【摘要】：隨著現(xiàn)代航空工業(yè)的不斷發(fā)展,微小型飛行器在現(xiàn)代軍事、民用領(lǐng)域得到了廣泛應(yīng)用,在不久的將來,微小型飛行器將在各個(gè)領(lǐng)域擔(dān)任越來越重要的角色。微小尺寸的發(fā)動(dòng)機(jī)是微型飛行器的心臟,其中壓氣機(jī)部件是發(fā)動(dòng)機(jī)極其重要的部件之一,因此,設(shè)計(jì)一款小尺寸、高壓比、高效率的高性能壓氣機(jī)是目前研究的重點(diǎn)之一。在微尺寸發(fā)動(dòng)機(jī)中,由于壓氣機(jī)的尺寸限制,對(duì)高精度制造難度較大,離心式壓氣機(jī)更為適宜,在制造難度上較低,此外,離心壓氣機(jī)單級(jí)壓比要遠(yuǎn)高于軸流式壓氣機(jī)。由于離心壓氣機(jī)的流場(chǎng)較軸流式壓氣機(jī)更為復(fù)雜,對(duì)于高壓比、高效率的壓氣機(jī),需要通過很好的控制內(nèi)部流動(dòng),同時(shí)考慮激波損失與附面層流動(dòng)分離等,設(shè)計(jì)難度極高,設(shè)計(jì)高性能的離心壓氣機(jī)有很大的研究?jī)r(jià)值。本文主要將應(yīng)用于16da N推力的一種微型渦噴發(fā)動(dòng)機(jī)中的離心壓氣機(jī)實(shí)施改型設(shè)計(jì),要求改型后壓氣機(jī)能夠達(dá)到20da N推力渦噴發(fā)動(dòng)機(jī)的使用要求,改型后壓氣機(jī)滿足給定設(shè)計(jì)指標(biāo)的各項(xiàng)性能要求。根據(jù)原型渦噴發(fā)動(dòng)機(jī)的離心壓氣機(jī)的結(jié)構(gòu),測(cè)量出壓氣機(jī)的葉型輪廓和通流通道的幾何數(shù)據(jù),利用三維建模軟件UG建立壓氣機(jī)的實(shí)體模型,最后利用三維流體計(jì)算軟件CFX對(duì)原型離心壓氣機(jī)進(jìn)行流場(chǎng)計(jì)算,得到設(shè)計(jì)點(diǎn)工況下原型離心壓氣機(jī)的內(nèi)部流場(chǎng)數(shù)據(jù)及總體性能參數(shù),與試驗(yàn)數(shù)值進(jìn)行對(duì)比,重點(diǎn)討論了造成內(nèi)部流動(dòng)嚴(yán)重?fù)p失及使流場(chǎng)趨于復(fù)雜紊亂流動(dòng)的原因,其中探討了尾跡、二次流、分離流的影響因素。接著,針對(duì)原型壓氣機(jī)的幾何外形尺寸,重新設(shè)計(jì)壓氣機(jī)部件,針對(duì)改型性能要求,改善壓氣機(jī)流動(dòng)方向的大折轉(zhuǎn)角度造成的惡劣分離流動(dòng),在不改變進(jìn)出口徑向尺寸的條件下,開展高壓比、高轉(zhuǎn)速、高效率的葉輪改型設(shè)計(jì);另外,由于原型擴(kuò)壓器結(jié)構(gòu)造成的嚴(yán)重的損失,流動(dòng)控制效果較差,重新設(shè)計(jì)了擴(kuò)壓器葉片形式及布置方式,重新進(jìn)行流場(chǎng)計(jì)算分析,將改型與原型進(jìn)行對(duì)比分析。最終設(shè)計(jì)結(jié)果表明,改型設(shè)計(jì)后離心壓氣機(jī)滯止等熵效率達(dá)到74.36%,流量達(dá)到0.4236kg/s,總壓比為4.136,較原型分別提高了12.67%、9.17%和18.17%,均達(dá)到了設(shè)計(jì)指標(biāo)。該型號(hào)離心壓氣機(jī)設(shè)計(jì)轉(zhuǎn)速達(dá)到125000r/min,轉(zhuǎn)速較高,在葉尖位置產(chǎn)生超音區(qū)域,在離心力和激波增壓共同作用下,提升了離心壓氣機(jī)的增壓能力。另外,改型后離心壓氣機(jī)出口參數(shù)更為均勻,葉頂處出口氣流角大幅減小,從整體來看,出口氣流角減小,均勻性提高。
[Abstract]:With the development of modern aviation industry, micro-aircraft has been widely used in modern military and civil fields. In the near future, micro-aircraft will play a more and more important role in various fields. Micro-sized engine is the heart of micro-aircraft, in which compressor component is one of the most important parts of the engine. Therefore, the design of a small size, high-pressure ratio, high-efficiency compressor is one of the most important research points at present. In micro-sized engine, because of the size limitation of compressor, it is difficult to manufacture high-precision compressor, centrifugal compressor is more suitable and less difficult to manufacture. In addition, the single-stage pressure ratio of centrifugal compressor is much higher than that of axial-flow compressor. Because the flow field of centrifugal compressor is more complicated than that of axial compressor, for high pressure ratio and high efficiency compressor, it is very difficult to design the compressor which needs to control the internal flow well and consider the separation of shock wave loss and boundary layer flow at the same time, it is very difficult to design the compressor with high pressure ratio and high efficiency. The design of high performance centrifugal compressor has great research value. In this paper, the centrifugal compressor used in a micro turbojet engine with 16da-N thrust is designed. It is required that the modified compressor can meet the requirements of the 20da-N thrust turbojet engine. The modified compressor meets the performance requirements of the given design index. According to the structure of the centrifugal compressor of the prototype turbojet engine, the geometric data of the blade profile and the passage of the compressor are measured, and the solid model of the compressor is established by using the 3D modeling software UG. Finally, the three-dimensional fluid calculation software CFX is used to calculate the flow field of the prototype centrifugal compressor, and the internal flow field data and the overall performance parameters of the prototype centrifugal compressor under the design point condition are obtained, which are compared with the experimental data. In this paper, the causes of serious loss of internal flow and the complicated and disturbed flow field are discussed, and the influencing factors of wake, secondary flow and separated flow are discussed. Then, according to the geometric dimensions of the prototype compressor, the compressor components are redesigned to improve the bad separation flow caused by the large rotation angle in the flow direction of the compressor according to the performance requirements of the modified compressor. The design of high pressure ratio, high speed and high efficiency impeller is carried out without changing the radial dimension of inlet and outlet. In addition, due to the serious loss caused by the structure of the prototype diffuser and the poor effect of flow control, the blade form and arrangement of the diffuser are redesigned, the flow field is calculated and analyzed again, and the contrast analysis is carried out between the retrofit and the prototype. The final design results show that the static Isentropic efficiency of centrifugal compressor is 74.36%, the flow rate is 0.4236 kg / kg, and the total pressure ratio is 4.136, which is 12.67%, 9.17% and 18.17% higher than the prototype, respectively. All of them have reached the design target. The centrifugal compressor has a design speed of 125 000 r / min and a high speed. The supersonic region is produced at the tip position of the centrifugal compressor. Under the combined action of centrifugal force and shock wave pressurization, the turbocharging capacity of the centrifugal compressor is improved. In addition, the outlet parameters of the modified centrifugal compressor are more uniform, and the outlet gas flow angle at the top of the blade decreases greatly. As a whole, the outlet gas flow angle decreases and the uniformity of the centrifugal compressor increases.
【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2015
【分類號(hào)】：V233

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