李伟1，2，李国祥1*，刘莹2，李建平2，甄冠富2，张晓林2,3
1.山东大学能源与动力工程学院，山东济南250061；2.康跃科技股份有限公司，山东寿光262718；
3.机械工业内燃机增压系统重点实验室，山东寿光262718
摘要：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80 000 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80 000 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。
关键词：涡轮增压器；回热试验；涡端密封环；涡端浮动轴承；润滑油流量
Abstract：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 80 000 r/min, the lubricating oil flow increases by more than 1186%, the stable operating temperature of the turbine end seal ring position decreases from 2585~2610 ℃ to 869~892 ℃, the stable operating temperature of the turbine end floating bearing position decreases from 1930~1960 ℃ to 1357~1378 ℃. The maximum heat soak back temperature of the seal ring at the turbine end decreases from 2997 ℃ to 2668 ℃ at 80 000 r/min for thermal stop,the maximum heat back soak temperature of the floating bearing at the turbine end decreases from 2712 ℃ to 2515 ℃. The estimated cost of adding injection hole at the turbine end will increase by 01 yuan/piece, which is feasible for process and cost implementation.
Keywords:turbocharger;heat soak back test;the sealing ring at the turbine end;the floating bearing at the turbine end; lubricating oil flow
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