NASA NTRS · 19800018159
Composite seal for turbomachinery
Abstract
A gas path seal suitable for use with a turbine engine or compressor is provided. A shroud wearable or abradable by the abrasion of the rotor blades of the turbine or compressor shrouds the rotor blades. A compliant backing surrounds the shroud. The backing is a compliant material covered with a thin ductile layer. A mounting fixture surrounds the backing.
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Bill, R. C., Ludwig, L. P.. 1980-06-10. Composite seal for turbomachinery. https://ntrs.nasa.gov/citations/19800018159
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