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本文提出具有可变几何喷嘴的增压器轴流涡轮热力计算方法。引入三个脉冲系数将脉冲涡轮按等压涡轮计算。给定通流部分尺寸,利用可变几何喷嘴来满足所驱动压气机和涡轮的配合。考虑各部实际损失,采用吴仲华燃气热力性质表迭代计算求出反动度、喷嘴出气角和喉口面积。可给定废气初温时迭代所需的初压或给定初压时迭代所需的初温,并算出涡轮当量通流面积。计算结果表明迭代计算是收敛的,算出的喷嘴喉口面积与实际相符。
In this paper, a method to calculate the thermal energy of turbocharger axial flow turbines with variable geometry nozzles is proposed. Introduce three pulse coefficients to calculate the pulse turbine according to equal pressure turbine. Given the size of the flow-through section, a variable geometry nozzle is used to match the driven compressor and turbine. Taking into account the actual losses of all ministries, Wuzhonghua gas thermodynamic properties table iteratively calculated the reaction, nozzle exit angle and throat area. Given the initial pressure required for the iteration at the initial temperature of the exhaust gas or the initial temperature required for the iteration at a given initial pressure, the turbulence equivalent flow area may be calculated. The calculation results show that the iterative calculation is convergent, and the calculated nozzle throat area is in accordance with the actual situation.