吸力面的英文

• suction back
• upstream face

• "吸力"英文翻译    suction; suck; attraction
• "面"英文翻译    face
• "螺桨吸力面" 英文翻译 :    propeller suction side
• "吸力" 英文翻译 :    suction; suck; attraction 地心吸力 force of gravity; 相互吸力 mutual attraction; 吸力计 suction gauge
• "波吸力" 英文翻译 :    wave suction force
• "抽吸力" 英文翻译 :    suction force
• "磁吸力" 英文翻译 :    magnetic attraction force
• "大吸力" 英文翻译 :    high suction
• "底吸力" 英文翻译 :    bottom suction force
• "风吸力" 英文翻译 :    wind suction; wind uplift
• "呼吸力" 英文翻译 :    wind 1
• "吸力；引力" 英文翻译 :    force of attraction
• "吸力泵" 英文翻译 :    suction pump
• "吸力表" 英文翻译 :    draught gauge
• "吸力侧" 英文翻译 :    suction side
• "吸力的" 英文翻译 :    attractive
• "吸力垫" 英文翻译 :    suction pad
• "吸力计" 英文翻译 :    audibility meter; suction gage; suction gauge
• "吸力锚" 英文翻译 :    suction anchor
• "吸力桥" 英文翻译 :    suction ladder
• "吸力值" 英文翻译 :    pf-value
• "承力面" 英文翻译 :    bearing area; carrying surface
• "剪力面" 英文翻译 :    plane of shear; shear plane
• "升力面" 英文翻译 :    carrying piston; lift airfoil; lifting surface; lifting-piston; plane surface; supporting piston; supporting surface
• "受力面" 英文翻译 :    stress surface; thrust face; thrust surface

• Propeller suction side
  螺桨吸力面
• Pseudothermal temperature on tension side is higher than that on suction side , and pseudothermal temperature near wall is higher than that in interior
  计算结果表明，叶轮吸力面上的颗粒拟温度小于压力面上的，而且靠近壁面处的大于叶道中的。
• The results show that a positive bowed blade can restrain the corner separation and change the separation configuration , while it can not avoid the flow separation on the suction surface
  结果表明，正弯可以有效遏止角区分离，改变吸力面的分离形态，但不能完全消除吸力面的分离。
• At the same time , tip leakage induced by pressure gradient and relative motion between the blade tip and the shroud wall is found to have a major influence on detailed flow properties in tip region of rotor passage
  同时，由于转子叶片压力面和吸力面之间压力梯度以及叶顶与机匣之问的相对运动产生的间隙流对转子通道内的细微流动结构有较大的影响。
• The results show that the negative bowing results in the " c " shape distribution of static pressure on blade surfaces , which is the main reason for the variation of characteristics of flowfield , however the aerodynamic performances of cascades can not be improved by negatively bowed blades
  结果表明：叶片反弯曲在叶片表面特别是吸力面建立了反“ c ”形压力分布，它是引起叶栅性能和流场变化的主要原因，但叶片反弯曲不能改善叶栅的气动性能。
• 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。
• Based on an engineering background , through numerical simulation of the flow field in the hp turbine of the energy efficient engine ( e3 ) , the article research the unsteady flow in a transonic turbine stage , the unsteady phenomena in the stage include the shockwave , wake , shedding vortex , endwall vortex , passage vortex and leakage vortex , etc . there are two shockwaves generated on the vane the tailing edge , one on suction side is named moving shockwave , and name another on pressure side steady shockwave
  本文首先对于研究的意义和国内外研究的现状做了简要的介绍，再从某工程背景出发，通过对e3发动机高压涡轮内流场的数值模拟，研究了干涉的周期性的问题，以及涡轮级内常见的非定常现象：激波、尾迹、脱落涡、根脚涡、通道涡、漏流涡。导向器尾缘会出现两道激波，在吸力面的激波可称为“运动”激波，压力面的激波可称为“定常”激波。
• As we know , inverse techniques make blade ' s profile well compatible with its surface velocity distribution , however , they give designers big challenges that the ideal velocity distribution is hard to obtained and sometimes the non - physical solution , such as double covering of flow field or unclosed profiles , would come out . the proposed design procedure in the paper has avoided the disadvantage mentioned above . in this paper , a quasi - irrotational equation is used to describe the flow in cascade instead of the generally used irrotational equation
  众所周知，一般的反问题和混合问题的最大特点，是在给定的压力面和吸力面上的压力分布或速度分布条件下，直接得到叶片的几何形状，它可以使叶型型面与表面气流参数有机结起来；其不足之处在于，对设计者而言，很难给定理想的叶片表面压力分布或速度分布，并且有时会得到一个非物理解，如：得出的初始叶型可能会出现前缘、尾缘不封闭的现象。
• ( 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。