平面叶栅尾流板开孔率对跨声速涡轮叶栅流道影响的数值分析

陈宇; 徐惊雷; 黄帅; 巩昊

doi:10.13224/j.cnki.jasp.2018.01.025

平面叶栅尾流板开孔率对跨声速涡轮叶栅流道影响的数值分析

doi: 10.13224/j.cnki.jasp.2018.01.025

南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京 210016

计量
- 文章访问数: 615
- HTML浏览量: 2
- PDF量: 481
- 被引次数: 0
出版历程
- 收稿日期: 2016-12-22
- 刊出日期: 2018-01-28

Numerical study on the effect of the linear cascade slotted tailboard void ratio on the passage of transonic gasturbine cascade

摘要

摘要: 跨声速平面叶栅风洞中通常通过尾流板来改善平面叶栅周期性,针对尾流板的设计需求,利用数值模拟的方法,研究了尾流板在15%、30%、50%开孔率下对实验叶栅的影响。数值分析结果表明:叶栅尾缘激波在自由边界上反射后,返回到叶栅通道中,破坏了叶栅通道的周期性；开槽尾流板减少了反射波对叶栅通道的影响,减弱叶栅尾缘激波的反射波强度,在某特定情况下能使反射波变成膨胀波,从而提高了叶栅通道周期性；尾流板开孔率为15%时能极大地改善平面叶栅通道的周期性,相对于开孔率为50%时叶栅的周期性误差降低约16.43%。
- 跨声速平面叶栅实验设计 /
- 叶栅尾缘激波 /
- 开槽尾流板 /
- 尾流板开孔率 /
- 周期性
Abstract: Transonic test in linear cascade wind tunnel usually uses a tailboard to improve the linear cascade periodicity. In order to meet the tailboard design requirement, a tailboard with void ratios of 15%,30%,50% was designed and optimized with a numerical method to attenuate such effects. The numerical results indicated that, shock waves stemming from the cascade trailing edges reflected back to the passages at the boundaries disturbing the interior flow and breaking periodicity of cascade passage. A substantial attenuation of such interference was obtained via use of a slotted tailboard downstream the blade trailing edge. Meanwhile, the reflected wave strength was different from the impinging one, and under certain conditions, the reflected wave can become an expansion wave, as a consequence, the pitchwise periodicity had a considerable improvement. The 15% tailboard void ratio significantly improved the periodicity of the cascade flow, reducing the periodicity error by 1643% in related to the 50% void ratio tailboard.
- tests design of transonic linear cascade /
- shock wave stemming from the cascade trailing edge /
- slotted tailboard /
- void ratio of the tailboard /
- periodicity

HTML

参考文献(18)

[1]	GOETHERT B H,NELSONW C.Transonic wind tunnel testing［M］.London:Pergamon Press,1961.
[2]	ARTS T,LAMBERTDEROUVROIT M,RUTHERFORD A W.Aerothermal investigation of a highly loaded transonic linear turbine guide vane cascade:a test case for inviscid and viscous flow computations［R］.Brussels,Belgium:Von Karman Institute for Fluid Dynamics,1990.
[3]	DAVIS J W.Optimization of wave cancellation in variable porosity transonic wind tunnel flows［R］.NASA TN-D-7432,1974.
[4]	CASTRO B M,JONES K D,EKATERINARIS J A,et al.Analysis of the effect of porous wall interference on transonic airfoil flutter［R］.AIAA2001-2725,2001.
[5]	NEAL T F,DARYL L B,VEER N V,et al.A boundary condition for simulation of flow over porous surfaces［J］.Journal of Aircraft,2001,40(4):2001-2412.
[6]	PACIORRI R,SABETTA F,RONA A.Wave reflection on porous walls:numerical modelling and application to transonic wind tunnels［R］.AIAA2002-1060,2002.
[7]	RONA A,GOSTELOW J,PACIORRI R,et al.Wall interference in the discharge flow in a linear cascade wind tunnel［J］.Counseling and Values,2003,42(1):41-54.
[8]	RONA A,PACIORRI R,SABETTA F.Experimental and numerical evaluation of nonreflecting porous tailboards for transonic cascade wind tunnels［C］∥Proceedings of 4th European Conference on Turbomachinery:Fluid Dynamics and Thermodynamics.Florence,Italy:University of Leicester,2001:247-260.
[9]	RONA A,PACIORRI R,GERON M,et al.Slot width augmentation in a slottedwall transonic linear cascade wind tunnel［R］.AIAA2004-608,2004.
[10]	DAVIS D D,WOODG P.Preliminary investigation of reflections of oblique waves from a porous wall［R］.NACA RM-L50G19A,1950.
[11]	DAVIS J W,GRAHAM R T.Flow interference in a variable porosity trisonic wind tunnel［R］.AIAA 72-1010,1972.
[12]	RONA A,GOSTELOW J.Performance of slotted end wall linear cascade tunnels at offdesign conditions［R］.AIAA2005-98,2005.
[13]	RONA A,PACIORRI R,GERON M.Design and testing of a transonic linear cascade tunnel with optimized slotted walls［J］.Journal of Turbomachinery,2006,128(1):23-34.
[14]	RONA A,GOSTELOW J.Performance margins of nonreflecting slotted walls in a transonic linear cascade tunnel［R］.ASME Paper GT2006-91057,2006.
[15]	NELSON W J,BLOETSCHER F.Preliminary investigation of porous walls as a means of reducing tunnel boundary effects at lowsupersonic Mach numbers［R］.NACA RM-L50D27,1950.
[16]	CARSCALLEN W E,FLEIGE H U,GOSTELOW J P.Transonic turbine vane wake flows［R］.ASME Paper 96-GT-419,1996.
[17]	CAMCI C,ARTS T.Shortduration measurements and numerical simulation of heat transfer along the suction side of a filmcooled gas turbine blade［J］.Journal of Engineering for Gas Turbines and Power,1985,107(4):991-997.
[18]	OLDFIELD M L G,KIOCK R,HOLMESA T,et al.Boundary layer studies on highly loaded cascades using heated thin films and a traversing probe［J］.Journal of Engineering for Gas Turbines and Power,1981,103(1):237-246.