Abstract: A platform seal assembly for a gas turbine engine with a turbine disk and a plurality of turbine blades is disclosed. The platform seal assembly includes a platform seal and a validation tab. The platform seal includes a first end, a second end, opposite and distal to the first end, and a body extending between the first end and the second end. The validation tab includes an attachment portion affixed to the platform seal and an observable indicator portion extending from the attachment portion.

Abstract: A method for designing a component for a circumferential machine is disclosed. The method includes selecting one or more seed nodes, creating a cylindrical coordinate system, and selecting an output subset. The method further includes creating a node set from the one or more seed nodes based on a selected feature of the component to be analyzed. The method yet further includes extracting an output for the node set from the finite element analysis module for each load cycle and presenting a result from the extracted output.

Abstract: A component for a gas turbine engine is disclosed. The component includes at least a first portion and a second portion, and a data representing matrix. The second portion includes a second portion surface. The data representing matrix is formed directly on the second portion surface and includes a plurality of contrasting cells arranged in a geometric pattern representing information about the component including test data, a serial number, and a part number. The plurality of contrasting cells includes a plurality of first cells and a plurality of second cells that contrast from the plurality of first cells.

Abstract: A method for designing a component for a circumferential machine is disclosed. The method includes selecting one or more seed nodes, creating a cylindrical coordinate system, and selecting an output subset. The method further includes creating a node set from the one or more seed nodes based on a selected feature of the component to be analyzed. The method yet further includes extracting an output for the node set from the finite element analysis module for each load cycle and presenting a result from the extracted output.

Abstract: A platform seal assembly for a gas turbine engine with a turbine disk and a plurality of turbine blades is disclosed. The platform seal assembly includes a platform seal and a validation tab. The platform seal includes a first end, a second end, opposite and distal to the first end, and a body extending between the first end and the second end. The validation tab includes an attachment portion affixed to the platform seal and an observable indicator portion extending from the attachment portion.

Abstract: A gas turbine engine turbine disk assembly includes a turbine disk, turbine blades, and pin seals. Each turbine blade includes a platform with a pressure side seal slot extending into a pressure side of the platform and a suction side seal slot extending into a suction side of the platform. The pressure side seal slot and the suction side seal slot are each angled between three and ten degrees in the radial direction relative to the axis of the turbine disk. The pin seal includes a cylindrical shape and is located within a seal slot formed from the pressure side seal slot and the suction side seal slot of adjacent turbine blades.

Abstract: A gas turbine engine turbine disk assembly includes a turbine disk, turbine blades, and pin seals. Each turbine blade includes a platform with a pressure side seal slot extending into a pressure side of the platform and a suction side seal slot extending into a suction side of the platform. The pressure side seal slot and the suction side seal slot are each angled between three and ten degrees in the radial direction relative to the axis of the turbine disk. The pin seal includes a cylindrical shape and is located within a seal slot formed from the pressure side seal slot and the suction side seal slot of adjacent turbine blades.