Pre-Design and Analysis of a Military Hybrid High-Pressure Turbine

Abstract

Abstract. Increasing aero-engine turbine inlet temperatures and stagnating operational limits of nickel-based superalloys creates the need for new materials and cooling technologies. Ceramic matrix composites (CMCs) can operate at higher temperatures but restrict the geometrical freedom and thus the complexity of the component. Additive manufacturing (AM) facilitates intricate cooling designs but compromises high-temperature mechanical performance. To understand their potential benefit, we investigate a high-pressure turbine (HPT) concept with different material technologies per turbine row using the German Aerospace Center (DLR) pre-design toolkit from engine to airfoil level. Multiple configurations are analyzed and promising ones are identified. CMC vanes can lead to benefits in terms of coolant requirements, turbine efficiency, thrust-specific fuel consumption, and aircraft maximum takeoff mass, whereas AM blades lead to the opposite trend. The pre-design process is discussed, and special attention is given to military-specific design challenges such as multi-point performance.