转-静盘预旋系统特征参数变化影响的研究
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摘要
航空发动机中,预旋冷却技术能够有效提高冷气对涡轮高温部件的冷却效率,从而保证发动机的可靠性,并延长其使用寿命。然而由于实际发动机涡轮盘腔结构的复杂性,通过对规则盘腔结构研究所得到的结论具有一定的局限性,因此,对复杂结构预旋进气盘腔的研究具有重要的理论意义和工程实用价值。
本文根据预旋冷却的研究背景和现状,对接近实际结构的、带有三种出气方式的复杂涡轮转-静盘腔预旋系统进行了系统的研究。首先利用FLUENT软件,研究了特征参数变化对预旋盘腔系统流量分配比例、预旋温降和总压系数的影响。特征参数主要包括盘间距、预旋角度、旋转雷诺数、无量纲冷气流量、进气总温等。并根据实验室的现有条件,初步设计了复杂盘腔预旋系统的试验系统,为后续试验研究做准备。
数值模拟研究结果表明:1)盘间距对流量分配比例的影响很小;2)预旋角度对流量分配比例的影响较小;3)旋转雷诺数对流量分配的影响较大;4)几何尺寸的改变对流量分配的影响较大;5)当旋转雷诺数增大时,无量纲总温差和总压系数逐渐减小;6)随着进气总温的增加,无量纲总温差和总压系数都逐渐增大;7)随着质量流量的增加,无量纲总温差逐渐减小,总压系数逐渐增大;8)随着盘间距增大,无量纲总温差和总压系数都是先减小后增大;9)随着预旋角度增大,无量纲总温差逐渐减小,总压系数逐渐增大。
本文的研究成果为实际预旋进气涡轮盘腔结构的设计提供了理论指导依据。
The using of pre-swirl cooling method could increase the efficiency of the cooling air to the turbine blades which swirl in the rotation direction of the turbine, and it can guarantee the safe and reliable performance of aero-engine and prolong its working time.The investgations of the regular pre-swirl rotor-stator cavity is limited due to the complicated structure of the real turbine disk. So it is necessary to do the research on the complicated pre-swirl rotor-stator cavity.
In this paper, numerical simulations were conducted to investigate the effects of the different characteristic parameters of the complicated pre-swirl rotor-stator cavity with three outflows by the use of FLUENT software according to the background and the actuality of the pre-swirl cooling. And it is got the conclusion that the influence of the characteristic parameters to the flux proportion,total temperature drop and total pressure coefficient. An experimental system was outlined in order to do experiments later .
Numercial results indicate that: 1) the flux proportion is influenced little by the gap between the rotor and the stator; 2) the flux proportion is influenced little by the pre-swirl angles; 3) the flux proportion is influenced evident by the rotational Reynolds number; 4) the flux proportion is influenced distinct by the geometry size; 5) the nondimensional total temperature difference and the total pressure coefficient are monotone decreased with the increase of rotational Reynolds number; 6) the nondimensional total temperature difference and the total pressure coefficient increase with the increase of the inlet total temperature; 7) the nondimensional total temperature difference decrease while the total pressure coefficient increase because of increasing the pre-swirl inflow; 8) the nondimensional total temperature difference and the total pressure coefficient decrease and then go up with the gap between the rotor and the stator increases; 9) the nondimensional total temperature difference increases while the total pressure coefficient decreases with the decrease of pre-swirl angles.
The present study will theoretically provide a direction for the design of complicated rotor-stator cavity with pre-swirl flow.
本文根据预旋冷却的研究背景和现状,对接近实际结构的、带有三种出气方式的复杂涡轮转-静盘腔预旋系统进行了系统的研究。首先利用FLUENT软件,研究了特征参数变化对预旋盘腔系统流量分配比例、预旋温降和总压系数的影响。特征参数主要包括盘间距、预旋角度、旋转雷诺数、无量纲冷气流量、进气总温等。并根据实验室的现有条件,初步设计了复杂盘腔预旋系统的试验系统,为后续试验研究做准备。
数值模拟研究结果表明:1)盘间距对流量分配比例的影响很小;2)预旋角度对流量分配比例的影响较小;3)旋转雷诺数对流量分配的影响较大;4)几何尺寸的改变对流量分配的影响较大;5)当旋转雷诺数增大时,无量纲总温差和总压系数逐渐减小;6)随着进气总温的增加,无量纲总温差和总压系数都逐渐增大;7)随着质量流量的增加,无量纲总温差逐渐减小,总压系数逐渐增大;8)随着盘间距增大,无量纲总温差和总压系数都是先减小后增大;9)随着预旋角度增大,无量纲总温差逐渐减小,总压系数逐渐增大。
本文的研究成果为实际预旋进气涡轮盘腔结构的设计提供了理论指导依据。
The using of pre-swirl cooling method could increase the efficiency of the cooling air to the turbine blades which swirl in the rotation direction of the turbine, and it can guarantee the safe and reliable performance of aero-engine and prolong its working time.The investgations of the regular pre-swirl rotor-stator cavity is limited due to the complicated structure of the real turbine disk. So it is necessary to do the research on the complicated pre-swirl rotor-stator cavity.
In this paper, numerical simulations were conducted to investigate the effects of the different characteristic parameters of the complicated pre-swirl rotor-stator cavity with three outflows by the use of FLUENT software according to the background and the actuality of the pre-swirl cooling. And it is got the conclusion that the influence of the characteristic parameters to the flux proportion,total temperature drop and total pressure coefficient. An experimental system was outlined in order to do experiments later .
Numercial results indicate that: 1) the flux proportion is influenced little by the gap between the rotor and the stator; 2) the flux proportion is influenced little by the pre-swirl angles; 3) the flux proportion is influenced evident by the rotational Reynolds number; 4) the flux proportion is influenced distinct by the geometry size; 5) the nondimensional total temperature difference and the total pressure coefficient are monotone decreased with the increase of rotational Reynolds number; 6) the nondimensional total temperature difference and the total pressure coefficient increase with the increase of the inlet total temperature; 7) the nondimensional total temperature difference decrease while the total pressure coefficient increase because of increasing the pre-swirl inflow; 8) the nondimensional total temperature difference and the total pressure coefficient decrease and then go up with the gap between the rotor and the stator increases; 9) the nondimensional total temperature difference increases while the total pressure coefficient decreases with the decrease of pre-swirl angles.
The present study will theoretically provide a direction for the design of complicated rotor-stator cavity with pre-swirl flow.
引文
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