基于3维数值仿真的变循环压缩系统部件匹配分析  

Component Matching Analysis of Variable Cycle Compression System Based on 3D Numerical Simulation

作　　者：李晓庆 孟德君 尹松 LI Xiao-qing;MENG De-jun;YIN Song(AECC Shenyang Engine Research Institute,Shenyang 110015,China)

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015

出　　处：《航空发动机》2024年第3期40-46,共7页Aeroengine

基　　金：航空动力基础研究项目资助。

摘　　要：为了研究变循环压缩系统中各部件之间的匹配关系以及在整机调节时的表现,采用3维数值仿真软件对变循环发动机的风扇、核心机驱动风扇级(CDFS)、高压压气机和外涵道开展联合数值仿真,并对比数值计算与试验结果的差异。针对单、双涵工作模式,开展内、外涵出口节流特性计算,分析了内、外涵出口压力调节导致的各部件匹配关系的变化,获得了涵道比的变化范围以及极限调节状态下的各部件表现出的流动特征,确定了制约整个压缩系统喘振裕度的关键部件。结果表明:在双涵模式下,外涵节流导致风扇匹配点明显提高,首先到达喘振边界;在单涵模式下,外涵节流导致风扇和CDFS匹配点同时提高,几乎同时到达喘振边界;在单、双涵模式下,内涵节流均使高压压气机首先到达喘振边界。仿真得到的外涵道损失与试验偏差在4%以内。In order to study the component matching of a variable cycle compression system and its performance during whole engine operation and adjustment,joint simulation of the fan,CDFS,compressor,and bypass duct of a variable cycle engine was carried out by using 3D numerical tools.The differences between numerical calculation and experimental results were compared.The core-flow throttling characteristics and bypass-flow throttling characteristics were investigated for the single and double bypass mode.The changes in component matching relationships caused by core and bypass outlet pressure regulation were analyzed.The variation range of the bypass ratio and flow characteristics of each component under limit regulation conditions were derived.The key components that constrain the surge margin of the whole compression system were identified.The results show that in double bypass mode,bypass throttling leads to a significant increase in the fan operating point,causing the fan to first reach the surge boundary;while under single bypass mode,bypass throttling leads to a simultaneous increase to the operating points of the fan and the CDFS,causing them to reach the surge boundary almost simultaneously.Core flow throttling causes the high-pressure compressor to first reach the surge boundary in both single and double bypass mode.The deviation between the numerically derived bypass loss and the experimental result is within 4%.

关 键 词：变循环 风扇 高压压气机 节流特性 涵道比 匹配性能 数值模拟 航空发动机 

分 类 号：V211.6[航空宇航科学与技术—航空宇航推进理论与工程]