pressure surface meaning in Chinese
承压面
内弧面
推进面
压力面
压力水面
Examples
- Time averaged temperature distributions on rotor surface will greatly change with the hot streak / airfoil ratio , and the temperature distribution changes more on the pressure surface than that on the suction surface of the rotor
改变热斑数与导叶通道数比会对动叶时均温度分布产生较大影响，动叶压力面温度分布所受的影响更大。 - On the rotor blade pressure surface , the dominant frequencies of unsteady surface pressure are the up - stream blade wake passing frequency and its harmonics , and the amplitudes of pressure fluctuations decrease from leading edge to trailing edge
转子叶片吸力面非定常压力受叶片附面层和上游叶片尾迹共同影响，其主导频率为上游叶片尾迹频率及其倍频，但是在吸力面前部气流加速区压力波动幅度沿流向增大，而在吸力面后部气流减速区压力波动幅度沿流向减小。 - ( 2 ) on the leading edge , the film cooling effectiveness at the zone immediately downstream of the cooling holes is affected by blowing ratio and mainstream reynolds number , while the effects are not important in the downstream zone far from the cooling holes . ( 3 ) on the front half of pressure surface , the effectiveness increases with decreasing blowing ratio at the downstream near the cooling row and it is contrary at the downstream far from the cooling row . ( 4 ) on the rear pare of the pressure surface , the effectiveness decreases with increasing blowing ratio and does not vary so much downstream in the cases of higher blowing ratio
研究结果表明叶片吸力面端壁附近区域压力系数分布呈现出较强的三维特性，动叶吸力面尤其明显；气膜孔流量系数随吹风比的增加而增大，在高吹风比情况下，流量系数逐渐趋于常数；在不同型面区域，冷却效率分布有较大的差异，而且吹风比与主流雷诺数的影响程度也不尽相同；低吹风比下，孔出口下游附近可以得到较好的冷却，中、高吹风比下，冷气射流在加速流动主流的作用下返回壁面进行二次冷却，孔下游较远区域可以得到较好的冷气覆盖。 - The primary purpose of this paper is how to solve the overloaded propeller ' s condition . the style of propeller trailing edge cutting and shave on the pressure surface is adopted . the propeller ' s actual effect pitch will be reduced which cause the propeller ' s torque down
本文主要是考虑螺旋桨出现负荷过重时如何处理的问题，所以采用桨叶随边切割并在叶面处将翼型修顺的方式，实质上是切割后导致螺旋桨实效螺距的减小，从而使螺旋桨吸收的转矩降低来达到主机负荷降低的目的。