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为确保发动机安全可靠运转,在基于地面高空台和飞行试验的空速/高度包线内进行了涡轮发动机的空中起动。发动机空中起动时间的差异可归因于以下不同因素:发动机再次起动转速(发动机核心转速,即发动机转子转速可以空起的转速)、燃烧室点火结束时间、各种安装效应(比如:引气、功率提取;起动机电机扭矩;燃油流量安排)以及发动机之间的差异和性能衰减。本文介绍的分析方法用于计算小涵道、双转子、军用涡扇发动机的上述不同因素,调整发动机空中起动时间。本文通过两个示例,说明空中起动时间的差异和用于调整起动时间的分析方法。
In order to ensure safe and reliable operation of the engine, air-start of the turbine engine was carried out within the airspeed / altitude envelope based on ground aerial platforms and flight tests. Engine start-up time differences can be attributed to the following different factors: engine restart speed (engine core speed, that is, the engine rotor speed can be empty of speed), the ignition end of the combustion chamber, a variety of installation effects (such as: bleed, Power draw; starter motor torque; fuel flow arrangements) and differences between engines and performance degradation. The analysis method introduced in this paper is used to calculate the different factors mentioned above for small bypass, twin rotor and military turbofan engines and to adjust the starting time of the engine in the air. This article shows two examples of differences in start-up time over the air and how to adjust start-up times.