Gas turbine engine including seal assembly with abradable coating and cutter
AssigneeRaytheon Technologies Corporation
InventorsAgnieszka M. Wusatowska-Sarnek, Pantcho P. Stoyanov, Thomas D. Kasprow
Life of this patent
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Abstract
A gas turbine engine according to an exemplary aspect of this disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The gas turbine engine further includes a seal assembly including a static structure and a rotatable structure configured to meet to form a contact area. The seal assembly includes an abradable coating on one of the static structure and the rotatable structure, and the seal assembly further includes a cutter on the other of the static structure and the rotatable structure.
Claims20
A gas turbine engine comprising:
- a compressor section, a combustor section, a turbine section, and at least one rotatable shaft;
- and
- a seal assembly including a static structure and a rotatable structure configured to meet to form a contact area, wherein the seal assembly includes an abradable coating on one of the static structure and the rotatable structure, and wherein the seal assembly further includes a cutter on the other of the static structure and the rotatable structure.
A bearing compartment for a gas turbine engine, comprising:
- a bearing assembly;
- and
- a seal assembly including a static structure and a rotatable structure configured to meet to form a contact area, wherein the seal assembly includes an abradable coating on one of the static structure and the rotatable structure, and wherein the seal assembly further includes a cutter on the other of the static structure and the rotatable structure.
Dependencies are inferred from the claim text.