Conceptual design of ceramic matrix composites turbine blade for typical turbofan engine
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摘要:
为了推动先进航空发动机陶瓷基复合材料(CMCs)涡轮叶片设计技术进步,以典型涡扇发动机基准性能参数为原始数据,按照涡轮叶片正向设计流程,从气动设计,到结构设计,再到变形及强度分析,梳理出以材料强度为约束,发动机推力和耗油率为输入值,涡轮叶片叶身模型为结果的概念设计方法。设计了一种陶瓷基复合材料低压涡轮转子叶片,该叶片实心无冷却,设计工况下的气动性能、强度和振动特性仿真结果满足设计要求。安全储备系数可达1.8,涡轮盘外载预估减少50%,验证了陶瓷基复合材料用于先进航空发动机热端部件的可行性。涡轮效率提高0.98%~1.17%表明陶瓷基复合材料具有提升先进航空发动机热端部件性能的潜力。
Abstract:For the purpose of technological progress for ceramic matrix composites (CMCs) turbine blade design in advanced aero-engines, based on main performance parameters of typical turbofan engine, and according to the forward turbine blade design process, a conceptual design method was established from aerodynamic design to structural design finally to deformation and strength analysis, and a CMCs low pressure turbine rotor blade was designed, which was solid without cooling. In the conceptual design method, strength was taken as the major constraint, aero-engine thrust and specific fuel consumption taken as inputs, and model of turbine blade body taken as output. The simulation results indicated that aerodynamic performance, strength and vibration performance of the designed blade under design conditions satisfy the design requirements. Reserve factor of safety reached 1.8 and the external load level of the turbine disk was estimated to be reduced by 50%, proving the feasible application of CMCs on advanced aero-engines. Turbine efficiency increased approximately 0.98%—1.17%, which demonstrated the potential of CMCs to promote the performance of high-temperature components in advanced aero-engines.
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表 1 设计点计算结果
Table 1. Calculation results of design point
参数 验算值 基准值[3] 中间状态推力/kN 105.5 105.5 中间耗油率/(kg/(daN·h)) 0.8371 0.837 换算空气流量/(kg/s) 124.02 126.50 总压比 27.1695 26.1 涵道比 0.3112 0.3 涡轮前温度/K 1802.9 1860 表 2 低压涡轮级性能参数值
Table 2. Performance parameters of low pressure turbine
参数 导向器进口 转子出口 流量/(kg/s) 96.10 96.10 总温/K 1379.33 1181.41 静温/K 1347.15 1137.49 总压/Pa 960877 458286 静压/Pa 867043 390233 绝对速度/(m/s) 283.56 327.06 焓/(J/kg) 1237530 992312 转速/(r/min) 11000 出口面积/m2 0.25 表 3 转子叶片进出口径向尺寸
Table 3. Radial dimension of inlet and outlet rotor blade
参数 进口 出口 内径/m 0.315 0.294 外径/m 0.412 0.414 叶片长度/cm 9.7 12.0 轮毂比 0.76 0.71 截面面积/m2 0.22 0.27 表 4 叶中处速度三角形设计值
Table 4. Value of velocity triangle design at average position
参数 进口 出口 $ {c}_{\mathrm{a}} $ 288.99 297.23 $ {c}_{\mathrm{u}} $ 543.17 41.51 $ c $ 615.27 300.11 $ {w}_{\mathrm{u}} $ 124.84 449.09 $ w $ 314.81 539.61 $ \alpha $ 28.02 82.05 $\,\beta$ 66.64 33.67 表 5 截面Ⅳ叶型几何参数
Table 5. Blade profile geometric parameters at section Ⅳ
参数 数值 相对栅距 0.66 相对厚度 0.09 进口攻角/(°) −1 叶栅出口角/(°) 32.10 弦长/mm 40.91 栅距/mm 27.20 叶型安装角/(°) 119.75 叶片宽度/mm 35.80 最大厚度/mm 3.70 进气边小圆半径/mm 0.77 排气边小圆半径/mm 0.44 进气边楔角/(°) 16 排气边楔角/(°) 4 喉道宽度/mm 14.50 几何进口角/(°) 65.64 几何出口角/(°) 32.88 叶背出口弯折角/(°) 9 表 6 三维四向编织某KD- Ⅰ SiC/SiC复合材料参数[30]
Table 6. Material parameters of three dimensional-four directional braided the KD- Ⅰ SiC/SiC composites[30]
参数 数值 弹性模量/GPa $ {E}_{1} $ 89 $ {E}_{2} $ 89 $ {E}_{3} $ 107 泊松比 $ {v}_{12} $ 0.27 $ {v}_{13} $ 0.24 $ {v}_{23} $ 0.24 切变模量/GPa $ {G}_{12} $ $ 38.60 $ $ {G}_{13} $ 38.20 $ {G}_{23} $ 38.20 热膨胀系数/10−6 K−1 $ {\alpha }_{1} $ 2.40 $ {\alpha }_{2} $ 2.40 $ {\alpha }_{3} $ 2.50 密度/(g/cm3) 2.00 表 7 设计截面的叶片表面温度
Table 7. Blade surface temperature of design sections
径向位置 r/cm 叶片表面温度 T/K 29.39 1240 31.47 1245 33.89 1252 36.32 1259 38.74 1268 40.97 1276 41.37 1278 表 8 叶片前5阶振型
Table 8. The first five mode shapes of blade
固有频率/Hz 振型 振型图 1644(1阶) 1阶弯曲振型 2503(2阶) 1阶扭转振型 4871(3阶) 1阶弯曲振型 5386(4阶) 2阶扭转振型 7006(5阶) 弯扭复合振型 -
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