核心机驱动风扇级与高压压气机匹配试验中外涵排气系统的设计与试验验证  

Design and test verficiation of bypass exhaust system for core driven fan stage in the matching environment of high pressure compressor

作　　者：马昌友 侯敏杰 梁俊 裴会平 MA Chang-you;HOU Min-jie;LIANG Jun;PEI Hui-ping(AECC Commercial Aircraft Engine Manufacturing CO.,Ltd.,Shanghai 201306,China;AECC Sichuan Gas Turbine Establishment,Mianyang 621000,China)

机构地区：[1]中国航发上海商用航空发动机制造有限责任公司,上海201306 [2]中国航发四川燃气涡轮研究院,四川绵阳621000

出　　处：《燃气涡轮试验与研究》2020年第1期6-11,共6页Gas Turbine Experiment and Research

摘　　要：为实现在常规轴单涵道压气机试验器上开展核心机驱动风扇级(CDFS)与高压压气机(HPC)匹配性能试验,根据匹配试验环境下的外涵气流和HPC级间气流的特点,提出采用大流量、低压损的抽气系统和直排大气的放气系统分别对外涵流量和HPC级间引气流量进行调节,实现对匹配涵道比和HPC级间引气率的有效控制。试验验证表明:在匹配试验件外涵流道出口机匣上沿周向开设的多个排气孔能间接实现外涵全环排气,但外涵集气装置是制约外涵排气能力的主要瓶颈,其气动性能可采用极限流量和总压损失影响因子描述;优化外涵集气与测量装置、降低外涵抽气背压,是提高外涵排气能力的主要途径。To carry out the matching performance experiment between the core driven fan stage(CDFS)and the high pressure compressor(HPC)on the conventional axial compressor test rig,according to the charac teristics of the bypass flow and HPC inter-stage flow in the matching environment,a large-flow air bleed system and a direct-discharge exhaust system were proposed to control the bypass flow and the HPC's in ter-stage bleeding flow respectively,ensuring the effective control of bypass ratio and bleeding ratio.The experimental verification shows that:1)It is possible to indirectly realize full bypass exhaust by using multi ple exhaust ports along the circumferential direction on the bypass casing of the matching test piece,but the bypass flow collection device is the main bottleneck restricting the bypass exhaust capacity,and its aerody namic performance can be described by using the maximum limit flow rate and total pressure loss influenc ing factor.2)Optimizing the aerodynamic performance of the bypass flow collection device and measure ment instrument,and reducing the back pressure of air bleed system are the main ways to improve the by pass exhaust capacity.

关 键 词：航空发动机 变循环发动机 核心机驱动风扇级 高压压气机 涵道比 外涵排气 匹配性能 试验研究 

分 类 号：V235.13[航空宇航科学与技术—航空宇航推进理论与工程]