Gas Turbine Heat Transfer and Cooling Technology Conference Paper uri icon

abstract

  • Gas turbines are extensively used for aircraft propulsion, land-based power generation, and industrial applications. Thermal efficiency and power output of gas turbines increase with increasing turbine rotor inlet temperature. The current rotor inlet temperature level in advanced gas turbines is far above the melting point of the blade material. Therefore, along with high temperature material development, a sophisticated cooling scheme must be developed for continuous safe operation of gas turbines with high performance. Modern development in turbine-cooling technology plays a critical role in increasing the thermal efficiency and power output of advanced gas turbines. Gas turbine blades are cooled internally and externally. Internal cooling is achieved by passing the coolant through several rib-enhanced serpentine passages inside the blade to remove the heat conducted from the outside surface of the blade. For the external cooling or so-called film cooling, relatively cooled air is injected from the blade internal coolant passages to the blade surface to form a protective layer between the blade surface and hot gas streams. In the past number of years there has been considerable progress in gas turbine heat transfer and cooling technology research and this paper is limited to reviewing a few selected publications to reflect recent developments in turbine blade cooling.

author list (cited authors)

  • Han, J., Dutta, S., & Ekkad, S.

complete list of authors

  • Han, Je-Chin||Dutta, Sandip||Ekkad, Srinath

publication date

  • December 2001