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dc.contributor.author方骁远
dc.contributor.author邢菲
dc.contributor.author徐磊磊
dc.contributor.author邢盼
dc.contributor.author王培勇
dc.date.accessioned2016-05-17T02:44:50Z
dc.date.available2016-05-17T02:44:50Z
dc.date.issued2013-10-29
dc.identifier.citation推进技术,2013,(11):77-83
dc.identifier.issn1001-4055
dc.identifier.otherTJJS201311010
dc.identifier.urihttps://dspace.xmu.edu.cn/handle/2288/105702
dc.description.abstract为探究级间燃烧室对各种航空发动机的性能影响,利用热力循环原理分别计算了在有无级间燃烧室的情况下涡喷、涡扇和涡轴发动机的性能结果并与实际型号做出对比。通过计算获得了上述三种发动机在加入级间燃烧室后的单位推力和耗油率随飞行马赫数等参数在一定范围内变化的曲线。结果表明加入级间燃烧室后对各种发动机的动力性能提升都在10%以上,个别涡轴发动机可达30%。同时若能将加入级间燃烧室后增加的质量控制在一定范围内,则对于各型发动机均可提高其推重比。
dc.description.abstractIn order to investigate the effects of the inter-stage turbine burner( ITB) on aero-engines,the thermodynamic cycle analysis was performed to demonstrate the performance of three kinds of aero-engines with the inter-stage turbine burners.The performance curves for different flight and operation conditions were obtained by calculation.Results show that specific thrust can be improved by at least 10%,and for one turboshaft engine the specific thrust even can be improved by 30%.Based on comparison between the real aero-engine performance and the calculation results,the errors are acceptable and the thrust-weight ratios show the potential capability of ITB application.
dc.description.sponsorship国家自然科学基金(11002125;51106131); 中央高校基本科研业务费专项资金(2013121019)
dc.language.isozh_CN
dc.subject航空发动机
dc.subject涡轮级间燃烧室
dc.subject单位推力
dc.subject燃油消耗率
dc.subject推重比
dc.subjectAero-engine
dc.subjectInter-stage turbine burner
dc.subjectSpecific thrust
dc.subjectSpecific fuel consumption
dc.subjectThrust-weight ratio
dc.title三种航空燃气轮机加入级间燃烧室后性能变化浅析
dc.title.alternativePerformance Analysis of Three Kinds of Aero-Engine with Inter-Stage Turbine Burner
dc.typeArticle


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