Patent attributes
A component configured for use in a gas turbine engine, including: a wall portion formed from sheet metal and extending between two end portions, the wall portion being stamped with a plurality of instances of a pre-defined three dimensional shape structured to increase a stiffness of the wall portion in a direction normal to the wall portion, each instance of the plurality of instances of the pre-defined three dimensional shape being orientated at 90 degrees with respect to each other adjacent instance of the plurality of instances, wherein the three dimensional shape has a pair of curved distal peripheral end portions that are at opposite ends of the three dimensional shape and each pair of curved distal peripheral end portions are connected to each other by a pair of opposing concave peripheral portions that curve towards each other at a mid-section.
