The gasturbine is one of the major prime movers. In this course a number of applications (aeroplanes, industrial and turbochargers) will be discussed. First, a number of different systems (regeneration, intercooling, etc.) are compared using simple thermodynamics, which will lead to the efficiency and applicability of these systems. Next, axial compressors are described using compressible flow equations. This starts from a mid-span inlet and outlet angle description, and, via radial equilibrium equations, ends at a full three dimensional flow description. This description is than extended to turbines (introducing choking) and radial compressors (introducing the added effect of the centrifugal force). From all this both design and off-design behaviour can be described and the compressor and turbine map can be made plausible.
A key issue in gasturbine flows is the condition of the boundary layer. It determines e.g. the losses in the compressor and the heat transfer in both the combustor and turbine. Therefore, boundary layer theory will be treated.
Furthermore, simulations of compressible flows will be treated.
No learning objectives have been stated yet for this course.