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基于短距/垂直起降战斗机用三轴承旋转喷管的特殊设计要求,通过几何约束条件开展了三轴承旋转喷管型面设计方法及运动规律推导与研究,研究了非线性和线性两种喷管矢量角控制规律下的三段筒体随时间的旋转规律。根据小型涡轮喷气发动机的几何尺寸,利用发展的型面设计方法和喷管筒体旋转规律,设计了小尺寸三轴承旋转喷管,并利用CFD数值模拟技术对该喷管的流场特性进行了计算与分析。通过CFD数值模拟技术得到了不同矢量角下喷管的三维流动特性及不同落压比下的气动特性。结果表明:采用喷管矢量角非线性控制规律可以减少非线性控制变量,保证喷管机动性的前提下减小了喷管的设计难度和控制复杂度;基于小型涡轮喷气发动机设计的三轴承旋转喷管0°的推力系数较理想喷管低,90°的推力系数较理想喷管高,喷管在地面最大落压比下0°比90°推力系数高约1%。
Based on the special design requirements of three-bearing rotating nozzle for short-range / vertical take-off and landing fighter jets, the design method of three-bearing rotating nozzle profile and the law of motion are deduced and researched by geometrical constraints. The effects of nonlinear and linear jetting Rotation regularity of three sections of cylinder under the control law of tube vector angle with time. According to the geometry of the small turbojet engine, a three-bearing rotating nozzle with a small size was designed by using the developed profile design method and the rotating rule of the nozzle barrel. The flow field characteristics of the nozzle were analyzed by CFD numerical simulation Calculation and analysis. The three-dimensional flow characteristics of nozzles under different vector angles and the aerodynamic characteristics under different pressure ratios were obtained by CFD numerical simulation. The results show that the non-linear control law of the nozzle vector angle can reduce the nonlinear control variables and reduce the design difficulty and control complexity of the nozzle under the premise of ensuring the nozzle mobility. The three-bearing rotation based on the small turbojet design The thrust coefficient of nozzle 0 ° is lower than the ideal nozzle. The thrust coefficient of 90 ° is higher than the ideal nozzle. The nozzle is 0% higher than the 90 ° thrust coefficient by 1% at the max.