ABSTRACT
Module matching means the interplay of the engine geometry and engine parameters. It is not only a matching between a turbine and the driven compressor, but is also the global synchronization of the different modules including the diffuser, combustion chamber, nozzle and fan (for turbofan engines), afterburner (for afterburning engines), propeller (for turboprop engines), and load (for gas turbines and turbo shaft engines). Turbine is coupled either to a compressor or to a fan, thus forming an engine spool as described in Chapters 4 through 8. However, the performance matching between these two modules is influenced by their front and back modules. Choked nozzle influences the performance of its preceding elements. The diffuser, on the contrary, controls the mass flow and total pressure/temperatures of all the succeeding modules. If the diffuser incorporates a water injection system, the mass flow in the succeeding elements is influenced. Fuel addition and pressure drop in combustion chamber influences the performance of the following turbine and nozzle. Afterburner influences the mass flow rate and inlet pressure to the succeeding nozzle.
