激波总压损失用正激波关系式通过马赫数法向分量估计。
The shock total pressure was estimated with the normal component of the Mach number using normal shock theory.
压气机叶型气动优化设计目标是静压升最大和总压损失最小。
The maximization of the static pressure rise and minimization of the total pressure loss are taken as the design targets.
但速度差随密度比、静温比增大而增大时总压损失亦随之增大。
But total pressure loss increases with the increasing of the velocity difference accompanied with the increase of the density and the static temperature ratio.
若密度比、静温比相同或相近时，速度差对总压损失的影响可忽略。
The effect of the velocity difference on total pressure loss may be neglected, if the density and the static temperature difference are equal.
分离区仅是高总压损失和高熵值的低能流体聚集区，而非高损失来源区；
Moreover, the separation zone is only a low-energy fluid gathering area for large total pressure loss and entropy rather than a zone of loss source.
通过叶片表面总压损失系数，证实了先进叶型在流动中可以降低叶型损失。
It is proved that the profile loss can be decreased with the use of advanced blade through the comparison of loss coefficient of blade surface overall pressure.
实验结果表明：混合过程的总压损失随两种超声速流的密度比、静温比增大而增加。
The experimental results show that the higher the static temperature and the density ratio between two supersonic flow, the more the total pressure losses of flow during mixing.
由于喷流方向与主流方向夹角较小，总压损失也较物理斜坡、横向喷流等混合增强方式小。
Due to the smaller Angle of injection, the ratio of total pressure loss of aerodynamic ramp is less than the physical ramp and transverse injection stream.
分析在不同叶片安装角下，叶片表面静压系数、出口总压损失系数和出口气流角的变化规律。
The static pressure loss coefficients, total pressure loss coefficients and flow outlet Angle distribution are simulated in conditions of different setting angles.
经优化后，透平高压级静叶的总压损失系数减少0.95%；多级压气机整机效率提高2.1%。
After optimization, the total pressure loss of the turbine vane was reduced by 0.95%, and the efficiency of the overall compressor was increased by 2.1%.
扩张角的增加可提高速度环量，但是流动混合损失增加，总压恢复系数减小。
The increase of lobe diffusion angle results in the increase of velocity circulation at the lobe exit section, but it raises the mixing loss and lowers the pressure recovery coefficient.
改型进气道减小了输出轴背风侧的分离和迎风侧的转弯损失，使其既保持了高总压恢复系数，且畸变指数最大降低了74%。
By modifying, the separation zone behind the shaft and turn loss at upwind side are all reduced. Modifying inlet maintains high pressure recovery, and the distortion index is reduced by 74% at most.
结果表明：在满足设计预期目标的同时，炉内单质硫生成量得到提高，总压降损失得到降低，具有节能效果。
The results showed that formation of sulfur furnace is improved and the total pressure drop is reduced which meet the design expectations with energy-saving effect.
结果表明：在满足设计预期目标的同时，炉内单质硫生成量得到提高，总压降损失得到降低，具有节能效果。
The results showed that formation of sulfur furnace is improved and the total pressure drop is reduced which meet the design expectations with energy-saving effect.
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