Integrated Airflow Concepts For Helicopter Engine And Drive System

Integrated engine/transmission/air-frame conceptual designs are developed for a utility helicopter to meet projected airflow requirements of future Army aircraft, These requirements include engine compartment cooling, drive train and transmission oil cooling, engine oil cooling, exhaust plume and hot metal infrared (IR) signature suppression, and engine inlet foreign particle protection. The baseline utilized in the investigation is a single main rotor, twin-engine utility helicopter with a design gross weight of 8500 pounds. This paper presents six integrated concepts which are evaluated in comparison to the baseline aircraft propulsion system on the basis of overall system performance, complexity, aircraft weight, installation design, technical risk, and control requirements.