高转速航空泛摆线滑油泵的研究

发布时间：2018-06-12 18:47

本文选题：航空泛摆线滑油泵 + 高转速转子　；参考：《南昌航空大学》2015年硕士论文

【摘要】：滑油泵作为航空发动机滑油系统的重要组成部件,主要用于发动机轴承和传动齿轮部分润滑油的输送和回收。由于泛摆线油泵具有结构紧凑、体积小、重量轻、填充性好、压力脉动小等特点。在国内外众多学者对其成型方式,工作特性及容积效率等方面研究的基础上。目前,我国和欧美一些发达国家的航空发动机上已经开始广泛应用泛摆线油泵。提高泛摆线滑油泵的转速,可以减小转子的几何尺寸,使油泵的体积减小。在相同转子配合间隙的条件下,提高内转子转速,能起到增强节流的作用,从而减少泄漏,提高容积效率。由于航空发动机滑油泵一般是由发动机附件机匣或主轴传动。提高转速,能有效减少变速结构重量,从而达到减轻发动机重量的效果。但是在航空泛摆线泵转子参数选择方面,我国目前主要采取测绘、试凑的方式,没有一套完整适当的方法。在实际应用中发现泛摆线滑油泵在高转速条件下,易出现因不合理的进、出油槽结构设计而导致油液充填不良和出现气穴的问题,从而严重影响泛摆线泵的容积效率、流量脉动率等性能,制约其高转速化发展。本文在了解泛摆线泵成型原理及工作原理的基础上,分析了影响泛摆线泵性能的重要因素。并在前人的基础上,根据航空滑油泵设计步骤及验收要求,改善了先前设计方法难以达到高转速寿命要求的问题,首次提出了以体积最小为设计目标,并将流量及滑动系数加入作为性能约束,提供了一种综合考虑了转速和齿宽影响的转子设计方法。为推动泛摆线滑油泵向高转速化方向发展,采用CFD方法,开展流体结构耦合研究,对高转速下,泛摆线泵进、出油槽结构对其性能的影响进行优化仿真分析及试验验证。通过研究高转速条件下,泛摆线滑油泵进、出油槽结构对泵容积效率影响的敏感性关系,发现在容积效率方面,多种转速下对角式油槽结构皆比其它两种油槽结构要高。在此基础上,针对高转速滑油泵工作特点,进一步优化发现,在进、出口中心线偏转25°左右时,内转子转速为15000r/min的泛摆线滑油泵地面容积效率略微下降,高空容积效率最高。保持偏转角度和转速不变的条件下,油槽深度取4.9mm附近时最为合适。在保证容积效率的前提下,对比得出,单级泵采用同时沟通进、出油槽的方式在降低流量脉动方面能够获得更好的效果。进一步分析发现,内转子转速为15000r/min时,地面状态下,进、出油槽较小的沟通面积和较大的油槽间距对容积效率及流量脉动改善效果不大,而过大的沟通面积和过小的油槽间距则会严重影响泵的性能。高空状态下,泛摆线泵实际流量最大值出现在沟通面积为:7.03~8.85 mm2之间,油槽间距:1.9~2.5mm之间,较不沟通的情况,提高约10%。高空状态下流量脉动最小值出现在沟通面积为:5.19~8.85 mm2之间,油槽间距:2.5~3.1mm之间,较不沟通的情况,下降约13%。两级泵的错相位法可以使流量脉动降低约40%。为以后航空滑油泵的设计提供参考依据。
[Abstract]:As an important component of the lubricating oil system of the aero engine, the lubricating oil pump is mainly used for transporting and recovering part of the lubricating oil of the engine bearing and transmission gear. Because the pan cycloid oil pump has the characteristics of compact structure, small volume, light weight, good filling, and small pressure pulsation, many scholars at home and abroad have the characteristics and capacity of its molding. At present, the pan cycloid oil pump has been widely used in the aero engines of China and some developed countries in Europe and America. To improve the rotational speed of the pan cycloid oil pump, the geometric size of the rotor can be reduced and the volume of the oil pump is reduced. The speed of the inner rotor can be raised under the condition of the same rotor clearance and the speed of the inner rotor can be raised. To increase the function of throttling to reduce the leakage and increase the volume efficiency. Since the aeroengine oil pump is usually driven by the engine accessory box or the spindle, it can effectively reduce the weight of the variable speed structure and reduce the weight of the engine. However, in the choice of the rotor parameters of the aero cycloidal pump, our country is the main body. In the practical application, it is found that under the conditions of high rotational speed, it is easy to cause the problem of poor filling and cavitation, which will seriously affect the volume efficiency of the pan cycloid pump and the rate of flow pulsation. On the basis of understanding the principle and working principle of the forming of the pan cycloid pump, this paper analyzes the important factors affecting the performance of the pan cycloid pump. On the basis of the predecessors, according to the design steps and acceptance requirements of the aviation oil pump, the problem that the previous design method is difficult to meet the high speed life requirement is improved for the first time. A design method is presented, which takes the minimum volume as the design objective, and adds the flow and sliding coefficient as the performance constraint. It provides a rotor design method which takes into account the influence of the speed and the tooth width. In order to promote the high rotational speed of the pan cycloid oil pump, the CFD method is used to carry out the coupling study of the flow body structure, and to pump the pan cycloid pump at the high speed. The effect of the oil outlet structure on its performance is optimized and simulated and tested. By studying the sensitivity relationship between the flooding pump and the effect of the oil outlet structure on the pump volume efficiency under the high speed conditions, it is found that the diagonal oil groove structure is higher than the other two kinds of oil groove structures at a variety of rotational speeds. At the same time, according to the working characteristics of the high speed skating oil pump, it is found that the surface volume efficiency of the pan cycloid oil pump with the inner rotor speed of 15000r/min is slightly decreased and the high altitude volume efficiency is the highest when the center line of the outlet is deflected at about 25 degrees, and the tank depth is most close to the 4.9mm when the deflection angle and speed are kept unchanged. Well. On the premise of guaranteeing the volume efficiency, it is concluded that the single stage pump can get better effect in reducing the flow pulsation by means of simultaneous communication and the way of the oil outlet to reduce the flow pulsation. Further analysis has found that when the rotor speed is 15000r/min, the small communication area and the larger tank spacing are the same to the volume efficiency. And the flow pulsation improvement is not very effective, and the excessive communication area and the small distance between the oil tank will seriously affect the performance of the pump. In the high altitude condition, the maximum actual flow rate of the pan cycloid pump occurs in the communication area between 7.03~8.85 mm2, the spacing of the oil slot, between the 1.9~2.5mm, and the situation of no communication, and increases the flow pulsation in the state of about 10%. high altitude. The minimum value appears in the communication area: 5.19~8.85 mm2, oil slot spacing: between 2.5~3.1mm and no communication, and the error phase method of decreasing about 13%. two level pump can reduce the flow pulsation by about 40%. to provide reference for the design of the aviation oil pump in the future.
【学位授予单位】：南昌航空大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V233.4

【参考文献】