超高压比民用发动机部件技术水平初步研究

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。

Preliminary Study on Component Technologies of Ultra High Pressure Ratio of Civil Engine

Increasing the total pressure ratio is one of the most important development tendencies of the next generation civil engine. Therefore, a study on the cycle parameters of that engine is necessary. The component-level variable specific heat zero dimension models are developed based on Gasturb. The paper concentrates on how the efficiencies and cooling system influence design point cycle parameters along with total pressure ratio increasing from 40 to 60 based on the changeless inlet area. Those parameters of two different turbofans which are Advanced Turbo-Fan (ATF) and Geared Turbo-Fan (GTF) were optimized. Results show that a design with higher total pressure ratio to achieve the lowest Specific Fuel Consumption (SFC) needs 1% higher components efficiencies and 20% higher cooling technical level. Compared with the performance of GTF-11, the performance of the two turbofans were improved significantly. Consequently, if the components technical level can not meet expectations, the appropriate lower total pressure ratio may match the lower SFC.