Small gas turbine engines present a
significantlylower performance when compared to large
ones. The major reasons for that are the lower
component efficiencies and size effects. The present work
accomplishes an investigation of data available in the
open literature for small turbojet and turbofan engines,
covering a range from 1 to 5 kN of thrust, to find the most
important parameters for these engine configurations.
This study aims to evaluate the parameters used in
engines in this thrust range, for the possible development
of an engine for a specific application. This overview
relies on a correlation between some of the major
parameters of the engine, namely thrust, specific fuel
consumption, pressure ratio, turbine inlet temperature,
weight, length, diameter, and mass flow.
Bypass Ratio, Overall Pressure Ratio, Revolutions Per Minute, Specific Fuel Consumption.