Design and Construction of a Gas Turbine Engine to Test Validity of Hybrid Combustion Systems for Use in High Altitude Aircraft Propulsion

The purpose of designing and constructing this engine is to investigate the application of hybrid and alternative combustion systems as applied to gas turbine engines used for aircraft propulsion. The interest in this type of system comes from undesirable performance of gas turbine engines at extreme altitudes. The engine is a high-bypass, two-spooled turbofan with the inner spool and combustion system located on the outside of the fan bypass duct. This unusual arrangement is to allow greater flexibility in combustion system modifications as well as to better facilitate maintenance and modification work without disturbing the fan spool. The hope is to evaluate the feasibility of a hypothetical gas turbine jet engine specifically designed for use at extreme altitude. (Figure 1)