| 邢卫东,佟鼎,刘莹,邓春龙,门日秀,吴新涛.车用柴油机高压比宽流量增压器研制[J].装备环境工程,2024,21(6):37-44. XING Weidong,TONG Ding,LIU Ying,DENG Chunlong,MEN Rixiu,WU Xintao.Development of High Pressure Ratio Wide Flow Turbocharger for Vehicle Diesel Engine[J].Equipment Environmental Engineering,2024,21(6):37-44. |
| 车用柴油机高压比宽流量增压器研制 |
| Development of High Pressure Ratio Wide Flow Turbocharger for Vehicle Diesel Engine |
| 投稿时间：2024-03-20 修订日期：2024-06-11 |
| DOI：10.7643/issn.1672-9242.2024.06.006 |
| 中文关键词: 高压比 增压器 压气机 涡轮 转子 高海拔环境中图分类号:TK402 文献标志码:A 文章编号:1672-9242(2024)06-0037-08 |
| 英文关键词:high pressure ratio turbocharger compressor turbine rotor high altitude environment |
| 基金项目: |
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| Author | Institution |
| XING Weidong | National Key Laboratory of Diesel Engine Turbocharging Technology, China North Engine Research Institute, Tianjin 300400, China |
| TONG Ding | National Key Laboratory of Diesel Engine Turbocharging Technology, China North Engine Research Institute, Tianjin 300400, China |
| LIU Ying | Kangyue TechnologyShandong Co., Ltd., Shandong Weifang 262718, China |
| DENG Chunlong | National Key Laboratory of Diesel Engine Turbocharging Technology, China North Engine Research Institute, Tianjin 300400, China |
| MEN Rixiu | National Key Laboratory of Diesel Engine Turbocharging Technology, China North Engine Research Institute, Tianjin 300400, China;Department of Mechanics, Tianjin University, Tianjin 300354, China |
| WU Xintao | National Key Laboratory of Diesel Engine Turbocharging Technology, China North Engine Research Institute, Tianjin 300400, China |
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| 中文摘要: |
| 目的 对于单级高压比宽流量增压器，为适应发动机强化指标，进行一系列的改进设计。方法 利用仿真设计与试验相结合的方法，对高海拔环境应用增压器进行改进设计。通过理论推导，确定压气机及涡轮的气动性能优化设计方法，开展高稳定裕度转子轴承系统设计方法研究与验证。结果 匹配高压比宽流量增压器的发动机与原机相比，高原功率恢复了17%，发动机排气温度降低了7%，增压器转速降低了13%。结论 在原机的基础上设计了压比为4.6的宽流量高性能涡轮增压器，成功实现了高压比宽流量增压器的设计，满足了发动机平原、高原不同环境的运行需求。 |
| 英文摘要: |
| The work aims to improve the design of the single stage high pressure ratio wide flow turbocharger, making it adapt to the engine strengthening index. The simulation design and experiment were combined to improve the design of the turbocharger for high altitude environment. Through theoretical derivation, the optimal design method of aerodynamic performance of the compressor and turbine was determined. The design method of the rotor bearing system with high stability margin was studied and verified. Compared with the original engine, the engine with high press ratio wide flow turbocharger restored the high altitude power by 17%, reduced the engine exhaust temperature by 7%, and reduced the turbocharger speed by 13%. A wide flow turbocharger with a pressure ratio of 4.6 is designed on the basis of the original engine, and the design of the high pressure ratio wide flow turbocharger is successfully realized, which can meet the operation requirements of the engine in plain and plateau. |
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