摘要
为了考察中介机匣气动性能水平并验证设计方法,对中介机匣进行了气动性能试验,同时采用NUMECA Fine软件进行了相应的数值模拟。为了准确测量流过中介机匣内涵的气流流量,设计了一种流量测量装置并进行了精度校核,结果表明:测量精度的相对偏差小于1.5%。针对高进口马赫数时在进口平直段上两侧的壁面静压比中间区域小,以及某些涵道比未能调节到目标进口马赫数的情况,进行了相应的数值模拟并提出了解决方案。用单点总压管对内、外涵出口进行了扇面测量,得到了内涵的总性能曲线、总压恢复系数径向变化曲线及内、外涵总压恢复系数云图,并与计算结果进行对比,结果表明:内涵总性能曲线及内、外涵总压恢复系数云图的计算结果与试验结果吻合较好,在设计状态下,内、外涵出口测量截面的总压恢复系数分别为0.992 1、0.986,两数值均高于设计指标,中介机匣具有较好的气动性能。
In order to investigate the aerodynamic performance of the intermediate casing and verify the design method,the aerodynamic performance of the intermediate casing was experimented.At the same time,corresponding numerical simulations were carried out by using NUMECA Fine software.To accurately measure the flow through the core of the intermediate casing,a flow measurement device was designed and the accuracy was checked.Results showed the relative deviation of the measurement accuracy was less than 1.5%.Considering the wall static pressure on both sides of the inlet straight section was smaller than in the center area at high inlet Mach number,and some bypass ratios failed to be adjusted to the target inlet Mach numbers,corresponding numerical simulations were carried out and the solutions were proposed.A single hole total pressure probe was used to measure the sector of the core and bypass outlet.The total performance curves and total pressure recovery coefficient radial change curves of the core,the total pressure recovery coefficient cloud images of the core and bypass were gained and compared with the calculated results.Results showed the core total performance curves,the core and bypass total pressure recovery coefficient cloud images of the calculated results were in good agreement with the experimental results.In the design state,the total pressure recovery coefficients of the core and bypass outlet measurement section were 0.9921 and 0.986,respectively,both were higher than the design indices,indicating the intermediate casing had good aerodynamic performance.
作者
刘建明
郝晟淳
武卉
赵展
张雷
李昊
LIU Jianming;HAO Shengchun;WU Hui;ZHAO Zhan;ZHANG Lei;LI Hao(Shenyang Engine Research Institute,Aero Engine Corporation of China,Shenyang 110015,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2022年第7期1560-1568,共9页
Journal of Aerospace Power
关键词
中介机匣
大落差长度比
涵道比
气动性能
总压恢复系数
intermediate casing
large radius change to length ratio
bypass ratio
aerodynamic performance
total pressure recovery coefficient
