Abstract: A radial-flow turbine wheel is provided. The radial-flow turbine wheel includes a hub having an outer radius gradually increasing from a front end to a rear end, a rear periphery of the hub being radially extended in a plane generally perpendicular to a center axis, and a plurality of turbine blades formed around the hub at constant intervals. A plurality of slots is formed by inward cuts at the rear periphery of the hub between the turbine blades of the hub. The turbine wheel restrains creation and propagation of cracks due to thermal stress, as well as improving a turbine efficiency.

Abstract: A gas turbine engine includes an interstage seal assembly positioned in a plenum between the compressor section and turbine section. The seal assembly includes an annular seal member positioned in the plenum adjacent to the compressor section for restraining a fluid flow between the compressor section and the turbine section, and an annular heat shield member positioned in the plenum adjacent to the turbine section for limiting heat transfer from the turbine section to the compressor section. The annular heat shield member includes a plurality of slots formed on a surface of the heat shield member in a radial direction of the annular heat shield member.

Abstract: A radial-flow turbine wheel is provided. The radial-flow turbine wheel includes a hub having an outer radius gradually increasing from a front end to a rear end, a rear periphery of the hub being radially extended in a plane generally perpendicular to a center axis, and a plurality of turbine blades formed around the hub at constant intervals. A plurality of slots is formed by inward cut at the rear periphery of the hub between the turbine blades of the hub. The turbine wheel restrains creation and propagation of crack due to thermal stress, as well as improving a turbine efficiency.

Abstract: A gas turbine engine includes an interstage seal assembly positioned in a plenum between the compressor section and turbine section. The seal assembly includes an annular seal member positioned in the plenum adjacent to the compressor section for restraining a fluid flow between the compressor section and the turbine section, and an annular heat shield member positioned in the plenum adjacent to the turbine section for limiting heat transfer from the turbine section to the compressor section. The annular heat shield member includes a plurality of slots formed on a surface of the heat shield member in a radial direction of the annular heat shield member.