| WP6发动机改RF031燃气轮机中低热值燃烧室改进设计 |
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| 引用本文： | 冯大强,杨灵,屈成泽,朱涛.WP6发动机改RF031燃气轮机中低热值燃烧室改进设计[J].航空发动机,2010,36(1):14-19. |
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| 作者姓名： | 冯大强 杨灵 屈成泽 朱涛 |
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| 作者单位： | 北京航空航天大学交通科学及工程学院,北京,100191 |
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| 摘 要： | 详细介绍了由WP6航空发动机去掉3级压气机改型而成的RF031燃气轮机燃烧室所用燃料由航空煤油改为中低热值气态燃料而进行的改进设计方案。经改进设计,实现了该燃烧室中低热值燃料(10467kJ/m3)的稳定燃烧,经试验验证,各项指标满足总体要求,基本实现了WP6发动机改地面燃气轮机的第1步目标。
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| 关 键 词： | 增压系统 匹配 性能 活塞发动机 仿真模型 无人机 |
Improved Design of Low/Middle Calorific Combustor for RF031 Gas Turbine Derived From WP6 Aeroengine |
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| Authors: | FENG Da-qiang YANG Ling QU Cheng-ze ZHU Tao |
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| Institution: | (School of Traffic, Beijing University of Aeronautics and Astronautics, Beijing, 100191 ) |
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| Abstract: | Two stage turbocharging system for a piston engine was improved to meet higher peocormance requirements of propulsion system for unmanned aireraft. Based on aeroengine operation process calculation theory first stage turbocharger model was built using CFD software and its accuracy was also validated. The parameters of the two stage turbocharger and the pressure ratio matching of high pressure and low pressure compressor were determined. The arrangement concepts of two stage turboeharger and intercooler were discussed. The high altitude characteristics of the two stage turbocharger were analyzed. The acceptable, turbocharger were selected for the two stage turbocharging system |
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| Keywords: | turbocharging system match performance piston engine simulation model unmanned aircraft |
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