Detailed Film Cooling Measurements over a Gas Turbine Blade Using a Transient Liquid Crystal Image Technique

Abstract

Detailed heat transfer coefficient and film effectiveness distributions over a gas turbine blade with film cooling are obtained using a transient liquid crystal image technique. The test blade has three rows of film holes on the leading edge and two rows each on the pressure and suction sur- for CO2 injection. Results show that film injection promotes earlier laminar-turbulent boundary layer transition on the suction surface and also enhances local heat transfer coefficients (up to 80%) downstream of injection. An increase in coolant blowing ratio produces higher heat transfer coefficients for both coolants. This effect is stronger immediately downstream of injection holes. Film effectiveness is highest at a blowing ratio of 0.8 for air injection and at a blowing ratio of 1.2 for CO2 injection. Such detailed results will help provide insight into the film cooling phenomena on a gas turbine blade.

Analytical and Numerical Results for the Diffusion-Reaction Equation When the Reaction Coefficient Depends on Simultaneously the Space and Time Coordinates

“…In the most prevalent case of computers, when the temperature of the CPU (central processing unit) exceeds the safe operating limits [9], a mechanism will be activated to cool it, usually by a heat pipe [10]. Utilizing heat-pipe-cooled micro-reactors presents a promising option for decentralized, remote electricity supply and space power technology due to their exceptional inherent safety and minimal maintenance requirements [11].…”