Demonstration of Inter-Turbine Burners for Part-Power Improvements

Conventional gas turbine engines are often optimized for a specific narrow range of the flight envelope and perform much less efficiently at off-design conditions. Introduction of an inter-turbine burner (ITB) into a gas turbine design can add a level of adjustability to the engine performance that in turn provides improved operating efficiency over a wider range of the operating envelope. In the proposed project, we will identify jet aircraft and missions that could benefit from part power fuel efficiency improvements brought about by incorporation of an ITB into the engine. ITB and engine design concepts will be developed, analyzed, and tested. During the Phase I, the potential benefit will be quantified with cycle analyses, and design concepts will be analyzed for aerodynamic, thermal, and structural performance. Preliminary design concepts will be chosen and a Phase II test program scope will be defined.