可变几何单凹腔驻涡燃烧室的贫油熄火性能试验

Experimental Researches on Lean Blowout Performance of a Variable Geometry Single-Cavity Trapped Vortex Combustor

关键词:  可变几何  单凹腔驻涡燃烧室  贫油熄火性能  实验

Key words:  Variable geometry  Single-cavity trapped vortex combustor  Lean blowout  Experiment

摘要:

为了研究可变几何单凹腔驻涡燃烧室的贫油熄火性能，设计了一个可变几何单凹腔驻涡燃烧室，通过改变凹腔前进气槽的开度，实现对凹腔当量比的控制，并在此基础上进行了贫油熄火性能试验。试验在常压状态下进行，采用航空煤油作为燃料。试验中的主要研究参数如下:进口温度在287～487K变化；进口马赫数在0.2～0.3变化。研究结果表明:可变几何单凹腔驻涡燃烧室的贫油熄火油气比随着进口温度的增加而减小，随着进口马赫数的增加而增加；保持进口马赫数为0.25不变，当进口温度为287K时，贫油熄火油气比随着凹腔前进气开度的减小先增加后减小，而当进口温度逐渐升高到487K时，这一趋势逐渐转变为单调减小；保持进口温度为487K不变，贫油熄火油气比随着凹腔前进气开度的减小而减小。

Abstract:

A variable geometry single-cavity trapped vortex combustor (STVC) was designed to study the lean blowout performance. The cavity equivalence ratio could be changed by changing the opening ratio (OR) of the cavity inlet. Experiments were accomplished at atmospheric pressure. Aviation kerosene was employed as fuel. In the all operating conditions， inlet temperature of the combustor varied from 287K up to 487K， and inlet Mach number ranged from 0.2 to 0.3. It was revealed that the lean blowout (LBO) decreased while inlet temperature increased. LBO also increased with the increasing of inlet Mach number. When the inlet temperature was 287K with inlet Mach number kept constant to 0.25， LBO first increased then decreased as cavity inlet OR increased. However， when the inlet temperature was up to 487K， the trend turned to be monotonously decreased as inlet temperature increased. Besides， when the inlet temperature was kept constant to 487K， the LBO decreased as OR increased.