Course contents *
The course is a continuation of MJ2241 Jet Propulsion Engines, General Course and therefore starts at an advanced level. As the nucleus of present-day aircraft engines consists of gas turbines, the course is to a large extent coordinated with the course MJ2430 Thermal turbomachinery. Propulsion of modern aircraft would not be possible without thermal turbomachines that are characterised by unrivalled power density.
The course starts with an introduction of simple calculus of one variable and turbomachine components and then the level of the course is extended to 2D and 3D analysis aspects. Important aspects such as cooling in combustion turbines, mechanical effects, material and the properties of the system are highlighted in the course and introduced in relevant contexts.
Special focus is placed on discussion of aerodynamic design of vanes for turbofan engines, as these produce the majority of thrust in propulsion of passenger aircraft.
Critical review of scientific articles will be carried out within the frame of the course to stimulate to discussions in an interdisciplinary environment. Practical assignments will be given to deepen the student's understanding of the phenomena treated in the course. A study visit to a gas turbine manufacturer or a relevant company is planned.
The course is given in English
Note: The course may not be chosen, if one follows or has taken the course MJ2430 Thermal turbomachinery.
Intended learning outcomes *
The course intends to give an overview of important aspects in the thermal turbomachines with a focus on applications in the air transport sector and in the energy sector
After passing the course, the student should be able to:
1. Explain stationary 2D and 3D flow phenomena for turbomachinery components
2. Carry out aerodynamic 3D design of fan blades for turbo fan engines
3. Explain the fluid-structural interaction in thermal turbomachines
4. Describe the non-stationary flow phenomena in turbomachines
5. Solve problems regarding aeromechanics for turbo machinery blades
6. Describe heat transfer for warm components, material aspects, combustion chamber principles and operational characteristics for thermal turbomachines
7. Carry out measurements and analyse the transient vane loads in an oscillating cascade
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