大涵道比轴流风扇增压级概念设计技术研究（英文）

Study of Conceptual Design of High Bypass Ratio Axial Fan Booster

本文为航空发动机设计培训总结报告。本培训目标为设计一款巡航状态下涡轮前温度(TET)1700K、可与LEAP发动机竞争的大涵道比航空发动机。为设计该发动机,需要进行市场调研、总体性能设计、总体结构设计、部件性能与结构设计等工作。为了进行大涵道比风扇增压级的设计工作,编写了轴流风扇增压级一维设计程序。在市场调研确定用户需求后,通过总体性能设计程序确定发动机总体性能参数,同时根据设计限制值开展风扇增压级的性能设计工作,得出风扇涵道比为9.6,风扇外涵压比和效率分别为1.6和0.91;风扇内涵压比和效率为2.0和0.90。

In the General Design Program(GDP)Training Program, a specified ultrahigh bypass ratio(BPR) aircraft engine with cruise TET 1700 K has been designed, and the aircraft engine shall be competitive with CFM LEAP. To develop the aircraft engine, customer requirements marketing research, overall performance and structure design, components performance and structure design have been implemented. The objective of this work is to develop an axial fan booster of aircraft engine. To design the ultrahigh BPR axial fan booster,a 1 D design procedure for axial fan and booster has been developed. The fan booster design is based on the requirements from marketing research, cycle parameters from overall performance design, and constraints from specification. The fan BPR is 9.6, fan bypass pressure ratio(PR) and isentropic efficiency are respectively 1.6 and 0.91;core PR and isentropic efficiency are respectively 2.0 and 0.90. It's concluded that all the parameters meet the requirements and the results are satisfactory.