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在常规轴流级流线曲率法通流设计和任意中弧线叶型造型方法的基础上,引入了适合于大小叶片的当量扩散因子叶型损失模型,发展了用Miller-Lewis-Hartmann(M-L-H)模型分别计算大叶片和小叶片激波损失的复合激波模型,制定了大小叶片装配方法,建立了大小叶片通流反问题设计系统。用该系统对某级增压比为2.20的单级高负荷后掠风扇进行了后掠和前掠大小叶片改型设计。经计算流体力学(CFD)检验,维持后掠造型的改型,在不提高设计点增压比的条件下,级绝热效率相当,流量和失速裕度都得到了提高;而大小叶片结合前掠的改型,当考虑单排静子的最大载荷将设计级增压比提高至2.31时,级绝热效率略微降低约0.3%,流量略减,失速裕度则显著提高。算例也表明通流反问题设计系统适合于大小叶片轴流级的设计。
Based on the conventional flow-through curvature design and arbitrary camber line modeling, the leaf loss model of equivalent diffusion factor suitable for large and small blades was introduced and the Miller-Lewis-Hartmann (MLH ) Model was used to calculate the composite shock model of the shock loss of the large and small leaf blades respectively. The system was used to design a single-stage high-load swept-back fan with a booster ratio of 2.20 at a swept back and forward swept size. Computational fluid dynamics (CFD) test, to maintain the swept shape of the retrofit, without increasing the design point pressurization ratio conditions, the level of adiabatic efficiency, flow and stall margin have been increased; and the size of the blade with a sweep When considering the maximum load of single-row stator, the design-stage supercharging pressure ratio is increased to 2.31, the grade adiabatic efficiency is slightly reduced by about 0.3%, the flow rate is slightly reduced, and the stall margin is significantly increased. The example also shows that the through-flow inverse problem design system is suitable for the design of the axial blade of large and small blades.