多级冷却涡轮燃烧不均匀性方位偏移的有效预测方法

Qingfu He, Zhongran Chi, S. Zang
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引用次数: 0

摘要

燃烧室出口温度通常由涡轮排气处的热电偶监测。为了建立每个热电偶测得的温度与每个燃烧器的工作状态之间的对应关系,需要对多级涡轮中燃烧热/冷条纹的方位迁移进行量化。测量这种迁移的实验成本高,误差大。在多种工作条件下的迁移也难以量化。三维全环空非定常模拟可以得到这种偏移。但单一工况的非定常模拟可能需要数周时间,这对于工程应用来说过于昂贵。提出了一种方位角偏移稳态计算方法。通过建立并求解迁移角输运方程,利用静-动界面混合平面进行稳态数值模拟,预测热/冷条纹的方位角迁移。将该方法计算的偏移量与多种工况下的全环空非定常模拟结果进行了比较。结果表明,该方法与全环空模拟结果吻合较好,而所花费的CPU时间仅为0.01%。同时发现,系统误差主要是由冷却剂源项边界值固定引起的。在此基础上讨论了汽轮机排气热电偶的最佳展向位置。该方法可用于燃气轮机燃烧室的故障诊断和精确维修。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
An Efficient Prediction Method for the Azimuthal Migration of Combustion Inhomogeneity in Multi-Stage Cooled Turbines
The outlet temperature of combustor is commonly monitored by thermocouples at the turbine exhaust. In order to establish the corresponding relationship between the temperature measured by each thermocouple and the working state of each burner, the azimuthal migration of the combustion hot/cold streaks in the multi-stage turbines needs to be quantified. Experiments to measure this migration have high cost and considerable error. It is also difficult to quantify the migration under multiple working conditions. Three-dimensional full-annulus unsteady simulation can obtain this migration. But the unsteady simulation of a single working condition could take several weeks, which is too expensive for engineering usage. A method named Steady-state Computation of Azimuthal Migration (SCAM) is proposed in this paper. By establishing and solving the transport equation of the migration angle, the azimuthal migration of hot/cold streaks can be predicted by steady-state numerical simulation using the mixing plane at rotor-stator interface. The migration computed by this method is compared with the full-annulus unsteady simulation results in multiple working conditions. The results of SCAM method show good agreement with full-annulus simulations, while costing only 0.01% of the CPU hours. It is also found that the error of SCAM is mainly caused by the fixed boundary value at coolant source terms. The optimal spanwise location of the thermocouples at turbine exhaust is discussed based on the results. The method proposed could be applied to the fault diagnosis and precise repair of the combustors of gas turbines.
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