轴向分级燃烧不稳定性的关键因素与控制  

Key factors and control methods of combustion instability under axial staging combustion

作　　者：秦蕾 张光宇 王晓宇[2] 孙晓峰[1] QIN Lei;ZHANG Guangyu;WANG Xiaoyu;SUN Xiaofeng(School of Energy and Power Engineering,Beihang University,Beijing 100191,China;Research Institute of Aero-Engine,Beihang University,Beijing 100191,China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]北京航空航天大学航空发动机研究院,北京100191

出　　处：《航空学报》2025年第5期221-232,共12页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(52476024,52406037);中国博士后科学基金(GZB20240930)。

摘　　要：工业燃气轮机的轴向分级燃烧技术显著拓宽了功率调节比,并有效降低了NOx污染物排放。然而,二级喷嘴的相关参数对燃烧不稳定性的影响仍需深入研究。为此,建立了一个三维理论分析模型,来考虑多热源与穿孔板阻抗边界的耦合作用,以此分析分级燃烧对燃烧不稳定性的影响及声衬的控制机理。研究结果表明,一级喷嘴的热源响应对轴向一阶模态影响明显,而二级喷嘴的相关参数主要影响周向一阶模态。当二级喷嘴位于轴向一阶模态的声压反节点,即燃烧室进出口附近时,对频率和增长率的影响更加明显。当两个二级喷嘴的周向角度差为π/2时,其热源响应对周向一阶分裂模态的综合影响相对微弱;而当周向角度差为π时,二级喷嘴的热源响应对周向一阶分裂模态的综合影响较为显著。此外,二级喷嘴的存在导致周向一阶模态出现轴向声压分布,从而使声衬在接近二级喷嘴的轴向位置能够有效抑制燃烧不稳定性。The axial staging combustion for industrial gas turbines significantly widens the power regulation range and effectively reduces NOx emissions.However,the impact of secondary nozzle parameters on the combustion instability requires further investigation.To address this,a three-dimensional theoretical model is developed to consider the cou⁃pling of multiple nozzles with the perforated liner,in order to analyze the effects of axial staging combustion on com⁃bustion instability and the control mechanisms of the perforated liner.Results show that the flame response of the pri⁃mary nozzle has a notable effect on the first-order axial modes,while the parameters of the secondary nozzle mainly affect the first-order azimuthal modes.Furthermore,when the secondary nozzle is located at the acoustic pressure an⁃tinode of the first-order axial mode,i.e.,near the inlet and outlet of the combustion chamber,its effects on frequency and growth rate become more important.When the circumferential angular difference between the two secondary nozzles isπ/2,the combined effects of their flame responses on the nondegenerate azimuthal modes are relatively weak.In contrast,when the circumferential angular difference isπ,the combined effects of the secondary nozzles’flame responses on the nondegenerate azimuthal modes become more significant.In addition,the presence of the secondary nozzles leads to an axial sound pressure distribution for the first-order azimuthal mode,allowing the perfo⁃rated liner positioned close to the secondary nozzle to effectively suppress the combustion instability.

关 键 词：燃烧不稳定性 轴向分级燃烧 二级喷嘴位置 穿孔板声衬 耦合作用 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]