涡轮增压器轴向力变化规律试验与仿真

doi:10.12382/bgxb.2022.0045

摘要/Abstract

摘要：

提出一种基于悬浮式设计的涡轮增压器轴向力测量方案,解决涡轮增压器轴向力测量范围窄和零点漂移问题,通过试验测量了增压器转子轴向载荷。进一步建立包含轮背间隙、密封环间隙的增压器压气机和涡轮仿真分析模型,基于试验结果验证模型的可靠性,并应用该模型研究揭示了增压器压轮和涡轮轴向力随工况的一般变化规律。研究结果表明:外吹状态时,在同一转速下增压器转子轴向力值随压气机端质量流量的减小而增大;自循环状态时,在转速低于额定转速时,增压器转子轴向力随转速的增加而增大,在转速高于额定转速时,增压器转子轴向力随转速的增加而减小;同一转速下,除喘振点附近,压气机轴向载荷随入口质量流量的减小而增大,涡轮轴向载荷随涡轮入口质量流量的增加而增大;压端和涡端轴向载荷最大的两个区域均为叶轮背盘和叶轮轮毂,且两区域轴向载荷方向相反。

关键词: 涡轮增压器, 止推轴承, 轴向力, 数值模拟计算

Abstract:

A turbocharger axial force measurement scheme based on suspension design was proposed to solve the problems of narrow measuring range and zero drift in turbocharger axial force measurement, and experimentally measure the axial load of turbocharger rotor. Furthermore, a simulation analysis model of turbocharger compressor and turbine was established, including wheel back clearance and seal ring clearance, and the reliability of the model was verified based on the test results. The general variation of axial force of turbocharger compressor and turbine wheel with working conditions was revealed through this model. The results showed that: under the condition of external blowing, the axial force of the turbocharger rotor increases with the decrease of the mass flow rate of the compressor end at the same speed; in self-circulation state, at the speed lower than rated speed, the axial force of the turbocharger rotor increases as the speed increases, while at the speed greater than rated speed, the axial force of the turbocharger rotor decreases with the increasing speed; in addition, at the same speed, the axial load of the compressor increases with the decreasing inlet mass flow except around the surge point, the axial load of the turbine increases with the increasing mass flow rate at the turbine inlet; the two regions with the largest axial loads at the compressor end and turbine end are the impeller back disk and the impeller hub, and the directions of the axial loads in the two regions are opposite.

Key words: turbocharger, thrust bearing, axial load, numerical simulation and calculation

中图分类号:

TK421⁺.8

王翠翠, 闫瑞乾, 丁占铭, 佟鼎, 吴新涛, 高超, 庄丽. 涡轮增压器轴向力变化规律试验与仿真[J]. 兵工学报, 2023, 44(1): 307-315.

WANG Cuicui, YAN Ruiqian, DING Zhanming, TONG Ding, WU Xintao, GAO Chao, ZHUANG Li. Experimental and Simulation Study on Axial Force Variation of Turbocharger[J]. Acta Armamentarii, 2023, 44(1): 307-315.

图/表 13

表1 增压器基本参数

Table 1 Turbocharger specificationsmm

参数	数值
涡轮进口叶尖直径	84
涡轮出口叶尖直径	75
涡轮进口叶高	13.8
压气机叶轮进口叶尖直径	66
压气机叶轮出口叶尖直径	93

图1 轴向力测量方案

Fig.1 Turbocharger axial load measurement scheme

图2 试验台架

Fig.2 Test bench

图3 涡轮增压器转子轴向载荷方向

Fig.3 Load directions of the turbocharger rotor

图4 各转速下的压气机性能和轴向力

Fig.4 Compressor performance and axial force at each speed

图5 自循环状态不同转速对应轴向力

Fig.5 Thrust forces at different rotating speed in a self-circulating state

图6 压气机计算域网格

Fig.6 Grid models of compressor

图7 涡轮计算域网格

Fig.7 Grid models of turbine

表2 仿真分析边界条件

Table 2 Boundary conditions for CFD simulation

算例	增压器转速/ (r·min^-1)	涡轮进口总温/K	涡轮进口总压/kPa	涡轮出口静压/kPa	压气机进口总压/kPa	压气机进口总温/K	压气机出口总压/kPa
1	91534	923.15	238.22	100.35	100	303.75	190
2	90933	923.15	226.39	100.35	100	303.75	210
3	90557	923.15	223.92	100.35	100	303.75	230
4	90332	923.15	211.16	100.35	100	303.75	250
5	91309	923.15	210.94	100.35	100	303.75	252
6	91309	923.15	207.43	100.35	100	303.75	243

图8 涡轮增压器轴向力对比

Fig.8 Comparision of thrust forces

图9 压气机轴向力随质量流量的变化曲线

Fig.9 Thrust forces of compressor at different mass flow rates

图10 涡轮端轴向力随质量流量的变化曲线

Fig.10 Thrust forces of turbine at different mass flow rates

图11 轴向力组成部分对比

Fig.11 Comparison of axial force components

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