Recommended Methodology for Army Helicopter Turbine Engine Component Vibration Qualification Testing

This paper will provide guidance on establishing a standard methodology for MIL-STD-810F based helicopter turbine engine component vibration qualification testing. The intent of such testing is to verify component operation in a representative vibratory environment, and to aid verification of component life. This methodology is intended as a general guide, and can serve as a default outline for testing when no flight data is available to tailor the applied vibration spectrum. This methodology involves consideration of airframe and engine induced vibratory inputs coupled with a broad spectrum random background vibratory input. It is recommended that aircraft vibratory frequencies be based on main rotor blade passage frequencies, that the narrow band spikes be based on engine compressor and power turbine speeds (fly and idle conditions), and that the broadband background be used to approximate other sources of noise over the entire airframe frequency spectrum not covered by the inputs detailed above.