航空涡扇发动机性能分散度控制

王赫; 王军; 施磊; 赵肃; 赵明阳

doi:10.13224/j.cnki.jasp.20240543

航空涡扇发动机性能分散度控制

doi: 10.13224/j.cnki.jasp.20240543

中国航发沈阳发动机研究所，沈阳 110015

详细信息

作者简介:
王赫（1989-），男，高级工程师，硕士，主要从事航空发动机总体性能设计的研究。E-mail：wanghe_200806@126.com

中图分类号: V231.3
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出版历程
- 收稿日期: 2024-08-03
- 网络出版日期: 2025-03-13

Performance dispersion control of aero turbofan engine

Shenyang Engine Research Institute，Aero Engine Corporation of China，Shenyang 110015，China

摘要

摘要:
面向航空涡扇发动机全生命周期性能分散度控制问题，开展出厂验收试车控制方法研究。针对部件特性和流道几何面积偏差导致的性能分散度，开展关键匹配参数与性能分散度关联性分析，提出出厂试车检查风扇压比公差±0.75%和相对高低压转子转差±0.5%的控制方法；经10台发动机试验验证，推力分散度由±4.9%降低至±2.2%，排气温度分散度由±2.0%降低至±0.7%。针对性能衰减导致的推力分散度，建立性能衰减模型，描述了全寿命期推力衰减与工作时间、排气温度、返厂修理的关系，提出出厂试车检查排气温度裕度20～30 ℃的控制方法，经1台发动机持久试车验证，推力衰减1.2%。衰减后推力相对其余9台发动机新机推力叠加分散度±3.4%，解决了寿命期内推力分散度大问题。
- 涡扇发动机 /
- 验收试车 /
- 全寿命期 /
- 性能分散度 /
- 性能衰减
Abstract:
Research on the dispersion control methods during the engine acceptance test process is a key to control performance dispersion throughout the entire life cycle of aero turbofan engine. Based on the deviation of component characteristics and geometric area, research on the correlation between engine matching and performance dispersion was carried out. The control methods of fan pressure ratio tolerance ±0.75% and rotors relationship ±0.5% were proposed. Through tests on 10 new engines, thrust dispersion reduced from ±4.9% to ±2.2% and exhaust gas temperature dispersion reduced from ±2.0% to ±0.7%. Based on the control methods of fan pressure and rotors relationship, an engine performance degradation model, which characterized the relationships among thrust degradation, working time, exhaust gas temperature and repair, was established to solve thrust dispersion during the whole life cycle. The control method of exhaust temperature margin 20—30 ℃ of new engine was proposed. Through endurance test on 1 engine, intermediate state thrust was degraded by 1.2%. The superimposed thrust dispersion of the other 9 new engines was ±3.4%, helping to solve the thrust dispersion problem during the whole life cycle.
- turbofan engine /
- acceptance test /
- whole life cycle /
- performance dispersion /
- performance degradation

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图 1 节流状态推力

Figure 1. Throttling state thrust

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图 2 节流状态排气温度

Figure 2. Throttling state exhaust gas temperature

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图 3 推力偏差量

Figure 3. Thrust deviation

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图 4 排气温度偏差量

Figure 4. Exhaust gas temperature deviation

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图 5 喷管面积变对风扇压比和推力的影响

Figure 5. Effect of nozzle area on fan pressure ratio and thrust

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图 6 部件特性偏差对涵道比的影响

Figure 6. Influence component characteristic deviation on bypass ratio

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图 7 涡轮导向器面积偏差对涵道比的影响

Figure 7. Influence turbine guide area deviation on bypass ratio

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图 8 转差控制要求

Figure 8. Control of rotors relationship

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图 9 增加控制后节流状态推力

Figure 9. Throttling state thrust with enhanced control

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图 10 增加控制后节流状态排气温度

Figure 10. Throttling state exhaust gas temperature with enhanced control

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图 11 发动机使用过程性能衰减

Figure 11. Engine performance degradation during operation

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图 12 初始排气温度裕度控制时发动机性能衰减

Figure 12. Engine performance degradation with initial exhaust gas temperature control

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