摘要:本文利用实验与数值模拟的方法研究航空发动机涡轮叶栅在改变节距时,其总压损失、出口气流角及叶栅表面静压系数的变化。通过实验和数值计算的结果对比,验证了数值计算的准确性。数值模拟结果显示:相对节距珋t在0.5~1.0范围内变化,叶栅的总压损失在珋t=0.9时达最小;叶栅入口攻角从-10°逐渐增加至+10°时,总压损失呈现递增的趋势;随着相对节距每增加0.1,气流出口角相应增加大约2°;随着叶栅相对节距的增加,附面层增厚、脱离,叶型损失增大。%In this paper , cascade pitch is changed to find out the trend of total pressure , exit flow angle and surface static pressure co-efficient by experiment and numerical simulation .Contrast experiment result with numerical simulation , prove that numerical simulation is correct .The result of simulation show:Relative pitches of cascade are changed from 0.5 to 1.0 and find out that total pressure loss has a best result when relative pitch t=0.9;When angle of attack is increased from -10°to +10°, the total pressure loss also in-creases;Flow exit angle increases 2°with each 0.1 increase in relative pitch;With the increasing of relative pitch , boundary layer be-come thicker and separate from the cascade , profile loss increases .
摘要:根据重型燃气轮机的高压燃气调压器的工作原理,建立了能够描述调压器静态和动态特性的数学模型,并利用Matlab/Simulink软件建立了其仿真模型。通过数值仿真,分析了低压腔体积、弹簧弹性系数、皮膜面积等关键设计因素对燃气调压器静态和动态特性的影响。研究结果对燃气轮机燃气调压器的技术开发、设计和选型具有参考价值。%A mathematical model describing both the static and dynamic characteristics of high -pressure gas regulator used on the heav-y-duty gas turbines was established according to the working principle .Based on it a simulation model was built by using Matlab /Sim-ulink platform.The static and dynamic characteristics of the regulator with different key structural parameters were analysed , such as the volume of the low pressure chamber , the spring elasticity coefficient and the film area .The result is instructive for the model selec-tion and development of this kind of regulator .