This article presents shortly reasons for improving designs of turboprop and turboshaft engines, and describes aero-thermodynamic aspects of methods or modification of these devices. The theoretical analysis of methods or modification concerns general changes or efficiency, flow, and rating. The influence of the following factors on engine performance is presented: change of efficiency or engine units, increase of compression and flow rate by using a compressor zerostage, change of compressor pressure ratio, changes of gas temperature keeping the gasgenerator rotational speed constant by adjusting the minimal throat area of turbine nozzle guide vanes, turbornachinery modelling, and changes of rotational speed of ratings.