AAE 590R Course Outline – Draft-Revised

1. Introduction (1 week)

— Brief history of gas turbine and rocket propulsion development

— Classification of aerospace propulsion systems

— Overview of rocket and airbreathing engine configurations

2. Ideal Nozzle Performance (2 weeks)

— Brief review of 1-D compressible flow

— Nozzle performance fundamentals

— Nozzle design

— Deviations from ideal performance

3. Combustion and Thermochemistry (2 weeks)

— First law of thermodynamics, fundamental energy balances

— Chemical equilibrium, adiabatic flame temperature and exhaust composition calculations

— Rocket nozzle thermochemistry

4. Heat Transfer Fundamentals (2 weeks)

— Mechanisms for heat transfer

o Conduction, convection, radiation

— Cooling schemes used in rocket/gas turbine engines

— Nozzle heat transfer

o Bartz equation

5. Turbomachinery and Turbopumps (2 weeks)

— Euler momentum equation, basic concepts

— Axial compressor and turbine on-design analysis

— Centrifugal compressor/pump on-design analysis

— Compressor/turbine maps

6. Chemical Rocket Engines (3 weeks)

— Liquid rocket engine (LRE) Cycles and Power Balance

o Components and component design

— Solid Rocket Motor (SRM) ballistics

o Components and component design

7. Gas Turbine Engines (3 weeks)

— Ideal engine cycle analysis for turbojet

— Component efficiencies, real turbojet engine analysis

— Other gas turbine cycles:  turbofan, turboprop, ramjet, scramjet