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An apparatus for cooling turbine blades in a turbine engine including a direct transfer axial tangential onboard injector (TOBI) for a turbine rotor and a self-supporting seal plate disposed on a rotating disk for the turbine engine. The TOBI includes a plurality of openings emanating a flow of cool

An apparatus for cooling turbine blades in a turbine engine including a direct transfer axial tangential onboard injector (TOBI) for a turbine rotor and a self-supporting seal plate disposed on a rotating disk for the turbine engine. The TOBI includes a plurality of openings emanating a flow of cooling air. The self-supporting seal plate comprises a plurality of shaped cooling holes in fluid communication with the flow of cooling air emanating from the TOBI. The rotating disk includes a plurality of turbine blade slots formed therein. The plurality of cooling holes are in fluid communication with the plurality of turbine blade slots for directing the flow of cooling air to provide cooling to the plurality of turbine blades. The plurality of openings, the plurality of cooling holes and the plurality of turbine blade slots are in axial alignment and optimized to minimize radial and hoop stresses.

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1. An apparatus, comprising: a tangential onboard injector (TOBI) for a turbine rotor having a plurality of openings emanating a flow of cooling air;a self-supporting seal plate having a plurality of cooling holes in fluid communication with the flow of cooling air emanating from the tangential onbo

1. An apparatus, comprising: a tangential onboard injector (TOBI) for a turbine rotor having a plurality of openings emanating a flow of cooling air;a self-supporting seal plate having a plurality of cooling holes in fluid communication with the flow of cooling air emanating from the tangential onboard injector (TOBI); anda rotating disk of a gas turbine engine including a plurality of turbine blade slots formed therein, wherein the self-supporting seal plate is disposed on the rotating disk,wherein the plurality of cooling holes are in fluid communication with the plurality of turbine blade slots for directing the flow of cooling air to provide cooling to a plurality of turbine blades of the gas turbine engine;wherein each of the plurality of cooling holes has an elliptical geometry to reduce operating hoop stresses;wherein the plurality of openings, the plurality of cooling holes and the plurality of turbine blade slots are in axial alignment; andwherein the plurality of cooling holes and the plurality of blade slots are in an abutting relationship. 2. The apparatus of claim 1, wherein the tangential onboard injector (TOBI) is a direct transfer axial injector system. 3. The apparatus of claim 2, wherein each of the plurality of cooling holes is sized and shaped to provide reduced operating stresses. 4. The apparatus of claim 3, wherein each of the plurality of cooling holes has a thickness optimized to reduce operating radial stresses. 5. The apparatus of claim 4, wherein each of the plurality of cooling holes is formed as an elongated, chamfered hole. 6. The apparatus of claim 3, wherein the plurality of cooling holes are uniformly spaced radially about the self-supporting seal plate. 7. The apparatus of claim 1, wherein each of the plurality of turbine blade slots is defined by an opening having an upper portion wherein a root portion of the turbine blade is inserted and a lower portion for directing the flow of cooling air to the turbine blade. 8. The apparatus of claim 7, wherein the lower portion of each of the plurality of turbine blade slots includes a radius in axial alignment with a radius of one of the plurality of cooling holes and one of the plurality of openings formed in the tangential onboard injector (TOBI). 9. The apparatus of claim 1, wherein each of the plurality of openings are disposed in the tangential onboard injector (TOBI) at an angle inclined with respect to a central axis of the apparatus. 10. An apparatus, comprising: a direct transfer axial tangential onboard injector (TOBI) for a turbine rotor having a plurality of openings emanating a flow of cooling air;a self-supporting seal plate including a plurality of elongated shaped cooling holes in fluid communication with the flow of cooling air emanating from the direct transfer axial tangential onboard injector (TOBI); anda rotating disk of a gas turbine engine including a plurality of turbine blade slots formed therein, wherein the self-supporting seal plate is disposed on the rotating disk,wherein the plurality of elongated shaped cooling holes are in fluid communication with the plurality of turbine blade slots for directing the flow of cooling air to provide cooling to a plurality of turbine blades of the gas turbine engine,wherein the plurality of openings, the plurality of elongated shaped cooling holes and the plurality of turbine blade slots are in axial alignment;wherein each of the plurality of elongated shaped cooling holes has a substantially elliptical geometry; andwherein the plurality of cooling holes and the plurality of blade slots are in an abutting relationship. 11. The apparatus of claim 10, wherein the plurality of elongated shaped cooling holes are equally sized. 12. The apparatus of claim 10, wherein the plurality of elongated shaped cooling holes are uniformly spaced radially about the self-supporting seal plate. 13. The apparatus of claim 10, wherein each of the plurality of turbine blade slots is defined by an opening having an upper portion wherein a root portion of the turbine blade is inserted and a lower portion for directing the flow of cooling air to the turbine blade. 14. The apparatus of claim 13, wherein the lower portion of each of the plurality of turbine blade slots includes a radius in axial alignment with a radius of one of the plurality of elongated shaped cooling holes and one of the plurality of openings formed in the direct transfer axial tangential onboard injector (TOBI). 15. The apparatus of claim 10, wherein each of the plurality of openings are disposed in the direct transfer axial tangential onboard injector (TOBI) at an angle inclined with respect to a central axis of the apparatus. 16. A gas turbine engine comprising: a compressor section;a combustor section; anda turbine section, wherein the turbine section comprises: a tangential onboard injector (TOBI) for a turbine rotor having a plurality of openings emanating a flow of cooling air;a self-supporting seal plate having a plurality of cooling holes of elliptical geometry in fluid communication with the flow of cooling air emanating from the tangential onboard injector (TOBI); anda rotating disk including a plurality of turbine blade slots formed therein, wherein the self-supporting seal plate is disposed on the rotating disk,wherein the plurality of cooling holes are in fluid communication with the plurality of turbine blade slots for directing the flow of cooling air to provide cooling to a plurality of turbine blades of the gas turbine engine;wherein the plurality of openings, the plurality of cooling holes and the plurality of turbine blade slots are in axial alignment; andwherein the plurality of cooling holes and the plurality of blade slots are in an abutting relationship. 17. The gas turbine engine of claim 16, wherein the cooling air is produced in a combustion plenum of the gas turbine engine. 18. The gas turbine engine of claim 17, wherein the tangential onboard injector (TOBI) is a direct transfer axial injector system.