New Lifing Methodology for Engine Fracture Critical Parts
Abstract
Within gas turbine aeroengines, fracture critical pans are defined as those whose failure would hazard the entire aircraft. Consequently, it is of central importance to the airworthiness of these engines that the probability of such a component suffering an in-service failure is kept below acceptable levels. In order to achieve this, lifing methodologies have been devised which provide a means for calculating the required limits. These methodologies consist of a material test requirement, together with a calculation process based on a statistical characterization of the material/component behavior. The outstanding safety record achieved by commercial and military aeroengines is in large part due to the success of these lifting methods.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 2003
- Accession Number
- ADP014140
Entities
People
- D. P. Shepherd
- S. J. Williams