Turbine Burner for Near-Constant Temperature Cycle Gas Turbine Engine

The proposed Phase II SBIR addresses the question of how the potential performance benefits demonstrated for the constant-temperature cycle aircraft gas turbine may actually be realized in an engine. The approach used is to take the engine design choicesand cycle performance for a constant-temperature cycle high bypass ratio, high thrust turbofan from the Phase I results, and layout the engine using a mean-line design process for component sizing and configuration. The proposal includes an enablingtechnology assessment, combustion component concept definition, sizing and performance evaluation, and an overall engine viability and risk assessment. The overall objective is to demonstrate that the constant-temperature cycle gas turbine engine concepthas the potential to be turned into a viable piece of turbo-machinery while achieving its performance benefits.