某型涡轴发动机喘振攻关与验证
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(海军驻常州地区航空军事代表室,江苏常州 213001)

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V235.1

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Research on a Certain Type of Turbine Shaft Engine Surge
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(Aeronautical Military Representatives Office of Navy in Changzhou, Changzhou Jiangsu 213001, China)

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    摘要:

    针对某型涡轴发动机夏季试车时常发生加速喘振故障的问题,使用故障树初步分析引起喘振的主要原因,并通过径向扩压器叶片进行流场仿真、串装、多台发动机对比计量、试车试验等,对喘振原因进行深入分析。研究表明径向扩压器进口叶根倒角变大对发动机加速性能有一定程度的改善作用,大气条件对发动机加速性有一定影响,径扩面积越大、叶根圆角与进气边转接越顺滑,越有利于加速性能。

    Abstract:

    For the problem of turbine shaft engine surge during the acceleration phase in summer, fault tree analysis wasused to analyze the main reasons preliminarily. The methods of flow field simulation of radial diffuser blade, replace mainparts, comparative analysis of multiple engines and commissioning test were used to analyze the reasons deeply. The resultshowed that blade root chamfering became larger conduce to acceleration, atmospheric environment reacted on the prob.lem also. The area of radial diffuser, the smoothness of the connect area of blade root chamfering and inlet had great influ.ence on the surge during the acceleration phase.

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引用本文

詹洪飞,黄帅.某型涡轴发动机喘振攻关与验证[J].海军航空大学学报,2017,32(3):295-301
ZHAN Hongfei, HUANG Shuai. Research on a Certain Type of Turbine Shaft Engine Surge[J]. JOURNAL OF NAVAL AVIATION UNIVERSITY,2017,32(3):295-301

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  • 在线发布日期: 2017-08-23
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