Design and Testing of a Rig to Investigate Buoyancy-Induced Heat Transfer in Aero-Engine Compressor Rotors
Design and Testing of a Rig to Investigate Buoyancy-Induced Heat Transfer in Aero-Engine Compressor Rotors
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研究航空发动机压缩机转子浮力诱导传热的装置的设计和测试
DOI：
10.1115/1.4048601
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发表时间：
2021
期刊：
影响因子：
--
通讯作者：
Luberti D
中科院分区：
文献类型：
--
作者：
Luberti D
在整个飞行周期中压气机叶尖间隙的变化取决于转子的膨胀，而转子的膨胀又取决于圆盘中的温度和应力。温度的径向分布与旋转盘腔中的浮力驱动的流动和传热直接相关。本文描述了一种专门设计用于研究这种共轭现象的新测试装置。钻机测试部分包括四个封闭三个空腔的旋转盘。中心腔中的两个圆盘装有热电偶，以提供温度的径向分布；两个外腔是隔热的，为传热分析创造适当的边界条件。在固定轴和圆盘孔之间供应轴向流通的空气。流通空气的温度由中心腔上游和下游耙架中的热电偶测量。对于冷流，中心腔的外罩被加热。两个独立控制的辐射加热器可实现上游盘和下游盘的不同护罩温度，如航空发动机压缩机中的情况。或者，可以将通流加热到护罩温度以上，以模拟发动机运行期间空腔内可能发生分层流的瞬态条件。该钻机设计用于在对流和辐射传热占主导地位的条件下运行；腔体的所有内表面均涂成哑光黑色，以便准确计算辐射传热。两个中心盘的轴上可以安装单独的附件；这些附件减少了棒子之间的轴向间隙，将间隙减小到零会形成一个封闭的空腔，这可能会出现在某些压缩机设计中。其他仪器包括护罩上的热通量计和嵌入圆盘隔膜中的高频压力传感器，以捕获不稳定的流动结构。关注了实验的不确定性，包括由嵌入旋转盘中的热电偶引起的热扰动误差的计算；贝叶斯统计模型用于减少温度测量的不确定性对努塞尔数计算的影响。一些典型情况显示了相关无量纲参数对圆盘径向分布和通流温度的影响。
The change in compressor blade-tip clearance across the flight cycle depends on the expansion of the rotor, which in turn depends on the temperature and stress in the disks. The radial distribution of temperature is directly coupled to the buoyancy-driven flow and heat transfer in the rotating disk cavities. This paper describes a new test rig specifically designed to investigate this conjugate phenomenon. The rig test section includes four rotating disks enclosing three cavities. Two disks in the central cavity are instrumented with thermocouples to provide the radial distribution of temperature; the two outer cavities are thermally insulated to create appropriate boundary conditions for the heat transfer analysis. An axial throughflow of air is supplied between a stationary shaft and the bore of the disks. The temperature of the throughflow air is measured by thermocouples in rakes upstream and downstream of the central cavity. For a cold throughflow, the outer shroud of the central cavity is heated. Two independently controlled radiant heaters allow differential shroud temperatures for the upstream and downstream disks, as found in aero-engine compressors. Alternatively, the throughflow can be heated above the shroud temperature to simulate the transient conditions during engine operation where stratified flow can occur inside the cavity. The rig is designed to operate in conditions where both convective and radiative heat transfer dominate; all internal surfaces of the cavity are painted matt black to allow the accurate calculation of the radiant heat transfer. Separate attachments can be fitted to the cobs of both central disks; the attachments reduce the axial gap between the cobs—reducing the gap to zero creates a closed cavity, which can occur in some compressor designs. Other instrumentation includes heat-flux gages on the shroud and high-frequency pressure transducers embedded into the disk diaphragm to capture unsteady flow structures. Attention has been given to experimental uncertainty, including the computation of the thermal-disturbance errors, caused by thermocouples embedded in the rotating disks; a Bayesian statistical model is used to reduce the effect of uncertainties in temperature measurements on the calculation of the Nusselt number. The effect of relevant nondimensional parameters on the radial distribution of the disk and throughflow temperatures has been shown for some typical cases.
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DOI：
10.1016/j.ijheatmasstransfer.2017.11.110
发表时间：
2018
影响因子：
5.2
作者：
Yongkai Quan;Di Han;Guoqiang Xu;J. Wen;Xiang Luo
通讯作者：
Xiang Luo
具有轴向流通的旋转腔中的流动可视化
影响因子：
5.8
作者：
D. Bohn;Gregor N. Deutsch;B. Simon;C. Burkhardt
通讯作者：
C. Burkhardt
利用鳍方程计算旋转圆盘的努塞尔数
影响因子：
2.6
作者：
Hui Tang;T. Shardlow;J. Owen
通讯作者：
J. Owen
DOI：
10.1016/j.ijheatfluidflow.2007.04.010
发表时间：
2007
影响因子：
2.6
作者：
C. Long;Nicolas Miché;P. Childs
通讯作者：
P. Childs
使用 fin 方程计算旋转圆盘的努塞尔数
影响因子：
1.7
作者：
Hui Tang;T. Shardlow;J. Owen
通讯作者：
J. Owen