某型涡扇发动机在线流道清洗喷射参数选择与试验

为了解决某型飞机进气道距离长、流道形状不规则造成从进气道唇口喷射清洗发动机时喷射参数难以确定的问题，利用linearized instability sheet atomization（LISA）模型和Spalart-Allmaras（S-A）湍流模型，以液滴颗粒大小和运动轨迹为优化目的，以液滴在发动机气流进口端面的覆盖面和穿透能力为效果目标进行数值仿真，优化选取喷嘴的设计参数，减轻了试车工作量并降低了试验费用。通过飞机进气道与发动机联合整机在线清洗台架验证试验测试评估了预先选择喷射参数的喷嘴的喷射性能。台架试车结果表明:发动机采用冷运转状态清洗，喷射参数确定为雾化角为18°，喷嘴在喷射架上的安装角度为上偏角为7°30′，清洗车的供液压力为1MPa。针对发动机的冷起动或者慢车状态，选取的喷嘴类型、喷射压力、喷射角度和安装角度等优化的喷射参数是合理的，不仅能使清洗液滴覆盖整个发动机的进口区域并穿透整个叶栅，而且不会引起附加的风扇压气机叶片侵蚀。 

Online washing injection parameters selection and experimentsfor a certain type of turbofan engine

In order to resolve the problem of determining the injection parameters when spraying to wash a certain type of turbofan engine from the inlet lip for the long distance of inlet and the irregular flow passage, the droplet size and motion trajectory were taken as the optimization goal, and the droplet on the airflow inlet face of the engine and the penetrating ability were taken as the effect target to carry out numerical simulation by using linearized instability sheet atomization（LISA）and Spalart-Allmaras（S-A）models.The nozzle design parameters were determined by optimized selection so that the commissioning workload and trial cost were reduced. Trial run of aircraft inlet combined with engine flow passage online washing was conducted to further measure and evaluate performance of the injection parameters predetermined nozzles. The trial run validation results showed that engine was washed in cold operation state and the injection parameters were determined as spray cone angle of 18°, installation upward offset angel of the nozzle on the spray frame of 7°30′and the washing vehicles feed liquid pressure of 1MPa. The optimal injection parameters, including nozzle type, injection pressure, spray angle and installation angle,for engines cold start or idle condition, were effective, making the washing droplet not only cover the entire engine entrance section and penetrate the whole blade cascade, but also not cause accessional blade erosion.