首页> 外文期刊>Journal of Thermal Science and Engineering Applications: Transactions of the ASME >A Novel Transient Technique to Determine Recovery Temperature, Heat Transfer Coefficient, and Film Cooling Effectiveness Simultaneously in a Transonic Turbine Cascade
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A Novel Transient Technique to Determine Recovery Temperature, Heat Transfer Coefficient, and Film Cooling Effectiveness Simultaneously in a Transonic Turbine Cascade

机译:同时确定跨音速涡轮级联的恢复温度,传热系数和薄膜冷却效率的新型瞬态技术

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The study presented in this article provides detailed description about a newly developed experimental technique to determine three key convective heat transfer parameters simultaneously in hot gas path of a modern high pressure turbine-recovery temperature (T_r), heat transfer coefficient (HTC), and adiabatic film cooling effectiveness (Eta). The proposed technique, dual linear regression technique (DLRT), has been developed based on the 1D semi-infinite transient conduction theory, is applicable toward film cooled heat transfer experiments especially under realistic engine environment conditions (high Reynolds number along with high Mach numbers). It addresses the fundamental three temperature problem by a two-test strategy. The current popular technique, curve fitting method (CFM) (Ekkad and Han, 2000, "A Transient Liquid Crystal Thermography Technique for Turbine Heat Transfer Measurements," Meas. Sci. Technol., 11(7), pp. 957-968), which is widely used in the low speed wind tunnel experiments, is not competent in the transonic transient wind tunnel. The CFM (including schemes for both film cooled and nonfilm cooled experiments) does not provide recovery temperature on the film cooled surface. Instead, it assumes the recovery temperature equal to the mainstream total temperature. Its basic physics model simplifies the initial unsteady flow development within the data reduction period by assuming a step jump in mainstream pressure and temperature, which results in significant under prediction of HTC due to the gradual ramping of the flow Mach/Reynolds number and varying temperature in a transient, cascade wind tunnel facility. The proposed technique is advantageous due to the elimination of these added assumptions and including the effects of compressible flow physics at high speed flow. The detailed discussion on theory and development of the DLRT is followed by validation with analytical calculation and comparisons with the traditional technique by reducing the same set of experimental data. Results indicate that the proposed technique stands out with a higher accuracy and reliability.
机译:本文提供的研究内容详细介绍了一种新的实验技术,该技术可以同时确定现代高压涡轮回收温度(T_r),传热系数(HTC)和绝热的热气路径中的三个关键对流传热参数。薄膜冷却效率(Eta)。基于一维半无限瞬态传导理论开发的拟议技术,双重线性回归技术(DLRT),适用于薄膜冷却的传热实验,尤其是在现实的发动机环境条件下(高雷诺数和高马赫数) 。它通过两次测试策略解决了基本的三个温度问题。当前流行的技术,曲线拟合方法(CFM)(Ekkad和Han,2000,“用于涡轮热传递测量的瞬态液晶热成像技术”,测量科学技术,11(7),第957-968页)低速风洞实验中广泛使用的,在跨音速瞬态风洞中没有能力。 CFM(包括膜冷却和非膜冷却实验方案)没有在膜冷却表面上提供恢复温度。相反,它假定恢复温度等于主流总温度。它的基本物理模型通过假设主流压力和温度发生阶跃变化,简化了数据缩减期内的初始非稳态流动发展,由于流动Mach / Reynolds数的逐渐增加和温度的变化,导致HTC的预测明显不足。瞬态的级联风洞设施。由于消除了这些增加的假设,并且包括高速流动下的可压缩流动物理学的影响,因此所提出的技术是有利的。在对DLRT的理论和发展进行详细讨论之后,将进行分析计算验证,并通过减少同一组实验数据与传统技术进行比较。结果表明,所提出的技术以较高的准确性和可靠性脱颖而出。

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