Suscripción a Biblioteca: Guest
Portal Digitalde Biblioteca Digital eLibros Revistas Referencias y Libros de Ponencias Colecciones
Computational Thermal Sciences: An International Journal
ESCI SJR: 0.249 SNIP: 0.434 CiteScore™: 1.4

ISSN Imprimir: 1940-2503
ISSN En Línea: 1940-2554

Computational Thermal Sciences: An International Journal

DOI: 10.1615/ComputThermalScien.2017019230
pages 183-193

INFLUENCE OF LATERAL ANGLE ON FILM COOLING PERFORMANCE OVER ASYMMETRICAL TURBINE BLADE

Mustapha Benabed
Aeronautical Laboratory and Propulsive Systems, Faculte de Genie-Mecanique, Universite des Sciences et de la Technologie d'Oran, B.P. 1505 El-Mnouar, Oran, Algeria

SINOPSIS

A numerical investigation was performed to determine the effect of the lateral angle injection on film cooling effectiveness over a turbine blade. The rows are located in the vicinity of the stagnation line. One row is located on the suction side and the other one is on the pressure side. The predicted pressure field for various blowing ratios (M = 0.5, 1.1, and 1.5) is compared to available experimental results at the design condition. Moreover, the effect of three lateral angles 30, 45, and 60 deg at three blowing rates is investigated by analyzing the results of both laterally averaged and area-averaged values of adiabatic film cooling effectiveness. The outcomes of the numerical results indicate that the thermal protection of the blade can be strongly influenced by the lateral angle. The coolant structure flow is characterized by a dominant single asymmetric vortex on both sides. Lateral injection at angle γ = 60 deg significantly improves film cooling effectiveness. From γ = 30 to 45 deg, overall, no appreciable improvement could be noted in cooling performance except for the lower blowing ratio M = 0.5. At suction side, the increase of blowing ratio has an adverse effect on the blade thermal protection.


Articles with similar content:

FILM TEMPERATURE AND EFFECTIVENESS MEASUREMENTS ON A CYLINDRICAL LEADING EDGE FILM COOLING MODEL
International Heat Transfer Conference 11, Vol.18, 1998, issue
Shuye Teng, Je-Chin Han, Dong Kee Sohn
FILM COOLING FROM TWO ROWS OF HOLES WITH OPPOSITE ORIENTATION ANGLES: INJECTANT BEHAVIORS
Proceedings of Symposium on Energy Engineering in the 21st Century (SEE2000) Volume I-IV, Vol.0, 2000, issue
Joon Ahn, In Sung Jung, Joon Sik Lee
CONJUGATED HEAT TRANSFER ANALYSIS OF A FILM COOLING PASSAGE WITH TURBULATOR RIBS
Heat Transfer Research, Vol.47, 2016, issue 2
Han Wu, Bengt Sunden, Chunwei Gu, Jin Wang, Qiu-Wang Wang, Jian Yang
FILM COOLING PERFORMANCE IN A LOW-SPEED 1.5-STAGE TURBINE: EFFECTS OF BLOWING RATIO AND ROTATION
Journal of Enhanced Heat Transfer, Vol.18, 2011, issue 5
Guoqiang Xu, Jun Xiao , Guoqing Li , Xiang Luo , Zhi Tao, Hongwu Deng
NUMERICAL STUDY OF DROPLET-LADEN MIST FILM COOLING EFFECTIVENESS OF CYLINDRICAL HOLES EMBEDDED IN A TRANSVERSE TRENCHE
International Heat Transfer Conference 16, Vol.18, 2018, issue
Viktor I. Terekhov, Maksim A. Pakhomov