扩压段的英文

• diffuser

• "扩"英文翻译    expand; enlarge; extend
• "压"英文翻译    press; push down; hold down; ...
• "段"英文翻译    section; segment; part; para ...
• "泵扩压段" 英文翻译 :    pumdiffuser
• "环形扩压段" 英文翻译 :    annular diffuser
• "桥形扩压段" 英文翻译 :    bridge diffuser
• "大张角扩压段" 英文翻译 :    wide-angle diffuser
• "扩散器扩压段" 英文翻译 :    diffuser
• "第二喉道扩压段" 英文翻译 :    second-throat diffuser
• "无扩压段式风洞" 英文翻译 :    non-diffuser-type wind tunnel
• "超音速到亚音速扩压段" 英文翻译 :    supersonic-subsonic diffuser
• "大扩张角扩压段,大扩散角扩散段" 英文翻译 :    wide angle diffuser
• "扩压" 英文翻译 :    diffusing action
• "低压段" 英文翻译 :    low pressure stage
• "泄压段" 英文翻译 :    tension releasing section
• "中压段" 英文翻译 :    intermediate pressure section
• "低压段级" 英文翻译 :    low pressure stage
• "螺杆释压段" 英文翻译 :    decompression zone
• "扩压泵" 英文翻译 :    diffuser casing pump
• "扩压管" 英文翻译 :    diffuser
• "扩压器" 英文翻译 :    diffuser recovery; diffusor
• "挤塑机释压段" 英文翻译 :    decompression section
• "超声扩压器" 英文翻译 :    supersonic diffuser
• "环形扩压器" 英文翻译 :    annular diffuser
• "简单扩压器" 英文翻译 :    simple diffuser

• The diffuser length should be long enough to ensure the main flow deceleration
  扩压段应具有一定的长度以保证主气流减速到一定程度。
• The configuration of the diffuser should be designed as a channel to allow the main flow pass through a shock train
  扩压段的形状应设计成能使主气流通过系列斜激波串减速的通道。
• E ) applying the inter - phase slip algorithm ipsa method to solve the set of discretized equations
  对燃烧室扩压段的计算区域离散采用了贴体坐标系； e采用了ipsa算法来求解离散方程。
• The effect of the diffusers was investigated for the different shapes and sizes , as well as different locations
  其中，扩压段的设计非常重要，它不是孤立的，而与主流系统和引射系统密切相关。
• The start process of the facility for the different cases was under research in order to find the optimal configuration for the system
  通过对不同几何形状的扩压段在不同安装位置进行调试，研究在风洞起动过程中整个系统流动状态的演变规律，探索扩压段的优化设计。
• The experimental results show that the location of the diffuser should be close to the nozzle exit , and the shape and size of the diffuser entrance should match the nozzle exit
  实验表明，扩压段应安装在距主喷管较近的位置，并具有与主喷管相匹配的入口面积和形状。
• When there are struts at the divergent parts of inlet , the total pressure recovery coefficients and the kinetic energy coefficients of inlet decrease , and the flow distortion index increases obviously
  当进气道扩压段有侧向支柱存在时，进气道总压恢复系数和动能系数均有所降低，而流场畸变指数则显著增大。