Advanced turboshaft engines will be required to support future Army Uninhabited AirVehicles (UAVs) and Objective Force Systems such as the A160, UCAR, Future CombatSystem, and Future Utility Rotorcraft. These systems will spend significant time at cruiseand as a result will require significantly improved part power engine performance. The intentof this program is to design and evaluate an inter-turbine burner that can significantlyimprove part power turboshaft engine performance. An innovative design is proposed thatwill potentially allow the size and weight of the burner reduced substantially. If sufficientgains can be realized, this technology would have potential application in main burners aswell as inter-turbine burners and could improve overall engine power to weight ratio.
Benefits: This Phase I program will produce the preliminary design of an innovative combustorconcept having accelerated burning rates that can be applied in inter-turbine burners forfuture military turboshaft engines. The adoption of this technology will significantly improvethe range and time-on-station capability of future aircraft. If fully successful the technologycan also be applied to gas turbine main burners and could significantly improve the overallpower-to-weight ratio of turboshaft engines.
Keywords: Inter-turbine burner, combustor, combustion, turboshaft, engine, ITB
