低燃速贫氧推进剂燃气发生器点火起动影响因素研究

推进技术 ›› 2015, Vol. 36 ›› Issue (5): 761-767.

低燃速贫氧推进剂燃气发生器点火起动影响因素研究

黄海龙¹,郑日恒^1,2,胡小兵¹,赖谋荣¹,刘　娜¹,高新锋¹

北京动力机械研究所，北京 100074,北京动力机械研究所，北京 100074;北京动力机械研究所高超声速冲压发动机技术重点实验室，北京 100074,北京动力机械研究所，北京 100074,北京动力机械研究所，北京 100074,北京动力机械研究所，北京 100074,北京动力机械研究所，北京 100074

发布日期:2021-08-15
作者简介:黄海龙(1979—)，男，工程师，研究领域为固体火箭发动机设计。

Factors on Affecting Ignition Start-up of Gas Generator with Low-Burning Velocity Fuel Rich Propellant

Beijing Power Machinery Institute，Beijing 10074，China,Beijing Power Machinery Institute，Beijing 10074，China; Science and Technology on Scramjet Laboratory，Beijing Power Machinery Institute，Beijing 100074，China,Beijing Power Machinery Institute，Beijing 10074，China,Beijing Power Machinery Institute，Beijing 10074，China,Beijing Power Machinery Institute，Beijing 10074，China and Beijing Power Machinery Institute，Beijing 10074，China

Published:2021-08-15

摘要/Abstract

摘要： 为了探索点火能量、燃速、级配及粒度、点火建压速率等因素对冲压发动机燃气发生器点火起动性能的影响，针对采用低燃速贫氧推进剂的燃气发生器点火起动的影响因素进行了研究，在地面直连式试车台上采用全尺寸燃气发生器进行了多次点火起动性能试验。试验结果表明:燃气发生器点火器点火药量提高20%，点火起动时间提高62.7%。低燃速贫氧推进剂燃速从2.3mm/s降低到1.6mm/s，点火起动时间降低43.6%，在低温-40℃条件下的点火起动时间为0.0895s。低燃速贫氧推进剂氧化剂AP平均粒径由193μm增大到201μm，燃气发生器点火起动时间降低36%。在低温-40℃条件下，喷口堵片优化后的点火起动时间为0.0879s，满足快速起动要求。采取措施解决了低燃速贫氧推进剂燃气发生器点火起动困难的问题。

关键词: 低燃速；贫氧推进剂；点火起动；影响因素；燃气发生器；冲压发动机

Abstract: In order to explore factors on affecting ignition starting of low burning velocity fuel-rich propellant of gas-generator used in ramjet，investigation has been performed for factors including ignition energy，burning velocity，grade and particle size，ignition building pressure rate. Multiple ignition start-up performance tests have been carried out for the full scale gas generator in the ground direct-connect test facility. Test results show that ignition start-up time increases by 62.7% after the igniter powder quantity increases by 20%.The ignition start-up time is also reduced by 43.6% when propellant burning velocity is reduced from 2.3mm/s to 1.6mm/s for the low fuel-rich propellant. The ignition start-up time is 0.0895s under the low temperature -40℃. The ignition start-up time is also reduced by 36% after oxidant particle size increases from 193μm to 201μm. The ignition start-up time is 0.0879s after nozzle cover is optimized under the low temperature -40℃. The ignition start-up problem has been solved after multiple measures are applied in the gas generator with low-burning velocity fuel-rich propellant.

Key words: Low burning velocity；Fuel-rich propellant；Ignition start-up；Affecting factor；Gas generator；Ramjet

黄海龙,郑日恒,胡小兵,赖谋荣,刘　娜,高新锋. 低燃速贫氧推进剂燃气发生器点火起动影响因素研究[J]. 推进技术, 2015, 36(5): 761-767.

HUANG Hai-long¹,ZHENG Ri-heng^1,2,HU Xiao-bing¹,LAI Mou-rong¹,LIU Na¹,GAO Xin-feng¹. Factors on Affecting Ignition Start-up of Gas Generator with Low-Burning Velocity Fuel Rich Propellant[J]. Journal of Propulsion Technology, 2015, 36(5): 761-767.

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