付垚,朱健,高源,贾亢,孟繁睿,程岩岩,文清兰,汪林全.喷嘴布局对加力燃烧室燃烧性能的影响[J].,2023,22(1):13-20 |
喷嘴布局对加力燃烧室燃烧性能的影响 |
Effects of the nozzle layout on the afterburner combustion performance |
投稿时间:2022-09-24 修订日期:2022-12-17 |
DOI:10.13738/j.issn.1671-8097.022232 |
中文关键词: 航空发动机 加力燃烧室 喷嘴布局 燃烧性能 数值模拟 |
英文关键词: aero-engine afterburner nozzle layout combustion performance numerical simulation |
基金项目:国家自然科学基金项目(面上项目,重点项目,重大项目) |
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中文摘要: |
为研究喷嘴布局对加力燃烧室燃烧过程及主要燃烧性能参数的影响,选择了某典型加力燃烧室,设计了两种喷嘴布局及在两个典型状态点的供油策略。方案1的喷杆数量少,喷嘴布置得更集中,内区喷杆在状态点1不工作;方案2的喷杆数量多,喷嘴布置得更分散,所有喷杆在不同状态点均工作。此外,两种方案喷嘴对应的喷射区域存在明显差别。应用Fluent模拟不同喷油条件下,加力燃烧室在两个状态点的燃烧情况。数值模拟结果表明:方案2使加力燃烧室内燃油分布得更均匀,改善了燃烧过程,提高了不同状态点的总温。相较于方案1,方案2使加力燃烧室在状态点1的总温升增加了49 K、燃烧效率提高了0.033,在状态点2的总温升增加了64 K、燃烧效率提高了0.041。然而,方案1在两个状态点的热态总压恢复系数较方案2分别高0.004和0.003。 |
英文摘要: |
In order to investigate the effects of the nozzle layout on the afterburner combustion process and the main combustion performance parameters, a typical afterburner was selected, two nozzle layouts and the fuel injection strategies at two typical operation points were designed. There were fewer injectors with more intensive arranged nozzles in Case 1, and the inner injectors were not operated at Operation Point 1; there were more injectors with more scattered arranged nozzles in Case 2, and all injectors were operated at dif-ferent operation points. Furthermore, there were significant differences on the injection regions of the nozzles in the two cases. The Fluent was applied to simulate the combustion processes of the afterburner at the two operation points under different injection conditions. The numerical simulation results suggested that: Case 2 made the fuel distributed more homogenously in the afterburner, improved the combustion process, and increased the total temperature at different operation points. Compared with Case 1, Case 2 made the total temperature rise of the afterburner increased 49 K and the combustion efficiency increased 0.033 at Operation Point 1, and made the total temperature rise increased 64 K and the combustion effi-ciency increased 0.041 at Operation Point 2. However, the reacting total pressure recovery coefficients of Case 1 at the two operation points were 0.004 and 0.003 higher than those of Case 2 respectively. |
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