论文部分内容阅读
提高总增压比是下一代民用发动机的重要发展趋势之一,有必要对于这一特征的涡扇发动机进行循环参数的研究。利用已有基于Gasturb平台开发的0维变比热部件级性能计算模型,在发动机安装尺寸给定的前提下,总增压比由40提高至60,分析比较不同构型的直驱风扇方案与齿轮传动方案对部件效率,冷却水平对循环参数优选过程的影响。结果表明:为实现更低耗油率,采用更高设计循环增压比,需要部件效率平均提高1%,冷却水平提高20%,此时性能均优于现有的大涵道比涡扇发动机GTF-11。因此,若技术水平未能达到预期目标,则需匹配合适的增压比才能达到更低的耗油率。
Improving the total pressure ratio is one of the important development trends of the next generation of civilian engines. It is necessary to study the parameters of turbofan engines with this characteristic. Based on the 0-dimensional variable-ratio hot component-level performance calculation model developed based on Gasturb platform, the total pressure increase ratio is increased from 40 to 60 under the premise of engine installation size. The comparison and analysis of different direct drive fan configurations Effects of Gear Drive Programs on Component Efficiency, Cooling Level, and Optimization of Cycle Parameters. The results show that, in order to achieve lower fuel consumption, a higher design cycle pressure ratio is required, which needs an average increase of 1% in part efficiency and an increase in cooling level of 20%, at this time the performance is better than the existing large bypass ratio turbofan engine GTF-11. Therefore, if the technical level fails to achieve the desired goal, you must match the appropriate booster ratio in order to achieve lower fuel consumption.