The performance goal of modern gas turbine engines, both land-base and air-breathing engines, can be achieved by increasing the turbine inlet temperature (TIT). The level of TIT in the near future can reach as high as 1700 °C for utility turbines and over 1900 °C for advanced military engines. Advanced and innovative cooling techniques become one of the crucial major elements supporting the development of modern gas turbines, both land-based and air-breathing engines with continual increment of turbine inlet temperature (TIT) in order to meet higher energy demand and efficiency. This paper discusses state-of-the-art airfoil cooling techniques that are mainly applicable in the mainbody and trailing edge section of turbine airfoil. Potential internal cooling designs for near-term applications based on current manufacturing capabilities are identified. A literature survey focusing primarily on the past four to five years has also been performed.
Recent Advances of Internal Cooling Techniques for Gas Turbine Airfoils
Manuscript received November 5, 2012; final manuscript received February 5, 2013; published online May 17, 2013. Assoc. Editor: Srinath V. Ekkad.
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Chyu, M. K., and Siw, S. C. (May 17, 2013). "Recent Advances of Internal Cooling Techniques for Gas Turbine Airfoils." ASME. J. Thermal Sci. Eng. Appl. June 2013; 5(2): 021008. https://doi.org/10.1115/1.4023829
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