为验证航空发动机轴对称矢量喷管控制系统的阶段性研究成果,开展了配装轴对称矢量喷管的航空发动机地面整机试车验证研究工作.试验选取了几个具有代表性的航空发动机典型工作状态点进行,首次进行了在阶跃输入条件下的航空发动机整机动态性能测试,获取了航空发动机矢量喷管控制系统静态性能和动态性能的基本数据,验证了航空发动机轴对称矢量喷管控制系统的有效性,总结了该系统的油源压力和流量对控制系统性能的综合影响,具有一定的工程应用价值.
It is an efficient way to study a new technical rearch on an exist engine. Based on a general gas turbine (turbofan) engine, a new method of verification is proposed for promoting variable cycle engine (VCE). This paper also presents a configuration promotion project with introduction of selector valve, forward variable area bypass injector (VABI) and rear VABI. The first stage of high pressure compressor is change to a core-driven fan stage (CDFS). The working principle of the VCE is stated. Based on the components performance level of general turbofan engine, a primary performance project is made and a numerical simulation on VCE is conducted. The calculation results show that the thrust can be increased by 5% to 8% in supersonic cruise using single bypass mode. Although specific fuel consumption cannot be decreased obviously in subsonic cruise using double bypass mode, the engine inlet air flux can be increased by 5%. And so the spillover is reduced and the intalled engine performance could be improved.
除夕的晚上,我在思乡的情绪中打开家乡捎来的艾菜罐头,烛光在年饭桌上诗一般地摇曳,一阵麻辣的气味串进鼻孔,我经受不了寒噤.眼圈开始温暖起来,朦胧中我看到透绿的艾菜叶在我颤动的筷子上闪着忧郁的光,仿佛向我传递故乡的云霓流逸,使我感知故乡冬季的田野,空中的月华以及月华中母亲的音容,若冰似玉.
The methods of the shell oilway design,check,assembly application and the design specification of aeroengine Hydraulic System Actuator by using UG were introduced.
根据已有研究成果,给出了飞机/发动机推力矢量综合控制系统的结构与控制逻辑,提出了研制飞机/发动机推力矢量综合控制系统对矢量喷管控制的要求和实现方法,最后对研制工作提出了建议.
