Investigation of measures improvement of turbine constructive element gas turbine engine cooling for middle range aircrafts

Abstract

Advanced heat transfer and cooling techniques form one of the major pillars supporting the continuing development of high efficiency, high power output gas turbine engines. Conventional gas turbine thermal management technology is composed of five main elements including internal convective cooling, external surface fi lm cooling, materials selection, thermal-mechanical design at the component and system levels, and selection and/or pre-treatment of the coolant fluid. The technology of cooling gas turbine components, primarily via internal convective flows of single-phase gases and external surface fi lm cooling with air, has developed over the years into very complex geometries involving many differing surfaces, architectures, and fluid-surface interactions. The fundamental aim of this technology area is to obtain the highest overall cooling effectiveness with the lowest possible penalty on the thermodynamic cycle performance. As a thermodynamic Brayton cycle, the efficiency of the gas turbine engine can be raised substantially by increasing the fi ring temperature of the turbine. Modern gas turbine systems are fired at temperatures far in excess of the material melting temperature limits.