燃气涡轮试验与研究
燃氣渦輪試驗與研究
연기와륜시험여연구
GAS TURBINE EXPERIMENT AND RESEARCH
2014年
2期
1-5
,共5页
航空发动机%风扇%压气机%高效设计%全三维计算%参数分析%单级设计
航空髮動機%風扇%壓氣機%高效設計%全三維計算%參數分析%單級設計
항공발동궤%풍선%압기궤%고효설계%전삼유계산%삼수분석%단급설계
aero-engine%fan%compressor%high-efficiency design%3D computation%parameter analysis%single stage design
以某三级风扇为例，将其拆分为第一级、前两级和后两级进行三维计算，然后取第一级和两级联算后一级的计算结果与三级联算结果进行对比。分析发现，采用此方式计算的各级气动流场与三级联算结果基本一致，通过此种计算方式可获取符合整个部件联算的各单级性能，为多级风扇/压气机设计提供参考和依据。这也揭示了在多级风扇/压气机设计过程中，可通过该方式以每级作为单元体进行设计，从而大大节省时间、提高设计效率。为验证算法的可行性，以七级高压压气机为例进行了验算，结果表明该方法合理可行。
以某三級風扇為例，將其拆分為第一級、前兩級和後兩級進行三維計算，然後取第一級和兩級聯算後一級的計算結果與三級聯算結果進行對比。分析髮現，採用此方式計算的各級氣動流場與三級聯算結果基本一緻，通過此種計算方式可穫取符閤整箇部件聯算的各單級性能，為多級風扇/壓氣機設計提供參攷和依據。這也揭示瞭在多級風扇/壓氣機設計過程中，可通過該方式以每級作為單元體進行設計，從而大大節省時間、提高設計效率。為驗證算法的可行性，以七級高壓壓氣機為例進行瞭驗算，結果錶明該方法閤理可行。
이모삼급풍선위례，장기탁분위제일급、전량급화후량급진행삼유계산，연후취제일급화량급련산후일급적계산결과여삼급련산결과진행대비。분석발현，채용차방식계산적각급기동류장여삼급련산결과기본일치，통과차충계산방식가획취부합정개부건련산적각단급성능，위다급풍선/압기궤설계제공삼고화의거。저야게시료재다급풍선/압기궤설계과정중，가통과해방식이매급작위단원체진행설계，종이대대절성시간、제고설계효솔。위험증산법적가행성，이칠급고압압기궤위례진행료험산，결과표명해방법합리가행。
The first stage, the first two stages and the last two stages of a three-stage fan were simulated. Then the results of the first stage and the second stage of the two-stage computation were compared with that of three-stage computation. It is found that the internal flow field of each stage is similar to that of three-stage calculation. By this method, parameters of every stage which was consistent with the whole fan/compressor performance could be obtained to provide a basis for the future multistage fan/compressor de-sign. It indicates that during the design of multi-stage fan/compressor, each stage can be designed as a unit to save time and improve the efficiency. A seven-stage compressor has been computed for example to testify the feasibility of this method.
