Abstract: A gas turbine system including a compressor section, a combustor section and a turbine section, wherein the compressor section includes a first wheel and a second wheel having a center bore extending axially therethrough, and wherein the first wheel and the second wheel are relatively adjacent each other. Also included is a gap disposed between the first wheel and the second wheel, wherein airflow is directed radially inward within the gap toward the center bore of the second wheel with or without the help of impellers extending radially. The compressor section further includes an airflow manipulation device disposed within the gap, comprising of at least one or multiple vanes which may start in radial direction but extend at least partially into the center bore.

Abstract: A system includes a turbine. The turbine includes a first turbine blade comprising a leading edge, a blade platform coupled to the first turbine blade, and a protrusion disposed on the blade platform adjacent the leading edge of the first turbine blade. The protrusion is configured to increase a first static pressure of a cooling flow near the leading edge above a second static pressure of a hot gas flow near the leading edge.