Aims: To provide knowledge of the development, performance and design of gas-turbine aeroengines. To apply the fundamentals of fluid mechanics and thermodynamics to the performance and design of aircraft and aeroengines. To introduce the basic mechanics of turbomachinery.
Learning Outcomes:
After taking this unit the student should be able to:Understand the fundamental differences between the performance characteristics of turbojet, turbofan and turboprop engines. Analyse thermodynamic cycles for turboprop, turboshaft, turbojet and turbofan engines. Understand principles and performance of compressor, turbine, combustor, intake and exhaust nozzle. Calculate performance of engines at design and off-design conditions. Understand basic turbomachinery design.
Skills:
Problem solving and numeracy (taught and assessed).
Content:
Birth of jet engine; engine classification; operational envelope; thrusts and efficiencies; thermodynamic cycles (turboshaft, turbojet, turbofan); combustors; intakes (subsonic and supersonic), afterburners and nozzles; design and off-design performance; turbine cooling.
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