Read more
Turbine Cooling and Aerodynamics examines the current state-of-the-art turbine cooling technologies and provides the reader with an understanding of the fundamental scientific issues pertinent to the cooling technology in addition to the factors relevant to the engineering design.
In order to achieve greater thrust/power and greater efficiency of high turbine engines, higher turbine inlet temperatures are desired without a significant penalty on the coolant usage and aerodynamic losses.. Modern turbine engines typically operate at turbine inlet temperatures in the 2550-3000 deg F which is above the material limits of the nickel alloy airfoil materials. Therefore the airfoils used in turbine engines have to be actively cooled using a fraction (15-20%) of the process air. The use of process air for cooling represents a loss of efficiency. It is therefore desired to minimize coolant air usage and maximize turbine inlet temperatures. These conflicting requirements have resulted in a wealth of strategies for turbine cooling aimed at maximizing cooling with minimal impact on aerodynamic efficiency. The science and engineering of turbine cooling and aerodynamics is reviewed in this monograph.
List of contents
Introduction to Gas Turbine Fundamentals & Technology.- Introduction to Turbine Cooling and Design.- Internal Cooling and Rotational Effects.- Film Cooling and Aerodynamics.- Tip Cooling and Leakage.- End Wall Cooling and Passage Aerodynamics.
About the author
Sumanta Acharya, Louisiana State University, Acharya@tigers.LSU.edu
