【摘要】：軸流式壓氣機不但是燃氣輪機的三大核心部件之一,而且作為單獨的動力設(shè)備在工業(yè)、能源、化工等行業(yè)中具有舉足輕重的作用；所以壓氣機的設(shè)計一直以來都受到了高度的重視。在多級軸流壓氣機新的設(shè)計中,為了縮短設(shè)計周期、增加設(shè)計可靠性、降低設(shè)計成本,經(jīng)常在現(xiàn)有壓氣機的基礎(chǔ)上進行加零級設(shè)計來增加質(zhì)量流量或提高壓比從而得到滿足新要求的壓氣機。 本文分析了原壓氣機的性能、加級要求以及基于相似準則的加零級設(shè)計基本原理；討論了壓氣機加零級的設(shè)計流程以及加級匹配點的選擇、零級壓比和通流的確定,并在此基礎(chǔ)上進行了壓氣機零級的一維設(shè)計,從而得到零級各個截面的參數(shù)；通過零級的平面葉型選擇、對稱葉型厚度分布及中弧線的確定、葉型的扭轉(zhuǎn)設(shè)計等步驟完成了零級葉柵的三維設(shè)計 利用CFD計算軟件對所設(shè)計零級以及壓氣機加級前后共15條特性曲線各個工況點進行了計算。文章首先分析了因蝸殼造成的進氣不均勻的影響、壓氣機加級前后總體性能以及所設(shè)計零級的總體性能；并從相對氣流角、絕對氣流角、總壓壓比、反動度、折合流量、折合轉(zhuǎn)速等方面分析了加級前后的匹配情況;然后通過葉片型面靜壓分布、徑向加功量分布討論了葉片載荷的問題；通過葉片表面流線、S1流面的流線和馬赫數(shù)的比較分析了流場性能；通過葉頂泄露以及熵的比較,分析了壓氣機中損失的情況；最后分析了非設(shè)計工況下壓氣機加級前后的性能比較。通過以上分析可以看出,壓氣機加零級后質(zhì)量流量滿足了新的工作條件的要求,并具有良好的整體匹配性能,原壓氣機的流動狀況得到了改善,加級后的壓氣機具有更好的運行穩(wěn)定性。
[Abstract]:Axial flow compressor is not only one of the three core components of gas turbine, but also plays an important role in industrial, energy, chemical and other industries as a separate power equipment. So the design of compressor has been highly valued. In the new design of multistage axial flow compressor, in order to shorten the design period, increase the design reliability and reduce the design cost, The zero stage design is often carried out on the basis of the existing compressor to increase the mass flow rate or increase the pressure ratio to obtain a compressor that meets the new requirements. In this paper, the performance of the original compressor, the requirements of the adding stage and the basic principle of the zero-adding stage design based on the similarity criterion are analyzed, and the design flow of the zero-adding stage of the compressor and the selection of the matching point, the determination of the zero-stage pressure ratio and the flow passage are discussed. On this basis, the one-dimensional design of the zero stage of the compressor is carried out, and the parameters of each section of the zero stage are obtained, and the thickness distribution of the symmetrical blade and the determination of the middle arc are obtained through the plane blade shape selection of the zero stage. The three dimensional design of the zero cascade was completed by the torsional design of the blade shape. The design of zero stage and the compressor before and after the addition of the zero stage were calculated by using the CFD calculation software, and 15 characteristic curves were calculated at each working point of the designed zero stage and the compressor before and after the addition of the zero stage. This paper first analyzes the influence of the inlet air inhomogeneity caused by the volute, the overall performance of the compressor before and after adding the stage and the overall performance of the designed zero stage, and analyzes the relative air flow angle, the absolute air flow angle, the total pressure ratio, the reaction degree and the equivalent flow rate. The matching situation before and after adding grade is analyzed in the aspects of reduced speed and so on, and then the problem of blade load is discussed through the static pressure distribution of blade profile and radial power addition distribution. The flow field performance is analyzed by comparing the streamlines and Mach numbers on the surface of the blade, S1 and the blade surface, and the loss in the compressor is analyzed by comparing the leakage of the blade top and the entropy. Finally, the performance comparison of compressor before and after adding stage under off-design condition is analyzed. Through the above analysis, it can be seen that the mass flow rate of the compressor after adding zero stage meets the requirements of the new working conditions, and has good overall matching performance, and the flow condition of the original compressor has been improved. The added stage compressor has better operation stability.
【學(xué)位授予單位】：哈爾濱工程大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2011
【分類號】：TH453

【相似文獻】

中國期刊全文數(shù)據(jù)庫 前10條

1 蔣洪德;;加速推進重型燃氣輪機核心技術(shù)研究開發(fā)和國產(chǎn)化[J];動力工程學(xué)報;2011年08期

2 ;[J];;年期

3 ;[J];;年期

4 ;[J];;年期

5 ;[J];;年期

6 ;[J];;年期

7 ;[J];;年期

8 ;[J];;年期

9 ;[J];;年期

10 ;[J];;年期

中國重要會議論文全文數(shù)據(jù)庫 前2條

1 趙連會;何磊;徐強;崔耀欣;虎煜;;某型多級軸流壓氣機三維CFD流場分析及氣動優(yōu)化[A];中國動力工程學(xué)會透平專業(yè)委員會2011年學(xué)術(shù)研討會論文集[C];2011年

2 符嬈;雷勇;;基于HHT的壓氣機氣動失穩(wěn)檢測技術(shù)研究[A];2010航空試驗測試技術(shù)學(xué)術(shù)交流會論文集[C];2010年

中國博士學(xué)位論文全文數(shù)據(jù)庫 前2條

1 馬文生;多級軸流壓氣機氣動優(yōu)化設(shè)計研究[D];清華大學(xué);2009年

2 孫蘭昕;燃氣輪機濕壓縮性能與水滴運動研究[D];哈爾濱工程大學(xué);2012年

中國碩士學(xué)位論文全文數(shù)據(jù)庫 前8條

1 蔡留成;某型發(fā)動機風扇性能增長改進設(shè)計[D];電子科技大學(xué);2009年

2 黃t熽，

本文編號：2263563