Effect of dilution holes on the performance of a triple swirler combustor  

作　　者：Ding Guoyu He Xiaomin Zhao Ziqiang An Bokun Song Yaoyu Zhu Yixiao 

机构地区：[1]Jiangsu Province Key Laboratory of Aerospace Power Systems, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics [2]Co-Innovation Center for Advanced Aero-Engine [3]AVIC Harbin Dongan Engine (Group) Corporation Ltd.

出　　处：《Chinese Journal of Aeronautics》2014年第6期1421-1429,共9页中国航空学报（英文版）

基　　金：supported by Funding for Outstanding Doctoral Dissertation in NUAA (No. BCXJ 14-01);Funding of Jiangsu Innovation Program for Graduate Education (No. CXLX12_0169)

摘　　要：A triple swirler combustor is considered to be a promising solution for future high temperature rise combustors. The present paper aims to study dilution holes including primary dilution holes and secondary dilution holes on the performance of a triple swirler combustor. Experimental investigations are conducted at different inlet airflow velocities（40–70 m/s） and combustor overall fuel–air ratio with fixed inlet airflow temperature（473 K） and atmospheric pressure. The experimental results show that the ignition is very difficult with specific performance of high ignition fuel–air ratio when the primary dilution holes are located 0.6H（where H is the liner dome height）downstream the dome, while the other four cases have almost the same ignition performance. The position of primary dilution holes has an effect on lean blowout stability and has a large influence on combustion efficiency. The combustion efficiency is the highest when the primary dilution holes are placed 0.9H downstream the dome among the five different locations.For the secondary dilution holes, the pattern factor of Design A is better than that of Design B.A triple swirler combustor is considered to be a promising solution for future high temperature rise combustors. The present paper aims to study dilution holes including primary dilution holes and secondary dilution holes on the performance of a triple swirler combustor. Experimental investigations are conducted at different inlet airflow velocities（40–70 m/s） and combustor overall fuel–air ratio with fixed inlet airflow temperature（473 K） and atmospheric pressure. The experimental results show that the ignition is very difficult with specific performance of high ignition fuel–air ratio when the primary dilution holes are located 0.6H（where H is the liner dome height）downstream the dome, while the other four cases have almost the same ignition performance. The position of primary dilution holes has an effect on lean blowout stability and has a large influence on combustion efficiency. The combustion efficiency is the highest when the primary dilution holes are placed 0.9H downstream the dome among the five different locations.For the secondary dilution holes, the pattern factor of Design A is better than that of Design B.

关 键 词：Combustor performance Fuel–air ratio Primary dilution holes Secondary dilution holes Triple swirler combustor 

分 类 号：V233[航空宇航科学与技术—航空宇航推进理论与工程]