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Gas Turbine Blade Cooling

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Title: Gas Turbine Blade Cooling
Author: Chaitanya D. Ghodke
ISBN: 0768095026 / 9780768095029
Format: Soft Cover
Pages: 236
Publisher: SAE
Year: 2019
Availability: 15-30 days
  • Description
  • Contents

Gas turbines play an extremely important role in fulfilling a variety of power needs and are mainly used for power generation and propulsion applications. The performance and efficiency of gas turbine engines are to a large extent dependent on turbine rotor inlet temperatures: typically, the hotter the better.

In gas turbines, the combustion temperature and the fuel efficiency are limited by the heat transfer properties of the turbine blades.

However, in pushing the limits of hot gas temperatures while preventing the melting of blade components in high-pressure turbines, the use of effective cooling technologies is critical.

Increasing the turbine inlet temperature also increases heat transferred to the turbine blade, and it is possible that the operating temperature could reach far above permissible metal temperature. In such cases, insufficient cooling of turbine blades results in excessive thermal stress on the blades causing premature blade failure. This may bring hazards to the engine’s safe operation.

Gas Turbine Blade Cooling, edited by Dr. Chaitanya D. Ghodke, offers 10 handpicked SAE International’s technical papers, which identify key aspects of turbine blade cooling and help readers understand how this process can improve the performance of turbine hardware.


Chapter 1 : High Temperature Turbine Design Considerations
Chapter 2 : Summary of NASA Aerodynamic and Heat Transfer Studies in Turbine Vanes and Blades
Chapter 3 : Cooling Modern Aero Engine Turbine Blades and Vanes
Chapter 4 : An Investigation of Convective Cooling of Gas Turbine Blades Using Intermittent Cooling Air
Chapter 5 : The Prospects of Liquid Cooling for Turbines
Chapter 6 : Feasibility Demonstration of a Small Fluid-Cooled Turbine at 2300°F
Chapter 7 : Design and Fabrication Aspects of Transpiration Air-Cooled Turbine Blades for 2500°F Turbine Operation
Chapter 8 : Design and Test of a Small Turbine at 2500°F with Transpiration-Cooled Blading
Chapter 9 : The Role of the Turbulent Prandtl Number in Turbine Blade Heat Transfer Prediction
Chapter 10 : Parametric Analysis of Aero-Derivative Gas Turbine: Effect of Radiative Heat Transfer on Blade Coolant Requirement

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