Internally cooled turbine platform

A gas turbine engine comprising:

• a primary flowpath defined within, and fluidly connecting, a compressor section, a combustor section, and a turbine section;
• said turbine section including a plurality of stages;
• at least one of said stages including at least one turbine flowpath component further comprising:
• a platform defining at least one internal cooling cavity;
• a turbine flowpath component cover disposed radially outward of said platform, wherein the turbine flowpath component cover defines a radially outward edge of said at least one internal cooling cavity;
• and
• wherein the turbine flowpath component cover further defines a transition region in which a radial depth of the at least one internal cooling cavity varies from a first depth to a second depth, and a first region having a first radial depth on a first side of the transition region and a second region having a second radial depth on a second side of the transition region, and wherein the transition region transitions from the first radial depth to the second radial depth, said first region being an upstream edge of said at least one internal cooling cavity relative to a fluid flow through a gas turbine engine, and said second region is a downstream edge of said at least one internal cooling cavity relative to the fluid flow through the gas turbine engine;
• and
• wherein the first radial depth is a radial distance between the platform and the turbine flowpath component cover at an upstream edge of the at least one internal cooling cavity and wherein the second radial depth is a radial distance between the platform and the turbine flowpath component cover at a downstream edge of the at least one internal cooling cavity, and wherein the first radial depth is greater than the second radial depth;
• and
• wherein the turbine flowpath component cover maintains a constant angle relative to the platform through the transition region.