多级透平试验模化准则研究  

Investigation on test modeling criteria for multistage turbine

作　　者：石䶮 周晟鋆 黄单 彭生红 SHI Yan;ZHOU Shengyun;HUANG Dan;PENG Shenghong(China United Gas Turbine Technology Company Limited,State Power Investment Corporation,Shanghai 200131,China)

机构地区：[1]国家电力投资集团有限公司中国联合重型燃气轮机技术有限公司,上海200131

出　　处：《航空动力学报》2024年第9期450-459,共10页Journal of Aerospace Power

摘　　要：为提升多级透平中温模化试验的流场相似性,构建并校验了两级透平三维数值模型,定量研究试验模化准则选取对流场相似性的影响,提出了一种调整工质比热比的新方法。结果表明:中温模化条件下的工质比热比与设计值不相等,导致多级透平流场相似性沿流动方向逐渐下降;保证膨胀比模化准则时,末级透平动叶气动载荷系数降低4.78%,出口气流角偏差达3°~5°;保证折合功率模化准则时,末级透平折合转速偏大1.29%,动叶气膜冷气出流背压下降2.5%~6.5%;将空气燃烧转变为燃气再与水蒸气掺混,可以得到与不同等级重型燃气轮机真实燃气比热比相等的试验工质;在中温试验条件下使用该工质,多级透平的折合转速、折合功率、膨胀比相等3个模化准则同时满足,气动参数与设计值偏差不超过-0.54%~0.52%。For the improvement of the flow field similarity in multi-stage turbine modeling tests operating at medium temperature level,a three-dimensional numerical model of a two-stage turbine was constructed and validated.The influence of the test modeling criteria selection on the flow field similarity was quantitatively studied and a new method for adjusting the specific heat ratio of working fluid was proposed.Results indicated that,the specific heat ratio of working fluid under medium temperature modeling conditions was not equal to the design value,resulting in a gradual decrease of the flow field similarity along the flow direction in the multi-stage turbine;When ensuring the similarity criterion of expansion ratio,the aerodynamic load coefficient of the last stage turbine blade was reduced by 4.78%,and the blade outlet flow angle deviated by 3°—5°;When ensuring the similarity criterion of corrected power,the corrected speed of the last turbine stage is 1.29%higher,and the back pressure for the film cooling flow of the blade decreased by 2.5%—6.5%;The test working fluid generated by combusting air into a gas and mixing with vapor had the same values of specific heat ratio to the real gas used in the different classes of heavy duty gas turbine.As this working fluid was used in the test condition at medium temperature level,the three modeling criteria including the corrected speed,the corrected power and the expansion ratio were satisfied together,and the deviation of aerodynamic parameters from the design values were within the range of-0.54%to 0.52%.

关 键 词：多级透平试验 模化准则 相似性 工质物性 比热比 气动载荷 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]