R. B. Mason, M. Singleton, M. Konrad, S. Scala, Concurrent Technologies Corporation, Largo, FL; D. Skelton, US Army, Picatinny Arsenal, NJ

Summary:

Under severe environmental operating conditions, such as a sand storm, a helicopter engine inevitably ingests particulate matter. As this ingested material impacts internal engine components at various velocities and angles, compressor component erosion results, leading to decreased compressor efficiency. This results in a decrease in delivered shaft horsepower, which can be reduced to the point where there is inadequate power delivered to the helicopter main rotor to produce sufficient lift.

Although there are real-time engine health monitoring systems currently available and installed aboard some aircraft, none have the capability to monitor particulate ingestion and provide the pilot with a display of remaining engine power margin based on such ingestion. The implementation of such a device could provide significant improvements in life cycle and maintenance costs, operator safety, and mission readiness to the Future Force. Concurrent Technologies Corporation is investigating the implementation of a gas turbine engine contaminant ingestion sensor under the US Army Technology Demonstration for the Prevention of Material Degradation Program. This paper describes the technologies that can be employed for a gas turbine engine contaminant ingestion sensor. Engine, sensor, and data processing requirements are discussed.