Basic Studies on Development of Ceramic Abradable Shroud

陶瓷耐磨护罩研制的基础研究

基本信息

批准号：
01550171
负责人：
KUMADA Masaya
金额：
$ 1.22万
依托单位：
Gifu University
依托单位国家：
日本
项目类别：
Grant-in-Aid for General Scientific Research (C)
财政年份：
1989
资助国家：
日本
起止时间：
1989 至 1990
项目状态：
已结题

来源：
https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-01550171/
关键词：
Gas Turbine Abradable Shroud Ceramic Tip Clearance Angle included by velocity Tip Clearance Leakage Flow Partial Load Heat Transfer Coefficient シュランド翼端すき間対流伝熱漏れ流れ

项目摘要

Detailed measurements of the local heat transfer coefficient and the tip clearance flow on the casing wall opposite the turbine blade row have been made under the conditions of both on- and off-design, using the axial-flow-type supercharger. The results are summarized as follows.(1) The local heat transfer coefficient decreases monotonically in the direction of outlet section and increases from near the middle of the wall opposite to the rotor blade row. Then h reaches a maximum value and decreases again and from near one axial chord length downstream of the end of the rotor blade, h increases again. These tendencies are generally evident regardless of rotational speed, tip clearance, and the condition of the load.(2) The above profile, on the other hand, increases similarly with an increase in the rotational speed and with a decrease in the tip clearance.(3) Mean Nusselt numbers in the region opposite to the rotor blade are correlated with the tip clearance and Reynolds number. Nu is proportional to the 0.8 power of Re.(4) Nu becomes smaller gradually with an increase in tip clearance regardless of rotational speed and the condition of the load.(5) Nu in the condition of acceleration is at its highest, and that in the on-design point is small.(6) In the downstream direction after the middle of the wall opposite to the rotor blade, the absolute velocity vector profiles show the three-dimensional behavior. At the middle region of the wall opposite to the rotor blade, the velocity vector becomes larger in the region directly under a blade and this effect can be seen near the wall in the region immediately after a blade passes through. This suggests the behavior of the tip clearance leakage flow.(7) The velocity vector in the condition of acceleration is wholly larger than that of the on-design point.(8) The characteristics of the flow field on the casing wall correspond to those of the local heat transfer.

使用轴向流型增压器，在涡轮刀片行与涡轮刀片行相对的壳体叶片行对面的套管壁上的额外测量值进行了详细测量。结果总结如下。（1）局部传热系数在出口截面的方向上单调降低，并从与转子叶片行相对的壁中间附近增加。然后，H达到最大值，并再次从转子叶片末端下游的一个轴向和弦长度下再次减小，H再次增加。这些趋势通常是显而易见的，无论旋转速度，尖端间隙以及负载的状况如何。（2）另一方面，上面的轮廓与旋转速度的提高和尖端间隙的降低相似。（3）与转子相反的区域中的平均Nusselt数字与尖端清除率和Reynolds数字相关。 NU与Re的0.8功率成比例。（4）Nu逐渐变小，而在旋转速度和负载状态的情况下，尖端间隙的增加。（5）NU处于加速度的状态最高，在设计点中，在壁上相反的壁上相反，在旋转的方向上，nu是旋转旋转玻璃体的中间方向的三分之一，三分之一的vection vertim verter vertim vetrim vertim vetriim vertim vector vetrim vertim vector。在与转子叶片相对的壁的中间区域，叶片直接在叶片下方的区域中变大，并且在刀片通过后立即在该区域附近看到这种效果。这表明尖端间隙泄漏流的行为。（7）加速条件下的速度向量完全大于设计点的速度。（8）（8）壳体壁上流场的特性与局部传热的相对应。