在氧枪喷头设计和制定供氧制度时要减小激波损失。
Loss of shock wave should be decreased when design oxygen lance nozzle and oxygen blowing system.
再应用改进了的端壁损失和激波损失模型，最终算出轴流压气机设计点损失沿叶高的分布规律。
Finally, the total loss distribution along the blade span of the axial flow compressor is estimated according to an improved end wall loss model and a shock loss model.
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.
结果表明，压气机转子前缘激波后掠可以有效地降低损失。
The result shows that the leading edge shock wave sweepback could reduce loss obviously.
在相对升程小于6%、压比小于0.7后，环形通道的末端将产生激波，激波带来较大的全压损失。
At the end of the annular passage, shock wave occurs when the relative lift is less than 6% and the pressure ratio is less than 0.7, which causes a greater total pressure loss.
由于声激波降噪需要附加一段具有高速流动的缩放管道，它会附加流动噪声和压力损失，本文提供了这方面的一组实验数据，以说明应用声激波消声器的现实可能性。
Meanwhile, a group of experimental data of additional noise pressure level and fluid pressure loss generated by flow in a duct is presented to explain the readability of us...
由于声激波降噪需要附加一段具有高速流动的缩放管道，它会附加流动噪声和压力损失，本文提供了这方面的一组实验数据，以说明应用声激波消声器的现实可能性。
Meanwhile, a group of experimental data of additional noise pressure level and fluid pressure loss generated by flow in a duct is presented to explain the readability of us...
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