压气机中介机匣几何结构的试验验证

李斌; 吴亚东; 滕金芳; 杜朝辉

压气机中介机匣几何结构的试验验证

上海交通大学航空航天学院, 上海 200240

基金项目: 国家自然科学基金(51076101)

计量
- 文章访问数: 1254
- HTML浏览量: 0
- PDF量: 1016
- 被引次数: 0
出版历程
- 收稿日期: 2012-09-29
- 刊出日期: 2013-10-28

Experimental validation of geometry of compressor intermediate casing

School of Aeronautics and Astronautics, Shanghai Jiaotong University, Shanghai 200240, China

摘要

摘要: 对4个压气机中介机匣试验件进行了试验研究,包括原型、优化模型、支板根部前掠及流道延长4种方案.试验利用压力扫描阀及气动探针对试验件进出口总温、总压,上下壁面,大支板50%叶高处的静压进行测量,分析几何结构对中介机匣性能的影响.试验结果表明:增加流道轴向距离可提高中介机匣性能;优化后中介机匣壁面型线可改善进出口总压分布;下壁面型线对流动加减速有重要影响,优化后压力分布较平稳;优化需考虑支板影响.
- 中介机匣 /
- 支板 /
- 几何结构 /
- 压力梯度 /
- 流道曲率
Abstract: Four kinds of intermediate casings were tested experimentally,including the original model,optimization model,and two models based on optimization model respectively.The length of the strut's chord and the flow path were changed for the last two models.Inlet and outlet total temperature,inlet and outlet total pressure,static pressure of outer and inner wall,static pressure of middle struct along 50% spanwise were measured by pneumatic intelligent pressure scanner and pressure probe,and the effects of the geometry structure on the intermediate casing's aerodynamic performance were evaluated.The results shows that:increase of the duct's axial distance can improve the performance of intermediate casing;the optimized intermediate casing profile can improve the pressure distribution in inlet and outlet;the inner wall profile has a significant impact on the acceleration and deceleration of flow,and optimized pressure distribution is relatively smooth;the geometry of the struts should be considered in optimization.
- intermediate casing /
- strut /
- geometry structure /
- pressure gradient /
- flow path curvature

HTML

参考文献(16)

[1]	向宏辉,张良,陆庆飞,等.进气条件对压气机中介机匣流场影响的试验研究[J].燃气涡轮试验与研究,2011,24(4):15-19. XIANG Honghui,ZHANG Liang,LU Qingfei,et al.Experimental investigation of inlet conditions' effect on compressor intermediate casing flow field[J].Gas Turbine Experiment and Research,2011,24(4):15-19.(in Chinese)
[2]	Bailey D W,Britchford K M,Carrotte J F,et al.Performance assessment of an annular S-shaped duct [R].ASME Paper 95-GT-242,1995.
[3]	Bailey D W,Carrotte J F.The influence of inlet swirl on the flow within an annular S-shaped duct [R].ASME Paper 96-GT-60,1996.
[4]	Gőttlich E,Marn A,Malzacher F,et al.On flow separation in a super-aggressive intermediate turbine duct. [EB/OL].[2012-9-08].http:[C]//www.mtu.de/en/technologies/enginee-ring_news/ develoment/Malzacher_On_Flow_Separation _en.pdf.
[5]	Wallin F,Eriksson L E.Response surface-based transition duct shape optimization [R].ASME Paper GT2006-90978,2006.
[6]	Dueñas C O,Miller R J,Hodson H P,et al.Effect of length on compressor inter-stage duct performance [R].ASME Paper GT2007-27752,2007.
[7]	Karakasis M K,Naylor E J,Miller R J,et al.The effect of an upstream compressor on a nonaxisymmetric S-duct [R].ASME Paper GT2010-23404,2010.
[8]	Naylor E M J,Urtiz D C,Miller R J,et al.Optimization of nonaxisymmetric endwalls in compressor S-shaped ducts[J].Journal of Turbomachinery,2010,132(1):011011.1-011011.10.
[9]	Walker A D,Barker A G,Carrotte J F.Integrated OGV design for an aggressive S-shaped compressor transition duct [R].ASME Paper GT2011-45627,2011.
[10]	Walker A D,Barker A G,Carrotte J F.Numerical design and experimental evaluation of an aggressive S-shaped compressor transition duct with bleed[R].ASME Paper GT2011-45628,2011.
[11]	阙晓斌,侯安平,周盛.基于壁面压力梯度控制的压气机S形过渡段设计[J].航空学报,2010,31(3):460-465. QUE Xiaobin,HOU Anping,ZHOU Sheng.S-shaped compressor transition duct design based on wall pressure gradient control[J].Acta Aeronautica et Astronautica Sinica,2010,31(3):460-465.(in Chinese)
[12]	安柏涛,韩万金,王松涛,等.大扩张角子午流道型线对损失的影响[J].推进技术,2001,22(3):211-214. AN Baitao,HAN Wanjin,WANG Songtao,et al.Effects of diffused meridional passage contour on loss[J].Journal of Propulsion Technology,2001,22(3):211-214.(in Chinese)
[13]	孙志刚.某型燃机涡轮过渡段流场优化设计[D].哈尔滨:哈尔滨工业大学,2006. SUN Zhigang.Optimization design for the turbine transition section of an aeroengine [D].Harbin:Harbin Institute of Technology,2006.(in Chinese)
[14]	孙志刚,黄洪雁,谭春青,等.某型燃机涡轮过渡段流场优化设计[J].工程热物理学报,2008,29(6):940-942. SUN Zhigang,HUANG Hongyan,TAN Chunqing,et al.Optimization design for the turbine transition section of an aeroengine[J].Journal of Engineering Thermophysics,2008,29(6):940-942.(in Chinese)
[15]	唐洪飞,黄洪雁,韩万金.大子午扩张涡轮过渡段的子午型线[J].推进技术,2009,30(4):439-445. TANG Hongfei,HUANG Hongyan,HAN Wanjin.Meridional passage contour of a large meridional expansion turbine[J].Journal of Propulsion Technology,2009,30(4):439-445.(in Chinese)
[16]	WU Yadong,LI Bin,TENG Jinfang.Automated design optimization and experimental validation for intermediate casing duct of aeroengine[R].ASME Paper GT2013-94137,2013.