涡扇发动机熄火故障在线检测方法

王玉东

doi:10.13224/j.cnki.jasp.20200432

涡扇发动机熄火故障在线检测方法

doi: 10.13224/j.cnki.jasp.20200432

王玉东

中国航空发动机集团有限公司商用航空发动机有限责任公司, 上海 200241

详细信息

作者简介:
王玉东(1981-),男,高级工程师,博士,主要从事航空发动机总体性能方案设计技术研究。E-mail:wangyd05@163.com

中图分类号: V231.3
计量
- 文章访问数: 161
- HTML浏览量: 8
- PDF量: 144
- 被引次数: 0
出版历程
- 收稿日期: 2020-10-16
- 刊出日期: 2021-07-28

On-line detection method of flameout in turbofan engine

WANG Yudong

Commercial Aircraft Engine Company Limited, Aero Engine Corporation of China, Shanghai 200241, China

摘要

摘要: 采用机载可测量的高压转子物理转速、低压转子物理转速和发动机进口总压等参数，建立了基于换算加速率的熄火故障在线检测方法。经全包线发动机工况计算仿真和试验验证，熄火过程的高低压转速加速率幅值为减速和喘振过程的1.5~5.0倍，高压轴断裂过程的高压转子加速率幅值是熄火过程的6.0~10.0倍，低压轴断裂过程的低压转速加速率幅值是熄火过程的2.0~3.5倍。这些特征能够将熄火与减速、喘振和断轴等瞬态过程明确区分。经发动机试车验证，该方法检测时间为0~0.3s，检测率100%，未发现误检和漏检。
- 涡扇发动机 /
- 熄火故障 /
- 转速加速率 /
- 逻辑 /
- 机载检测
Abstract: The on-board measured parameters including high pressure rotor speed, low pressure rotor speed and engine inlet total pressure were used to establish the flameout on-line detection method based on the corrected change rates of these physical speeds. According to engine states modulations in the whole envelop and engine tests, the amplitude of change rates of high and low pressure rotor speeds in flame out process was 1.5-5.0 times that in deceleration and surge process, the amplitude of change rate of high pressure rotor speed in high pressure shaft fracture process was 6.0-10.0 times that in flameout process, and the amplitude of change rate of low pressure rotor speed in low speed pressure shaft frac-ture process was 2.0-3.5 times that in flameout process. With these properties, the detection method could clearly distinguish flameout process from other transient processes such as deceleration, surge and shaft fracture. Being verified in engine tests, the detection time was 0-0.3s, the detection rate of this method was 100%, and no false or missed detection had been found.
- turbofan engine /
- flameout /
- rate of change of speed /
- logic /
- onboard detection

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参考文献(22)

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