1) turbine blade trailing edge
涡轮叶片尾缘通道
1.
Effect of different clapboards structure in turbine blade trailing edge complex passages on heat transfer characteristics;
涡轮叶片尾缘通道中纵向肋对换热特性的影响
2) trailing edge of turbine vane
涡轮叶片尾缘
1.
Two-dimensional numerical simulation study have been conducted on flow and heat transfer of cooling configuration for trailing edge of turbine vane, the effects of the length of trailing edge (L/H), outlet air angle (a), the ratio of the coolant to mainstream mass flow (M) and the coolant Reynolds number (Re) on cooling efficiency were investigated.
对叶片尾缘偏劈缝冷却结构的流动与换热进行了二维的数值模拟,研究了涡轮叶片尾缘无量纲长度L/H(即尾缘长度与冷气 流出口的高度比)、偏劈缝喷射角α、吹风比M及Reynolds数(Re)对涡轮叶片尾缘平均冷却效果的影响。
3) turbine crown
涡轮叶片轮缘
4) impeller passage
叶轮叶片间通道
5) turbine blade trailing edge
叶片尾缘
1.
Different structure diaphragm plates in complex passages of turbine blade trailing edge;
涡轮叶片尾缘复合通道隔板结构
2.
The experiment mainly aimed at to investigate the effect of different aperture in different clapboard structure in the turbine blade trailing edge complex passages on heat transfer and pressure drop characteristics.
采用热色液晶测温法,测量了涡轮叶片尾缘带隔板的复合通道的温度场。
6) turbine blades
涡轮叶片
1.
Parametric design of turbine blades based on feature modeling;
基于特征造型技术的涡轮叶片参数化设计
2.
Research on Fatigue Life of Large Gas Turbine Blades;
大型燃气轮机涡轮叶片疲劳寿命研究
3.
The single crystal Ni-base superalloys were widely used for manufacturing advance gas turbine blades,but the ignored weakness of these alloys to date is that the extent of primary creep at intermediate temperature is much higher than that at high temperature.
单晶镍基高温合金已广泛用于制造先进燃气涡轮叶片,但这种合金至今仍被忽视的薄弱环节是它的中温Ⅰ阶蠕变伸长量远高于高温蠕变,而且与高温蠕变相比,中温Ⅰ阶蠕变对取向偏离、合金成分和热处理组织的变化更为敏感。
补充资料：MS6001系列燃气轮机一级空心涡轮叶片
MS6001系列燃气轮机一级空心涡轮叶片
Ms6()()l系列燃气轮机一级空心涡轮叶片 中同科学院金属研究所供稿
说明：补充资料仅用于学习参考，请勿用于其它任何用途。
参考词条