Influencing factors of flow resistance in oil-air separator

XU Rang-shu; HU Hui; SHAO Chang-hao; NIU Ling

doi:10.13224/j.cnki.jasp.2014.10.018

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Influencing factors of flow resistance in oil-air separator

更新时间：2026-07-07

- Influencing factors of flow resistance in oil-air separator
- Issue 10, (2014)
- 作者机构：
  
  1. 沈阳航空航天大学航空航天工程学部,沈阳,110136
  2. 沈阳航空航天大学航空航天工程学部辽宁省航空推进系统先进测试技术重点实验室,沈阳,110136
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2014.10.018
  CLC：
- Published：2014
- 稿件说明：
移动端阅览
徐让书, 胡慧, 邵长浩, 牛玲. 离心通风器通风阻力的影响因素[J]. 航空动力学报, 2014, (10): 2410-2416. doi: 10.13224/j.cnki.jasp.2014.10.018

XU Rang-shu, HU Hui, SHAO Chang-hao, et al. Influencing factors of flow resistance in oil-air separator[J]. 2014, (10).
徐让书, 胡慧, 邵长浩, 牛玲. 离心通风器通风阻力的影响因素[J]. 航空动力学报, 2014, (10): 2410-2416. doi: 10.13224/j.cnki.jasp.2014.10.018 DOI：

XU Rang-shu, HU Hui, SHAO Chang-hao, et al. Influencing factors of flow resistance in oil-air separator[J]. 2014, (10). DOI： 10.13224/j.cnki.jasp.2014.10.018.

摘要

为分析航空发动机离心通风器通风阻力的影响因素，应用计算流体动力学（CFD）和雷诺应力模型（RSM）对离心通风器内流场进行数值计算.比较相同工况下通风阻力的计算与试验值，保证模型的适用性.通过计算得到不同工况和结构的足够拟合数量的离心通风器阻力值，对数据进行二元二次空间趋势面回归分析.结果表明：流量和转速的增加都带来更大的通风阻力；通风孔偏心设计与减小辐板顶圆半径可以减小通风阻力，通风孔偏心设计存在最佳偏心距约为7.5mm.

Abstract

In order to analyze the influencing factors of flow resistance in the oil-air separator of the aero-engine

flow field in the oil-air separator was caculated numerically using computational fluid dynamics (CFD) and Reynolds stress model (RSM). The flow resistance of calculation and experiment under the same operating conditions were compared to ensure the applicability of the model. Enough number of flow resistance values of different operating conditions and structures had been calculated for the binary quadratic space trend surface regression. The results show that the increasing of flow rate and rotational speed will bring greater flow resistance. The design of the breather hole eccentricity and the reducing the plate tip radius can reduce the flow resistance

the breather hole eccentricity design has the best eccentricity about 7.5mm.

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Related Institution

School of Mechanical Engineering,Liaoning Technical University

Shenyang Engine Research Institute,Aero Engine Corporation of China,Shengyang

School of Power and Energy,Northwestern Polytechnical University

National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics

北京航空航天大学能源与动力工程学院

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