大涵道比发动机核心机流量与推力相关性研究

唐宇峰，李长晖，丁宁，魏宝锋

中国航发沈阳发动机研究所，辽宁 沈阳  110015

摘要：为满足大涵道比发动机不同起飞推力的设计要求，对不同进气质量流量及压缩比的核心机采用Gasturb软件开展发动机起飞推力相关性研究；以压缩比最大、核心机进气质量流量最大的核心机为例，采用核心机低压部件重新匹配方法，试验设计不同推力量级下对应的发动机性能参数。结果表明：核心机进气质量流量对发动机起飞推力影响较大，核心机压缩比对发动机推力影响较小；核心机进气质量流量越大，发动机推力越大；降低低压部件级数，可减小发动机推力，但可能影响发动机油耗、尺寸、部件设计等；提高低压部件设计水平和增加低压部件级数，可增大发动机设计起飞推力，但应满足发动机温度裕度要求。

关键词：核心机；大涵道比发动机；核心机流量；推力

Correlation between core engine flow and thrust of a high bypass ratio engine

TANG Yufeng, LI Changhui, DING Ning, WEI Baofeng

AECC Shenyang Engine Research Institute, Shenyang 110015, China

Abstract: To meet the design requirements of different takeoff thrusts for high bypass ratio engines, a study on the correlation of engine takeoff thrust is conducted using Gasturb software based on core engines with varying intake mass flow rates and compression ratios. Taking the core engine with the highest compression ratio and the largest intake mass flow rate as an example, the method of re-matching the low-pressure components of the core engine is employed to design the engine performance parameters corresponding to different thrust levels. The results indicate that the intake mass flow rate of the core engine significantly affects the engine takeoff thrust, whereas the compression ratio has a smaller impact. The larger the intake mass flow rate of the core engine, the greater the engine thrust. Reducing the number of low-pressure component stages can decrease the engine thrust, but may affect fuel consumption, size, and component design. Enhancing the design level of low-pressure components and increasing the number of low-pressure component stages can increase the designed takeoff thrust of the engine, but the engine temperature margin requirements must be met.

Keywords: core engine; high bypass ratio engine; core engine flow; thrust