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为了探究航空发动机涡轮集气腔的流动特性,对4个主进气口、双排125个出流孔的涡轮集气腔出口流量分配规律和流阻系数进行了实验研究,重点分析了进出口压比、集气腔腔室高度等参数变化带来的影响。研究发现,正对主进气口的出流孔流量最大,而紧邻其两侧的周向出流孔流量明显减小。随着出流孔周向位置远离主进气口,出流孔流量迅速恢复并基本维持一个定值。但是位于每2个主进气口间1/2周向夹角位置,会出现最小的出流流量。实验结果表明,尽管周向上局部出流孔出现了极大和极小出流流量,但其仅为进口总流量的9.34%和3.29%。在本文实验参数范围内,随着进出口压比、集气腔高度的增加,通过集气腔的空气流量均变大,但并没有改变周向出流孔的流量分配规律。两者相比,集气腔高度带来的影响明显微弱。最终本文拟合得到了流阻损失系数同集气腔几何参数、进/出口气动参数之间的经验关系式,并将其应用于开发的一维空气系统集气腔元件中,为后续空气系统的设计与优化提供依据。
In order to explore the flow characteristics of the aero-engine turbine gas-gathering chamber, the flow distribution rules and flow resistance coefficients of the outlet ports of the four main inlets and 125 outlets of the turbine were experimentally studied. The import and export Pressure ratio, gas chamber height and other parameters of the impact. The study found that the outlet flow to the main inlet was the largest while the flow from the outlet to the outlet immediately adjacent to the main inlet was significantly reduced. As the outlet orifice is circumferentially located away from the main inlet port, the outlet orifice flow rapidly recovers and maintains a substantially constant value. However, located at a 1/2 circumferential angle between every two main inlets, a minimum outflow occurs. The experimental results show that although the maximum and minimum outflows occur in the partial outflow bores in the circumferential direction, they are only 9.34% and 3.29% of the total inlet flows. In the experimental parameter range of this article, with the pressure ratio of inlet and outlet increased, the height of the gas gathering chamber increased, the air flow through the gas gathering chamber became larger, but did not change the flow distribution rules of the circumferential outlet. Compared with the two, the influence of the height of the gas gathering chamber is obviously weak. Finally, the empirical relationship between the loss coefficient of flow resistance and the geometrical parameters of the gas-gathering chamber and the aerodynamic parameters of the inlet / outlet is obtained. The empirical formula is applied to the developed one-dimensional air-system gas-collecting chamber components for the subsequent air system Provide the basis for the design and optimization.