P.A. Domas

Damage Tolerance for aircraft gas turbine engines is the element of the engine life management process which recognizes the potential existence of component imperfections as the result of inherent material structure, material processing, component design, manufacturing or usage; and addresses this situation through incorporation of fracture resistant design concepts, fracture mechanics analysis, process control, and nondestructive inspection in the engine design, development, production, and field management. Airframe and engine research and development (RandD) in this field in recent years has appropriately targeted advancements in fracture mechanics and nondestructive evaluation (NOE), two key technology areas for Damage Tolerance. However, as more demanding performance (thrust-to-weight ratio) requirements lead to higher component usage temperatures and stresses, application of advanced high strength materials, and utilization of new design concepts, additional technology needs emerge. This paper discusses a range of other, applied engineering development topics where technological advancements would facilitate implementation of Damage Tolerance on aircraft engines. The appropriateness of cooperative Industry and Government RandD programs in these areas, to augment fracture mechanics and NOE developments, is emphasized.

5th International Conference on Structural Airworthiness of New and Aging Aircraft, Hamburg, 1993

Conference Paper

englisch

21,0 x 29,7 cm, 4 Seiten

DGLR-Bericht, 1993, 1993-02, 5th International Conference on Structural Airworthiness of New and Aging Aircraft - Proceedings; S.165-168; 1993; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

structural fatigue

Bestellbar

1993