本文選題：航空泛擺線滑油泵 + 高轉(zhuǎn)速轉(zhuǎn)子��； 參考：《南昌航空大學(xué)》2015年碩士論文

【摘要】：滑油泵作為航空發(fā)動機滑油系統(tǒng)的重要組成部件,主要用于發(fā)動機軸承和傳動齒輪部分潤滑油的輸送和回收。由于泛擺線油泵具有結(jié)構(gòu)緊湊、體積小、重量輕、填充性好、壓力脈動小等特點。在國內(nèi)外眾多學(xué)者對其成型方式,工作特性及容積效率等方面研究的基礎(chǔ)上。目前,我國和歐美一些發(fā)達國家的航空發(fā)動機上已經(jīng)開始廣泛應(yīng)用泛擺線油泵。提高泛擺線滑油泵的轉(zhuǎn)速,可以減小轉(zhuǎn)子的幾何尺寸,使油泵的體積減小。在相同轉(zhuǎn)子配合間隙的條件下,提高內(nèi)轉(zhuǎn)子轉(zhuǎn)速,能起到增強節(jié)流的作用,從而減少泄漏,提高容積效率。由于航空發(fā)動機滑油泵一般是由發(fā)動機附件機匣或主軸傳動。提高轉(zhuǎn)速,能有效減少變速結(jié)構(gòu)重量,從而達到減輕發(fā)動機重量的效果。但是在航空泛擺線泵轉(zhuǎn)子參數(shù)選擇方面,我國目前主要采取測繪、試湊的方式,沒有一套完整適當(dāng)?shù)姆椒āＴ趯嶋H應(yīng)用中發(fā)現(xiàn)泛擺線滑油泵在高轉(zhuǎn)速條件下,易出現(xiàn)因不合理的進、出油槽結(jié)構(gòu)設(shè)計而導(dǎo)致油液充填不良和出現(xiàn)氣穴的問題,從而嚴(yán)重影響泛擺線泵的容積效率、流量脈動率等性能,制約其高轉(zhuǎn)速化發(fā)展。本文在了解泛擺線泵成型原理及工作原理的基礎(chǔ)上,分析了影響泛擺線泵性能的重要因素。并在前人的基礎(chǔ)上,根據(jù)航空滑油泵設(shè)計步驟及驗收要求,改善了先前設(shè)計方法難以達到高轉(zhuǎn)速壽命要求的問題,首次提出了以體積最小為設(shè)計目標(biāo),并將流量及滑動系數(shù)加入作為性能約束,提供了一種綜合考慮了轉(zhuǎn)速和齒寬影響的轉(zhuǎn)子設(shè)計方法。為推動泛擺線滑油泵向高轉(zhuǎn)速化方向發(fā)展,采用CFD方法,開展流體結(jié)構(gòu)耦合研究,對高轉(zhuǎn)速下,泛擺線泵進、出油槽結(jié)構(gòu)對其性能的影響進行優(yōu)化仿真分析及試驗驗證。通過研究高轉(zhuǎn)速條件下,泛擺線滑油泵進、出油槽結(jié)構(gòu)對泵容積效率影響的敏感性關(guān)系,發(fā)現(xiàn)在容積效率方面,多種轉(zhuǎn)速下對角式油槽結(jié)構(gòu)皆比其它兩種油槽結(jié)構(gòu)要高。在此基礎(chǔ)上,針對高轉(zhuǎn)速滑油泵工作特點,進一步優(yōu)化發(fā)現(xiàn),在進、出口中心線偏轉(zhuǎn)25°左右時,內(nèi)轉(zhuǎn)子轉(zhuǎn)速為15000r/min的泛擺線滑油泵地面容積效率略微下降,高空容積效率最高。保持偏轉(zhuǎn)角度和轉(zhuǎn)速不變的條件下,油槽深度取4.9mm附近時最為合適。在保證容積效率的前提下,對比得出,單級泵采用同時溝通進、出油槽的方式在降低流量脈動方面能夠獲得更好的效果。進一步分析發(fā)現(xiàn),內(nèi)轉(zhuǎn)子轉(zhuǎn)速為15000r/min時,地面狀態(tài)下,進、出油槽較小的溝通面積和較大的油槽間距對容積效率及流量脈動改善效果不大,而過大的溝通面積和過小的油槽間距則會嚴(yán)重影響泵的性能。高空狀態(tài)下,泛擺線泵實際流量最大值出現(xiàn)在溝通面積為:7.03~8.85 mm2之間,油槽間距:1.9~2.5mm之間,較不溝通的情況,提高約10%。高空狀態(tài)下流量脈動最小值出現(xiàn)在溝通面積為:5.19~8.85 mm2之間,油槽間距:2.5~3.1mm之間,較不溝通的情況,下降約13%。兩級泵的錯相位法可以使流量脈動降低約40%。為以后航空滑油泵的設(shè)計提供參考依據(jù)。
[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.
【學(xué)位授予單位】：南昌航空大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：V233.4

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相關(guān)期刊論文 前1條

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本文編號：2010703