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Film Cooling of Turbine Blade Surface With Extended Exit Holes

[+] Author Affiliations
Fariborz Forghan, Omid Askari, Uichiro Narusawa, Hameed Metghalchi

Northeastern University, Boston, MA

Paper No. ES2014-6527, pp. V001T01A005; 7 pages
  • ASME 2014 8th International Conference on Energy Sustainability collocated with the ASME 2014 12th International Conference on Fuel Cell Science, Engineering and Technology
  • Volume 1: Combined Energy Cycles, CHP, CCHP, and Smart Grids; Concentrating Solar Power, Solar Thermochemistry and Thermal Energy Storage; Geothermal, Ocean, and Emerging Energy Technologies; Hydrogen Energy Technologies; Low/Zero Emission Power Plants and Carbon Sequestration; Photovoltaics; Wind Energy Systems and Technologies
  • Boston, Massachusetts, USA, June 30–July 2, 2014
  • Conference Sponsors: Advanced Energy Systems Division
  • ISBN: 978-0-7918-4586-8
  • Copyright © 2014 by ASME


The main goal of gas turbine design is the effective use of energy. Usually, the efficient high temperature first and second stage turbine blade surface is cooled by jet of coolant flow from extended exit holes (EEH). Against the prevailing hot gas flow, the flow through EEH must be designed to form a film of cool air over the blade. Computational analyses are performed to examine the cooling effectiveness of flow from EEH over the suction side of a blade by solving conservation equations (mass, momentum and energy) and the ideal gas equation of state for the three-dimensional, turbulent, compressible flow. A diverging flow through EEH is typically choked at its throat, resulting in a supersonic flow, a shock and then a subsonic flow downstream. The location of the shock relative to the high-temperature gas flow over the blade determines the temperature distribution along the blade surface; which is analyzed in detail when the coolant flow rate is varied.

Copyright © 2014 by ASME



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