塞式喷管对乙烯燃料旋转爆轰冲压发动机工作特性的影响

Effect of Aerospike Nozzle on Operating Characteristics of Ethylene-fuel Rotating Detonation Ramjet Engine

摘要

摘要:推进性能的提升是旋转爆轰发动机研究的重要目标，而尾喷管是将推进剂化学能转化为发动机机械能的关键部件，制约发动机的推进性能。研究了塞式喷管对旋转爆轰冲压发动机工作特性的影响，采用乙烯和空气作为推进剂，实验在总温 860K、总流量 1.0kg/s 的来流条件下，对比了无喷管基准构型与不同设计压比的塞式喷管构型的起爆界限、传播模态及推进性能。实验结果表明:塞式喷管利用其高度补偿特性，显著改善了燃烧室出口流场，有效降低了自持旋转爆轰的当量比下限。随着设计压比增大，起爆范围呈先宽后窄趋势，在压比为 3 时达到最优;当压比超过 6 时，过强的喉部反射激波导致起爆失败。实验观测到喷管反压诱导的双波对撞与轴向脉冲爆轰模态，其中轴向脉冲爆轰模态会导致隔离段流场转为亚声速。推进性能方面，塞式喷管显著提升了推力与比冲，在最优压比 3 的构型下，推力较基准构型提升 38.6%，最大燃料比冲达到 2458.8s。验证了塞式喷管在拓宽旋转爆轰冲压发动机稳定工作边界和提升推力性能方面的显著优势。

Abstract

Abstract: Improving propulsion performance is a critical objective in the study of rotating detonation engine (RDE). As the key component converting the chemical energy of the propellant into mechanical energy, the nozzle plays a crucial role in constraining the propulsion performance. This paper primarily investigates the impact of aerospike nozzles on the operating characteristics of rotating detonation ramjet engine (RDRE). Experimental studies were conducted using ethylene and air as propellants under inflow conditions of 860 K total temperature and 1.0 kg/s total mass flow rate. The ignition limits, propagation modes, and propulsion performance were compared between baseline nozzle-less configuration and aerospike nozzle configurations with different design pressure ratios. The results indicate that the aerospike nozzle, leveraging its altitude compensation characteristics, significantly improves the combustor outlet flow-field and effectively lowers the lean equivalence ratio limit for self-sustaining rotating detonation. As the design pressure ratio increases, the ignition range initially expands and then contracts, reaching an optimum at a pressure ratio of 3; when the pressure ratio exceeds 6, excessive reflected shock waves at the throat lead to ignition failure. The experiments also observed nozzle back-pressure induced dual-wave collision and longitudinally pulsating detonation (LPD) modes, wherein the LPD mode causes the airflow in the isolator section to transition to subsonic. In terms of propulsion performance, the aerospike nozzle significantly enhances thrust and specific impulse. Under the optimal configuration (pressure ratio of 3), the thrust increases by 38.6% compared to the baseline, with a maximum fuel specific impulse reaching 2458.8 s. The study validates the significant advantages of aerospike nozzles in enhancing the wide-range operational stability and thrust performance of RDRE.

关键词

旋转爆轰发动机 / 塞式喷管 / 冲压推进 / 传播模态 / 乙烯燃料

Key words

rotating detonation engine / aerospike nozzle / ramjet propulsion / propagation mode / ethylene fuel

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基金资助

国家自然科学基金(12272185)