Thermodynamic analysis of flow field at the end of combustor simulator

摘要

This study was accomplished in order to investigate the effects of different cooling hole configurations on the thermal and flow field characteristics inside a combustor simulator. By using the well-known Brayton cycle, great turbine industries try to extend the inlet temperature and augment engine performance. However the turbine inlet temperature increment creates an extremely harsh environment for the downstream components of the combustor. In this research a three-dimensional representation of Pratt and Whitney aero-engine was simulated and analysed with a commercial finite volume package FLUENT 6.2 to gain fundamental data. The current study has been performed with Reynolds-averaged Navier-Stokes turbulence model (RANS) on internal cooling passages. This combustor simulator combined the interaction of two rows of dilution jets, which were staggered in the streamwise direction and aligned in the span wise direction, with that of film-cooling along the combustor liner walls. The entire findings of the study declare that the greater penetration depth, the thicker the film-cooling layers. Furthermore, in the combustor simulator with more cooling holes, the temperature near the wall and between the jets was slightly increased. Also at the leading edge of the jet, and at the jet-mainstream interface, the gradients of temperature were quite high.