航空用ガスタービンエンジン燃焼器の希釈流配分およびライナ冷却流流出位置がNOxに及ぼす影響(創立40周年記念)

Abstract

It is very important to predict the internal combusting flow fields and NOx emission for efficient design and improvement of low-NOx combustors for aircraft engines. In this study, steady RANS simulation is conducted on the sector combustor model for a regional jet aircraft engine. The effects of dilution air flow balance between liners and liner-cooling air flow outlet location (i.e. effect of single/double wall liners) are investigated. The results show that the numerical results are in general agreement with the experimental ones. The equal dilution air flow balance between liners and the downstream liner-cooling air flow outlet location by using double-wall liners are desirable design options for low NOx combustor.