Propulsion
本课程系统讲授航空航天推进系统的基本原理与工作特性。内容包括推进系统分类与性能参数，活塞式航空发动机原理，喷气发动机基本理论与热力循环，涡轮喷气发动机、涡轮风扇发动机、涡轮螺旋桨发动机的结构与工作原理，冲压发动机与火箭发动机基础。课程强调推进系统的性能分析与参数匹配，使学生掌握航空发动机的基本设计思想与性能评估方法。
This course systematically teaches fundamental principles and operating characteristics of aerospace propulsion systems. Topics include propulsion system classification and performance parameters, piston aircraft engines, jet engine theory and thermodynamic cycles, turbojet, turbofan, and turboprop engine structures and principles, ramjet and rocket engine fundamentals. The course emphasizes performance analysis and parameter matching, equipping students with basic design concepts and performance evaluation methods for aero engines.
学生需完成一台分开排气涡轮风扇发动机的设计点性能计算。给定飞行高度、马赫数、推力要求、涵道比、总增压比、涡轮前温度等设计参数，按部件依次计算进气道、风扇、压气机、燃烧室、高压涡轮、低压涡轮、尾喷管的气动参数与性能。计算发动机推力、耗油率等总体性能参数，并分析涵道比、增压比对发动机性能的影响规律。提交完整的计算程序与分析报告。
Students perform design-point performance calculation for a separate-exhaust turbofan engine. Given flight altitude, Mach number, thrust requirement, bypass ratio, overall pressure ratio, and turbine inlet temperature, calculate aerodynamic parameters and performance of inlet, fan, compressor, combustor, high-pressure turbine, low-pressure turbine, and nozzle. Compute overall performance including thrust and specific fuel consumption, and analyze effects of bypass ratio and pressure ratio on engine performance. Submit complete calculation program and analysis report.