The course presents the principles of gas turbine propulsion systems for aircraft.  Throughout the course, the overall procedure and methodology for designing a propulsion device is presented, starting from the aircraft concept and the associated engine requirements, through to the performance analysis of the thermodynamic cycle and the aero-thermal design of the engine components.

2 lectures per week

None

None

50% Written Exam

50% Set Exercise

The aims of this course are to:

■ Provide an introduction to the overall design process for aerospace gas turbines from the initial concept based on the aircraft requirements through to meeting certification requirements;

■ Introduce key aspects of the thermodynamic cycle design and performance characteristics of aerospace propulsion systems, including key design variables, parametric investigation of performance and off design analysis;

■ Introduce key aspects of the design and limitations of aero-thermal components, including compressors, turbines and combustion systems.

By the end of this course students will be able to:

■ apply mathematical analysis to gas turbine thermodynamic systems, rigorously and accurately;

■ critically assess and apply the basic measures of performance for aerospace gas turbine engines and evaluate aircraft mission criteria to assess the performance constraints when determining the appropriate propulsion configuration;

■ describe and apply the overall design process for a gas turbine from initial concept to testing for certification;

■ calculate the necessary performance requirements for the propulsion system from the aircraft mission criteria and critically assess the key design parameters that control and influence the overall engine performance, demonstrating through analysis that design criteria are met;

■ complete a detailed analysis of the thermodynamic cycle of a modern aerodynamic gas turbine to meet specific performance requirements and demonstrate how the engine configuration can be optimised for both design and off-design conditions;

■ evaluate the aero-thermal design of the turbomachinery components (compressors; turbines) and elucidate the associated design problems along with material and performance limitations of these components.

Students must attend the degree examination and submit at least 75% by weight of the other components of the course's summative assessment.