摘要：This study is part of research project concerning the development of High Pressure turbine blades with advanced cooling systems. Due to the high gas temperatures entering the turbine of the most recent aero-engines in general up to 2000 K at the turbine inlet at 40 bars, a very efficient cooling system is required in order to maintain the metal temperatures below the allowable limits. This means to use a certain amount of "cold" air directly extracted from the compressor, with a significant negative impact on the engine performance. A novel methodology has been used to design the layout of the tip cooling nozzles of a high pressure rotor blade turbine. The methodology used is through a complete CAE approach, by means of a parametric CFD model which is run many times for the exploration of several designs by an optimizer.
