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Erosion and the gas turbine engine, part 2

Published 2011-08-15 From Legacy CDMS 1 author
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Attribution

This is the abstract and citation. Full text lives at NASA NTRS — we link out rather than host. All credit to the authors and Legacy CDMS.

Abstract

Verbatim from NASA NTRS. Not paraphrased, not summarized.

Procedures for protecting aircraft engines from impact damage due to sand and dust particles are discussed. One system is to develop a filtration system to remove most of the solid particles. Another method is to design blade materials and blade protection coatings. The concepts of erosion within aircraft engines are explained. Curves are presented to show the effect of impingement angle on ductile and elastic modes of erosion. Engine sand and dust ingestion tests were conducted on T63-A-5A engines and the results are produced in graph form. The results of tests conducted in a dynamic erosion facility are analyzed.

Author

  • Newhart, J. E. Naval Air Propulsion Test Center

Citation: Newhart, J. E. (2011). Erosion and the gas turbine engine, part 2. Legacy CDMS. NASA NTRS ID 19740018701. https://ntrs.nasa.gov/citations/19740018701 ↗