Basic Studies on Development of Ceramic Abradable Shroud

陶瓷耐磨护罩研制的基础研究

• 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

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.

在轴流式增压器上，对涡轮机叶排对面机匣壁面的局部换热系数和叶顶间隙流动在设计工况和非设计工况下进行了详细测量。结果总结如下。(1)局部换热系数沿出口截面方向单调减小，从靠近动叶排对面的壁面中部开始逐渐增大。然后，h达到最大值并再次减小，并且从转子叶片端部下游的一个轴向弦长附近开始，h再次增大。无论转速、叶尖间隙和载荷条件如何，这些趋势通常都是明显的。(2)另一方面，上述轮廓类似地随着转速的增加和叶尖间隙的减小而增加。(3)与转子叶片相对区域的平均努塞尔数与叶尖间隙和雷诺数相关。Nu与Re的0.8次方成正比。(4)Nu随着叶尖间隙的增大而逐渐变小，而与转速和载荷条件无关。(5)加速工况下的Nu最大，设计工况下的Nu较小。(6)在下游方向上，在与转子叶片相对的壁的中间之后，绝对速度矢量剖面显示出三维行为。在与转子叶片相对的壁的中间区域，在叶片正下方的区域中速度矢量变大，并且在叶片刚通过之后的区域中的壁附近可以看到这种效果。这表明叶尖间隙泄漏流的行为。(7)加速度条件下的速度矢量完全大于设计点的速度矢量。(8)机匣壁面的流场特征与局部换热特征相对应。

项目成果

熊田 雅弥: "ガスタ-ビンシュラウドの熱伝達に関する基礎的研究" 第17回ガスタ-ビン定期講演会講演論文集. 25-31 (1989)

Masaya Kumada：“燃气轮机护罩传热的基础研究”第 17 届燃气轮机例会论文集（1989 年）。

Masaya Kumada: "Characteristics of Tip Leakage Flow and Local Heat Transfer coefficient on the Casing Wall Surface Opposite to Turbine Blade Row" 4th Int.Symposium on Transport Phenomena in Heat and Mass Transfer,1991.7 Sydney,Australia.

Masaya Kumada：“叶尖泄漏流特性和与涡轮叶片排相对的壳体壁表面的局部传热系数”第四届国际传热传质研讨会，1991.7 澳大利亚悉尼。

Masaya Kumada: "Characteristics of Heat Transfer on Gas-Turbine Shroud" Proc. of 18th GAs turbine Conference, 1990-6, 11.

Masaya Kumada：“燃气轮机护罩传热特性”Proc。

Masaya Kumada: "Characteristics of Tip leakage Flow and Local Heat Transfer Coefficients on the Casing Wall Surface Opposite to Turbine Blade Row" Proc. of 28th National Heat Transfer Symposium of Japan, 1991-5, Fukuoka.

Masaya Kumada：“与涡轮叶片排相对的壳体壁表面上的尖端泄漏流和局部传热系数的特性”Proc。

Masaya Kumada: "Characteristics of Tip leakage Flow and Local Heat Transfer Coefficcients on the Casing Wall Surface Opposite to Turbine Blade Row" Proc. of 4th lnt. Symposium on Heat and Mass Transfer, 1991-7, Sydney.

Masaya Kumada：“叶尖泄漏流的特性和与涡轮叶片排相对的壳体壁表面的局部传热系数”Proc。