涡轮增压器涡轮机端温度改善试验研究

Experimental study on temperature improvement at turbine end of turbocharger

为保证涡前温度升高时增压器的可靠性及寿命,设计涡轮机端增加喷油孔和减小涡轮壳与隔热罩接触宽度的优化方案,并进行增压器回热试验及工艺成本核算。结果表明:与原方案相比,优化后的增压器在转速为80000 r/min时,润滑油流量增加118.6%以上;涡端密封环位置稳定运行温度由258.5~261.0℃降低到86.9~89.2℃;涡端浮动轴承位置稳定运行温度由193.0~196.0℃降低到135.7~137.8℃;转速为80000 r/min热停机时,涡端密封环位置最高回热温度由299.7℃降低到266.8℃,涡端浮动轴承位置最高回热温度由271.2℃降低到251.5℃;增加涡端喷油孔结构成本预计增加0.1元/件,具备工艺及成本实施可行性。

In order to improve the reliability of the turbocharger when the temperature before the turbine housing increases,a oil injection hole at the turbine end is designed,the contact width between the turbine housing and the heat shield is reduced.The turbocharger heat soak back test and process cost accounting are carried out.The results show that when the turbocharger runs at 80000 r/min,the lubricating oil flow increases by more than 118.6%,the stable operating temperature of the turbine end seal ring position decreases from 258.5~261.0℃to 86.9~89.2℃,the stable operating temperature of the turbine end floating bearing position decreases from 193.0~196.0℃to 135.7~137.8℃.The maximum heat soak back temperature of the seal ring at the turbine end decreases from 299.7℃to 266.8℃at 80000 r/min for thermal stop,the maximum heat back soak temperature of the floating bearing at the turbine end decreases from 271.2℃to 251.5℃.The estimated cost of adding injection hole at the turbine end will increase by 0.1 yuan/piece,which is feasible for process and cost implementation.