field at the end of Combustor Simulator, International Journal of Heat and Mass Transfer, Vol. 61, 2013, 389-396.