Abstract
Abstract
This paper deals with the determination of the optimum amount of air mass flow needed to cool down the turbine blades of aircraft engines. The optimum mass flow is built up as a result of two opposite tendencies. As the specific cool air mass flow increases the admissible gas temperature in front of the turbines increases, which has a positive effect. On the other hand, there is an increase of the loss of the cool air mass flow that has been compressed and then drained and thus not doing a 100 per cent useful work any more; this increase of the losses is a negative effect. This paper shows that the optimum value of the cool air mass flow depends primarily on the ability to expand of the cool air flowing from the blades of the turbine and returning to the working process.
Keywords: gas turbine, turbine blades cooling, optimum cool air mass flow