节流通风的航空发动机轴承腔腔压计算方法

郁丽; 李国权

节流通风的航空发动机轴承腔腔压计算方法

郁丽^1,2,
李国权^1,2

1.
中国航空工业集团公司沈阳发动机设计研究所, 沈阳 110015
2.
中国航空工业集团公司航空发动机动力传输航空科技重点实验室, 沈阳 110015

计量
- 文章访问数: 1296
- HTML浏览量: 2
- PDF量: 503
- 被引次数: 0
出版历程
- 收稿日期: 2011-11-29
- 刊出日期: 2012-11-28

Calculatation method of bearing chamber pressure for aero-engine throttling vent lubrication system

YU Li^1,2,
LI Guo-quan^1,2

1.
Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China
2.
Key Laboratory for Power Transmission Technology of Aero-Engine, Aviation Industry Corporation of China, Shenyang 110015, China

摘要

摘要: 为解决节流通风的航空发动机轴承腔的腔压难以计算的问题,考虑节流孔处通风介质可压缩性,结合某典型节流通风轴承腔的实例,分析了节流通风的发动机轴承腔通风气体流动的特点,提出了其腔压计算方法.通过实例计算,结果表明:计算值与试验值的绝对误差较小,结果满足滑油系统与空气系统联合计算的工程需要.该计算方法可为节流通风的航空发动机轴承腔腔压计算提供参考.
- 航空发动机 /
- 滑油系统 /
- 通风系统 /
- 节流通风 /
- 轴承腔
Abstract: The compressibility of the ventilation in the orifice should be considered in the calculation process.A representative bearing chamber for throttling vent lubrication system was studied,and gas flowing characteristics of bearing chamber of aero-engine throttling vent system was analyzed.The calculation method of bearing chamber pressure was concluded and validated by a real case.Compared with experimental data,the calculation result shows a low absolute error which can meet the requirements of the engineering.This calculation method can be used as a reference for further calculation of the pressure of aeroengine bearing chamber by throttling.
- aero-engine /
- lubrication system /
- vent system /
- throttling vent /
- bearing chamber

HTML

参考文献(15)

[1]	林基恕,张振波.21世纪航空发动机动力传输系统的展望[J].航空动力学报,2001,16(2):108-114. LIN Jishu,ZHANG Zhenbo.Prospects of aeroengine power transmission system in the 21st century[J].Joumal of Aerospace Power,2001,16(2):108-114.(in Chinese)
[2]	林基恕.高性能涡轮发动机润滑系统设计[J].燃气涡轮试验与研究,2003,16(1):7-9,17. LIN Jishu.Design of high performance turbo-engine lubrication systems[J].Gas Turbine Experiment and Research,2003,16(1):7-9,17.(in Chinese)
[3]	李国权,史妍妍,曹家梅.航空发动机传动腔压力计算方法的探讨.沈阳:辽宁省航空学会动力装置专业第十五届学术交流会,2000.
[4]	史妍妍.某型发动机润滑系统腔压计算与三维两相流动分析 [D].沈阳:东北大学,2009. SHI Yanyan.Calculation and analyse on the gas-liquid two-phase 3-D flow of chamber pressure for an aeroengine lubrication system [D].Shangyang:Northeastern University,2009.(in Chinese)
[5]	邢宗文.流体力学基础[M].西安:西北工业大学出版社,1992.
[6]	林基恕,航空燃气涡轮发动机机械系统设计[M].北京:航空工业出版社,2005.
[7]	Vermes G A.Fluid mechanics approach to the labyrinth seal leakage problem[J].ASME Journal of Engineering for Power,1961,83(2):161-169.
[8]	Miller D S.Internal flow systems[M].Britain:British Hydromechanics Research Association,1970.
[9]	纪国剑.航空发动机典型篦齿封严泄漏特性的数值和实验研究 [D].南京:南京航空航天大学,2008. JI Guojian.Numerical and experimental investigation of sealing characteristics on typical labyrinth seals in aeroengine [D].Nanjing:Nanjing University of Aeronautics and Astronautics,2008.(in Chinese)
[10]	Glahn A,Kurreck M,Willmann M,et al.Feasibility study on oil droplet flow investigations inside aero engine bearing chambers-PDPA techniques in combination with numerical approaches[J].Journal of Engineering for Gas Turbines and Power,1996,118(10):749-755.
[11]	Flouros M.Analytical and numerical simulationg of the two-phase flow heat transfer in the vent and seavenge pipes of the CIEAN engine demonstrator[J].Journal of Turbomachinery,2010,132(1):011008.1-011008.15.
[12]	Rodkey S C,Heister S D, Collicott S H.Physics of gas tubine engine bearing chambers [R].AIAA-2007-5033,2007.
[13]	葛治美,韩振兴,张恩和,等.航空发动机轴承腔热分析计算[J].航空动力学报,2005,20(3):483-486. GE Zhimei,HAN Zhenxing,ZHANG Enhe,et al.Thermal analysis of aeroengine bearing compartment[J].Journal of Aerospace Power,2005,20(3):483-486.(in Chinese)
[14]	方弘毅,徐让书,王娟娟.航空发动机轴承腔内油气两相分布数值计算[J].沈阳航空工业学院学报,2010,27(5):14-17. FANG Hongyi,XU Rangshu,WANG Juanjuan.Numerical simulation of two-phase air/oil distribution in aero-engine bearing chamber[J].Journal of Shenyang Institute of Aeronautical Engineering,2010,27(5):14-17.(in Chinese)
[15]	田文正,李国权.某型机滑油发动通风节流嘴流量-阻力特性试验研究[J].航空发动机,2010,36(5):56-58. TIAN Wenzheng,LI Guoquan.Experimental study of choke flow-drag characteristics for an aeroengine lubrication throttling vent system[J].Aeroengine,2010,36(5):56-58.(in Chinese)