| 苏志善,李华聪,徐刚刚.航空发动机燃油系统附件低温试验方法[J].装备环境工程,2021,18(6):94-100. SU Zhi-shan,LI Hua-cong,XU Gang-gang.Low Temperature Test Method For Aviation Engine Fuel System Accessories[J].Equipment Environmental Engineering,2021,18(6):94-100. |
| 航空发动机燃油系统附件低温试验方法 |
| Low Temperature Test Method For Aviation Engine Fuel System Accessories |
| 投稿时间：2021-01-18 修订日期：2021-02-26 |
| DOI：10.7643/issn.1672-9242.2021.06.014 |
| 中文关键词: 空发动机 燃油系统 附件 标准 低温试验中图分类号:V233 文献标识码:A 文章编号:1672-9242(2021)06-0094-07 |
| 英文关键词:aeroengine fuel system accessories standard low temperature test |
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| Author | Institution |
| SU Zhi-shan | School of Power and Energy, Northwestern Polytechnical University, Xi¢an 710129, China;AECC Xi¢an Engine Control Technology Co., Ltd, Xi¢an 710077, China |
| LI Hua-cong | School of Power and Energy, Northwestern Polytechnical University, Xi¢an 710129, China |
| XU Gang-gang | AECC Xi¢an Engine Control Technology Co., Ltd, Xi¢an 710077, China |
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| 中文摘要: |
| 目的 探索一种航空发动机燃油系统附件低温试验方法。方法 梳理对比国内外航空发动机燃油系统附件低温试验方法的差异，分析国内外标准规定的试验温度差异的来源，检测3号喷气燃料的实际低温特性，验证‒51 ℃的试验温度对3号喷气燃料的不适用性。分析航空发动机系统附件低温工作时会升温的特点，提出尽量模拟起动过程的低温试验方法。结果 利用提出的试验方法，在环境温度为‒55 ℃、燃油温度为‒40 ℃下，进行了135 h低温试验，额外单独进行1000次模拟发动机低温起动过程。试验过程中，某型主燃油泵调节器工作正常，并随某航空发动机通过了某飞机在我国北方某机场的高寒试飞试验。结论 GJB 241A规定的燃油温度‒51 ℃或黏度12 mm2/s对应的温度(‒56 ℃)不适用于3号喷气燃料，环境温度为‒55 ℃，燃油温度为‒40 ℃，并尽量模拟发动机低温起动过程的低温试验方法能够有效验证航空发动机燃油系统附件的低温工作能力。 |
| 英文摘要: |
| In order to explore a low temperature test method for aircraft engine fuel system accessories, this paper summarized and compared the differences between domestic and foreign low temperature test methods for aircraft engine fuel system accessories. The source of the differences of test temperature in domestic and foreign standards was analyzed. The actual low temperature characteristics of No.3 jet fuel were tested. The inapplicability of the test temperature of ‒51 ℃ to No.3 jet fuel was verified. This paper analyzed the characteristics of heating up when the aero-engine system accessories work at low temperature and put forward a low temperature test method to simulate the starting process as much as possible. Under the ambient temperature of ‒55 ℃ and fuel temperature of ‒40 ℃, a 135-hour low temperature test was carried out with the proposed test method. An additional 1000 times of simulation of the low temperature starting process of the engine was carried out separately. During the test, the regulator of a certain type of main fuel pump worked normally, and passed the high cold flight test of a certain aircraft with an aeroengine in a certain airport in north China. The fuel temperature specified in GJB 241A is ‒51 ℃ or the temperature (‒56 ℃) corresponding to a viscosity of 12 mm2/s is not applicable to No. 3 jet fuel. The ambient temperature is ‒55 ℃, the fuel temperature is ‒40 ℃, and the low temperature test method which simulates the low temperature starting process of the engine as far as possible can effectively verify the low temperature working ability of the aviation engine fuel system accessories. |
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