大涵道比风扇/增压级进气畸变数值模拟研究

doi:10.13675/j.cnki. tjjs. 180632

推进技术 ›› 2019, Vol. 40 ›› Issue (11): 2498-2504.DOI: 10.13675/j.cnki. tjjs. 180632

大涵道比风扇/增压级进气畸变数值模拟研究

郭晋¹,胡骏^1,2,屠宝锋^1,2,王志强^1,2

1.南京航空航天大学能源与动力学院,江苏省航空动力系统重点实验室,江苏南京 210016;2.先进航空发动机协同创新中心,北京;100191

发布日期:2021-08-15
作者简介:郭晋，博士生，研究领域为压缩系统气动稳定性预测与控制技术。E-mail：guojin_nj@126.com

Numerical Study of High Bypass Ratio Fan/BoosterStage with Inlet Distortion

1.Jiangsu Province Key Laboratory of Aerospace Power Systems,College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;2.Collaborative Innovation Center of Advanced Aero-Engine,Beijing 100191,China

Published:2021-08-15

摘要/Abstract

摘要： 为探究进口总压畸变下大涵道比风扇/增压级内部流场的主要特征，基于三维彻体力模型的思想，开发了一套能够实现风扇/增压级内外涵联算功能的三维数值计算程序。利用该程序模拟了某大涵道比风扇/增压级在周向总压畸变进气下的三维流场。计算结果表明：大涵道比风扇单转子不同叶高处的畸变传递特征差异较大，转子出口总压畸变强度由叶根到叶尖逐渐降低，在叶尖处衰减为最小值1.5%；在转子出口相应诱导出的总温畸变强度由叶根到叶尖逐渐升高，在叶尖处达到最大值1.4%；进口周向总压畸变导致风扇转子总压比下降0.5%，而风扇转子出口形成的总压总温复合畸变导致增压级总压比下降2%；总压畸变在增压级中呈逐级衰减趋势，而高温畸变区的周向范围在逐级增加。

关键词: 大涵道比风扇/增压级;周向总压畸变;三维彻体力模型;数值模拟

Abstract: In order to explore the main characteristics of the internal flow field in a high bypass ratio fan/booster stage with inlet total pressure distortion, a three-dimensional numerical calculation program was developed based on the idea of three-dimensional body force model. This program can realize the synchronous calculation of core and bypass compressors, which was used to simulate the three-dimensional flow field of a high bypass ratio fan/booster stage under circumferential total pressure distortion. The results show that the characteristic of distortion transfer at different blade heights of the fan rotor with large bypass ratio varies greatly. The intensity of total pressure distortion at the rotor outlet decreases gradually from hub to tip, and decreases to a minimum value of 1.5%. Correspondingly, the intensity of total temperature distortion induced at the rotor outlet increases gradually from hub to tip, reaching a maximum value of 1.4%. The total pressure ratio of the fan rotor is reduced by 0.5% due to the inlet circumferential total pressure distortion. Meanwhile, the total pressure ratio of the booster stage is reduced by 2% due to the combined distortion of total pressure and total temperature at the rotor outlet. Besides, the total pressure distortion is attenuated in the booster stage, while the circumferential range of high temperature distortion zones is increasing stage by stage.

Key words: High bypass ratio fan/ booster stage;Circumferential total pressure distortion;Three-dimensional body force model;Numerical simulation

郭晋,胡骏,屠宝锋,王志强. 大涵道比风扇/增压级进气畸变数值模拟研究[J]. 推进技术, 2019, 40(11): 2498-2504.

GUO Jin¹,HU Jun^1,2,TU Bao-feng^1,2,WANG Zhi-qiang^1,2. Numerical Study of High Bypass Ratio Fan/BoosterStage with Inlet Distortion[J]. Journal of Propulsion Technology, 2019, 40(11): 2498-2504.

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大涵道比风扇/增压级进气畸变数值模拟研究

Numerical Study of High Bypass Ratio Fan/BoosterStage with Inlet Distortion

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