某大负荷涡轮过渡段设计探索

谭洪川; 卫刚; 周山; 罗华玲; 李剑白

doi:10.13224/j.cnki.jasp.2017.07.030

某大负荷涡轮过渡段设计探索

doi: 10.13224/j.cnki.jasp.2017.07.030

1.
中国航空发动机集团有限公司四川燃气涡轮研究院，成都 610500
2.
中国航空发动机集团有限公司商用航空发动机有限责任公司，上海 201108

计量
- 文章访问数: 670
- HTML浏览量: 2
- PDF量: 422
- 被引次数: 0
出版历程
- 收稿日期: 2015-10-22
- 刊出日期: 2017-07-28

Design exploration of a highly loading intermediate transition duct of turbine

摘要

摘要: 对某大负荷过渡段进行了探索设计和数值模拟。对比分析表明：在支板数很少的情况下，支板厚度分布对主流区的流动影响很小，主要通过叶型曲率分布来影响支板表面逆压梯度和分离。凹曲率和凸曲率搭配可以有效控制轮毂、机匣和支板叶尖的流动分离。可以通过支板周向倾斜改变支板叶型在S1流面的安装角，从而起到改变攻角效应和控制流动分离的作用。在条件允许的情况下应尽可能将支板部分或全部置于主流逆压梯度较小的区域以减小支板表面压力梯度和分离风险。
- 过渡段(ITD) /
- 壁面曲率 /
- 支板(SV) /
- 逆压梯度 /
- 大负荷
Abstract: Aerodynamic design and numerical simulation were carried out to investigate a intermediate transition duct (ITD). Results of the analyses and comparisons showed that the thickness distribution of ITD strut vane(SV) had little impact on the main flow when SV number was small，while the pressure gradient and separation of SV surface were affected mainly through the profile curvature distribution. The flow separation in the region of hub, shroud and SVs tip was controlled effectively with the combination of concave and convex curvature. The stagger angles of the SV on S1 stream surface were changed by circumferential lean to impact the effect of attack angle and depress the flow separation. The SV should be placed in the main flow with low pressure gradient as more as possible no matter part or all to decrease the pressure gradient and risk of flow separation.
- intermediate transition duct (ITD) /
- wall curvature /
- strut vane (SV) /
- adverse pressure gradient /
- highly loading

HTML

参考文献(18)

[1]	曹玉璋，陶智，徐国强.航空发动机传热学［M］.北京:北京航空航天大学出版社,2005.
[2]	DAVID J,NICHOLAS C.Diffuser design technology［M］.Norwich,Vermont:Concepts ETI Incorporation,1998.
[3]	DOMINY R G,KIRKHAM D A.The influence of blade wakes on the performance of inter-turbine diffusers［J］.Journal of Turbomachinery,1996,118(2):347-352.
[4]	SANZ W M,KELTERER R,PECNIK1 A,et al.Numerical investigation of the effect of tip leakage flow on an aggressive S-shaped intermediate turbine duct［R］.ASME Paper GT2009-59535,2009.
[5]	DOMINY R G,KIRKHAM D A,SMITH A D.Flow development through inter-turbine diffusers［R］.ASME Paper 96-GT-139,1996.
[6]	WALLIN F,ERIKSSON L E.Response surface-based transition duct shape optimization［R］.ASME Paper GT2006-90978,2006.
[7]	SERGIO L.Aerodynamic analysis of an innovative low pressure Turbine vane placed in a S-shaped duct［J］.Journal of Turbomachinery,2012,134(4):632-640.
[8]	WALLIN F,ERIKSSON L E.Design of an aggressive flow-controlled turbine duct\[R\].ASME Paper GT2008-51202,2008.
[9]	MARN A,GTTLICH E,PECNIK R,et al.The influence of blade tip gap variation on the flow through an aggressive S-shaped intermediate turbine duct downstream of a transonic turbine stage:Part Ⅰ time-averaged results［R］.ASME Paper GT2007-27405,2007.
[10]	AXELSSON L U,JOHANSSON T G.Experimental investigation of the time-averaged flow in an intermediate turbine duct［R］.ASME Paper GT2008-50829,2008.
[11]	WALLIN F.Experimental and numerical investigation of an aggressive intermediate turbine duct:Part Ⅰ flowfield at design inlet conditions［R］.AIAA-2008-7055,2008.
[12]	MILLER R J,MOSS R W,AINSWORTH R W,et al.The development of turbine exit flow in a swan-necked inter-stage diffuser［R］.ASME Paper GT2003-38174,2003.
[13]	GTTLICH E.Research on the aerodynamics of intermediate turbine diffusers［J］.Progress in Aerospace Sciences,2011,47(4):249-279.
[14]	GIEL P W.Fundamental aeronautics subsonic fixed wing project aerothermodynamics discipline (NASA/GE highly-loaded turbine research program)［R］.Cleveland,Ohio:AIAA TETWoG Meeting,2008.
[15]	SOVRAN G,KLOMP E D.Experimentally determined ptimum geometries for rectilinear diffusers with rectangular,conical or annular cross-section,fluid mechanics of internal flow［M］.Amsterdam,Holland:Elsevier,1967.
[16]	邹正平，王松涛，刘火星,等.航空燃气轮机涡轮气体动力学［M］.上海：上海交通大学出版社,2012.
[17]	李兆瑞，叶剑，陆利蓬.变逆压梯度湍流边界层条纹结构的流动显示［J］.工程热物理学报，2001，22（5）:563-565.LI Zhaorui,YE Jian,LU Lipeng.The visual display of coherent structure in the turbulence with variational adverse pressure gradients［J］.Journal of Engineering Thermophysics,2001,22(5):563-565.(in Chinese)
[18]	袁湘江，周桓.考虑流向曲率和压力梯度的可压缩边界层稳定性分析［J］.空气动力学学报，1998，16(3):276-281.YUAN Xiangjiang,ZHOU Heng.Stability analysis for compressible boundry layers with streamwise curvature and pressure gradient［J］.Acta Aerodynamica Sinica,1988,16(3):276-281.(in Chinese)