Abstract
Damage Tolerance Philosophies are being used today in the Design, Development, and Life Management of USAF turbine engines. The establishment of a Damage Tolerance Philosophy and implementation of a Fracture Control Program has been an integral part of the USAF turbine engine development process since 1978. It has been applied to new engine programs as part of the USAF’s Engine Structural Integrity Program (ENSIP) described in military standard 1783 issued formally in 1984. This military standard was reviewed and approved by the Aerospace Industries Association of America, Inc (AIA) in 1982. Damage Tolerance philosophy has also been applied to existing inventory USAF engines through structural durability and damage tolerance assessments. In all, fracture control programs have been applied to the F-100, TF-34, F100-PW-220, F100-PW-229, F110-GE-100, F110-GE-129, F101-GE-102, F109-GA-100, F-119, F120 and T406 engines and have resulted in the generation of NDE flaw size quantification probability of detection data and in implementation of enhanced nondestructive evaluation methods (i.e., eddy current) at manufacturing and at field/depot. Experience has shown that these inspection have been successful in detecting early cracking and in accelerating corrective actions. It has been highlighted that several development efforts in the last five years have been identified FPI process improvements that must be implemented within industry and Air Force depots to improve flaw detection reliability. The need to quantify detection reliability for imbedded defects is also identified. The engine development process has been evolutionary in terms of application of upgraded requirements. The new process of fracture control, sometimes referred to as damage tolerance, is contained in ENSIP and selects material as well as governs design and life management. Recent experience clearly demonstrates that the damage tolerance requirement is cost effective when assessed on a life cycle basis.
Published Version
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