Abradable layer with glass microballoons
AssigneeRaytheon Technologies Corporation
InventorsKevin Seymour, Christopher W. Strock
Life of this patent
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Abstract
A gas turbine engine includes a circumferential row of blades, with the blades having respective blade tips. A seal is disposed about the blades. The seal has an abradable layer which the tips of the blades, at times, rub against when the blades rotate. The rubbing produces a maximum temperature at the abradable layer. The abradable layer includes a metal matrix and microballoons dispersed in the metal matrix. The microballoons are formed of a glass that has a glass transition temperature that is approximately 50° F. to 300° F. greater than the maximum temperature.
Claims19
A gas turbine engine comprising:
- a circumferential row of blades, the blades having respective blade tips;
- and
- a seal disposed about the blades, the seal having an abradable layer which the tips of the blades, at times, rub against when the blades rotate, there being a maximum temperature at the abradable layer without rubbing, the abradable layer including,
- a metal matrix, and
- microballoons dispersed in the metal matrix, the microballoons being formed of a glass having a glass transition temperature that is approximately 50° F. to 300° F. greater than the maximum temperature.
Dependencies are inferred from the claim text.