This course consists of five basic elements which are basic propulsion considerations, turbomachinery, gas dynamics, propeller based propulsion and environmental considerations.

tbd

None

None

95% Written examination

5% Report

This course aims to provide the basic theory, including thermodynamics and gas flow, that underlies various methods used to propel aircraft including gas turbines and rocket engines. It also aims to give an awareness of the environmental impact of aircraft propulsion and to provide practical experience in the laboratory.

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

■ compare the relative advantages of the various aircraft propulsion methods;

■ describe and differentiate the basic principles of propellers, axial and centrifugal compressors and axial flow turbines;

■ describe and apply the basic design procedure of gas turbine compressors and turbines;

■ evaluate the design of a combustion system for a gas turbine and a simple modelling procedure for it;

■ elucidate the design problems of nozzles for aircraft propulsion and rockets;

■ evaluate the problems of intake design for aircraft gas turbines;

■ describe the causes of pollution by aircraft;

■ test a gas turbine and measure the flow of gas under conditions when compressibility is significant;

■ solve problems in gas turbines and propulsion with a clear, analytical approach;

■ write reports that show mature technical communication skills.

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

Students must attend the timetabled laboratory classes.

Students should attend at least 75% of the timetabled classes of the course.

Note that these are minimum requirements: good students will achieve far higher participation/submission rates.  Any student who misses an assessment or a significant number of classes because of illness or other good cause should report this by completing a MyCampus absence report.