用于微型涡轮机的节流孔式静压气浮轴承实验

黄国平; 王跃; 梁德旺

用于微型涡轮机的节流孔式静压气浮轴承实验

南京航空航天大学微型发动机研究所, 210016

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出版历程
- 收稿日期: 2007-08-20
- 修回日期: 2007-12-10
- 刊出日期: 2008-03-28

Experiment investigation of throttle hole aerostatic bearing of micro turbine engine

The Institute of Micro-Engine, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 对用于厘米级微型涡轮发动机的径向静压气浮轴承展开了实验研究,分析了长径比、节流孔径、气膜间隙及供气压力等对承载力、刚度和耗气量的影响.提出了这些设计参数的优选方法,并结合直径11 cm的某微型喷气发动机,给出了与之匹配的径向静压气浮轴承设计方案:工作面直径15 mm、长度17.5 mm、节流孔径0.35 mm、气膜间隙25μm.此方案在供气绝对压力2.5 kPa时,双轴承支撑能力为13.72 N,耗气量小于1.0 g/s,有效地满足了微型涡轮发动机要求.
- 航空、航天推进系统 /
- 静压气浮轴承 /
- 微型涡轮发动机 /
- 径向轴承 /
- 设计参数 /
- 实验
Abstract: Miniature aerostatic journal air bearings used in Micro-turbine engine was studied by experiment in this paper,while the effects of ratio of length to diameter,orifice,clearance of journal air bearing and supply pressure on the characters of journal air bearing were analyzed.The optimum methods for selecting these parameters were presented.An aerostatic bearing for a micro turbine engine(diameter about 11 cm) was designed: diameter: 15 mm,length: 17.5 mm,orifice: 0.35 mm,and clearance: 30 μm.When the air feed pressure is 2.5 kPa,the bearing can load 13.72 N,and the air feed is less than1.0 g/s.The aerostatic bearing designed in this paper can meet the needs of 11 cm micro turbine engine.
- aerospace propulsion system /
- aerostatic bearings /
- micro turbine engine /
- journal bearings /
- design parameter /
- experiment

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参考文献(8)

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