CPC F01D 11/125 (2013.01) [F05D 2220/32 (2013.01); F05D 2230/31 (2013.01); F05D 2240/55 (2013.01)] | 18 Claims |
1. An abradable insert for a gas turbine engine, the abradable insert comprising:
a base layer;
a lattice layer connected to the base layer, wherein the lattice layer comprises a series of walls that define a plurality of cells; and
a sheet layer connected to the lattice layer on an opposite side on the lattice layer from the base layer, wherein the sheet layer is curved and includes a direction of concavity that points away from the base layer;
an intermediate sheet layer, wherein the intermediate sheet layer is disposed between the sheet layer and the base layer, wherein the intermediate sheet layer divides the plurality of cells into a first layer of cells and a second layer of cells;
wherein the sheet layer, the intermediate sheet layer, or both comprise a plurality of dimples, wherein each dimple of the plurality of dimples is aligned with a cell of the plurality of cells.
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