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李翔,吴正洪,林磊,等. 涡扇发动机外涵流道一体化精细设计[J]. 科学技术与工程, 2020, 20(32): 13477-13481.
LIXIANG,et al.Refining of the integal bypass duct design for turbofan engine[J].Science Technology and Engineering,2020,20(32):13477-13481.
涡扇发动机外涵流道一体化精细设计
Refining of the integal bypass duct design for turbofan engine
投稿时间:2019-09-17  修订日期:2020-07-01
DOI:
中文关键词:  外涵道,分流环,下偏结构,上凸型
英文关键词:bypass duct  splitter, lean  lean trailing structure  curve type
基金项目:
                    
作者单位
李翔 中国航发四川燃气涡轮研究院
吴正洪 中国航发四川燃气涡轮研究院
林磊 中国航发四川燃气涡轮研究院
马健 中国航发四川燃气涡轮研究院
邓雪娇 中国航发四川燃气涡轮研究院
刘超 中国航发四川燃气涡轮研究院
伏宇 中国航发四川燃气涡轮研究院
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中文摘要:
      外涵流道气流是发动机推力主要来源之一,外涵流道设计对整机性能有着重要的影响。外涵流道主要由中介机匣、外涵机匣、核心机外机匣、调节机构以及燃滑油管路等部件形成。其中,中介机匣分流环与核心机外机匣连接处的突扩结构以及管路等各种突兀结构,产生了外涵流道的大量损失。为了解决上述问题,本文基于外涵流道一体化评估系统,系统分析了外涵流道中突兀结构的流动损失特性。为了降低中介机匣与外涵连接结构的突扩程度,提出了中介机匣分流环尾缘下偏的改进措施,精细设计了2°、4°和6°三种下偏角,以及直线型、上凸型两种下偏型面,并且对比分析了各工况下的收益评估,结果表明上凸型分流环尾缘下偏结构能够有效的降低中介机匣的突扩损失,提升了外涵流道的性能。
英文摘要:
      Bypass duct is main source of aircraft power, and is consisted of compressor intermediate duct, bypass shroud, core shroud, blade adjuster and fuel, oil pipe. The sudden expansion structure in the junction between splitter and core shroud and the abrupt pipe structure leads lots of loss in bypass duct, which reduce the mixer efficiency and engine performance. In order to solve this problems, according to the loss mechanism of bypass duct,a lean splitter trailing structure has been propose. The lean splitter trailing structure can smooth the abrupt expansion junction between splitter and core shroud, and also reduce the loss in CID exit. The lower loss of CID has improve inlet flow quantity of bypass duct, and subsequently reduce the loss of bypass and increase the total pressure in the exit of bypass outlet. In order to improve the performance of bypass furthermore, a line type and a curve type lean splitter trailing structure has been come up with. Some researches has been take to compare the benefit. It is found that the curve type get more benefit than the line type because of its transition function.
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