19. Turbomachinery

The following chapter consists of two sections. Section 19.1 presents a concise treatment of the theory of turbomachinery stages including the energy transfer in absolute and relative systems. Contrary to the traditional approach that treats turbine and compressor stages of axial, radial or mixed configurations differently, these components are treated from a unifying point of view. A detailed instruction in Sect. 19.2 for turbine and compressor blade design concludes Sect. 19.1

Section 19.3 is dedicated to steady and unsteady performance of gas turbine engines, where the components are treated as generic modules. Thus, any arbitrary power generation or aircraft gas turbine engine with single or multiple shafts can be composed of these modules. Several examples show, how different gas turbine configurations can be constructed and dynamically simulated. Finally, a section about the new generation gas turbines shows, how the efficiency of gas turbines can be improved far beyond the existing level. This chapter is based on [19.1], where the reader can find detailed explanation of relevant aerodynamic aspects of turbomachines, their component losses and efficiencies, and the design and off-design performance calculations.