Blade Containment Evaluation of Civil Aircraft Engines

AbstractThe potential hazard resulting from an uncontained turbine engine rotor blade failure has always been the long-term concern of aeroengine manufacturers, and to fully contain the failed blades under critical operating conditions is also one of the most important considerations to meet the rotor integrity requirements. There are many factors involving the engine containment capability which need to be reviewed during the engine design phase, such as case thickness, rotor support structure, blade weight and shape, etc. However, the most suitable method to demonstrate the blade containment capability is the fan blade-off test and Margin of Safety (MS) analysis. Based on a concrete engine model, this paper aims to explain the key points of aero engine containment requirements in FAR Part 33, and introduce the implementation of MS analysis and fan blade-off test in the engine airworthiness certification. The information provided here will be greatly helpful to the industrial community to evaluate the engine containment capability and prepare the final test demonstration in engine certification