초록 ▼

A turbine rotor blade includes a mounting portion that partially defines a cooling circuit within the turbine rotor blade and an airfoil portion that extends radially outward from the mounting portion. The airfoil portion further defines the cooling circuit. The turbine rotor blade further includes

A turbine rotor blade includes a mounting portion that partially defines a cooling circuit within the turbine rotor blade and an airfoil portion that extends radially outward from the mounting portion. The airfoil portion further defines the cooling circuit. The turbine rotor blade further includes a platform portion that is disposed radially between the mounting portion and the airfoil. The platform portion includes a bottom wall, a top wall, a forward wall, an aft wall and a pair of opposing side walls. A cooling plenum that at least partially defines the cooling circuit is defined within the platform portion. The cooling plenum is at least partially defined between the forward wall, the aft wall and between the pair of opposing side walls.

대표청구항 ▼

1. A turbine rotor blade, comprising: a mounting portion that partially defines a cooling circuit within the turbine rotor blade;an airfoil portion that extends radially outward from the mounting portion, the airfoil portion further defining the cooling circuit;a platform portion disposed radially b

1. A turbine rotor blade, comprising: a mounting portion that partially defines a cooling circuit within the turbine rotor blade;an airfoil portion that extends radially outward from the mounting portion, the airfoil portion further defining the cooling circuit;a platform portion disposed radially between the mounting portion and the airfoil, the platform portion having a bottom wall, a top wall, a forward wall, an aft wall and a pair of opposing side walls;a cooling plenum defined within the platform portion, the cooling plenum further defining the cooling circuit, wherein the cooling plenum is at least partially defined between the forward wall, the aft wall and between the pair of opposing side walls; andan exhaust outlet that extends through the bottom wall, wherein the exhaust outlet provides for fluid communication out of the cooling plenum. 2. The turbine rotor blade as in claim 1, further comprising a shank portion that extends between the mounting portion and the airfoil portion, the shank portion being at least partially encased within the cooling plenum. 3. The turbine rotor blade as in claim 1, further comprising an exhaust outlet that extends through one of the opposing side walls, wherein the exhaust outlet provides for fluid communication out of the cooling plenum. 4. The turbine rotor blade as in claim 1, wherein the top wall includes an inner side disposed within the cooling plenum, the turbine rotor blade further comprising an impingement plate that extends within the cooling plenum substantially parallel to the inner side, wherein the impingement plate defines a first cooling chamber and a second cooling chamber within the cooling plenum. 5. The turbine rotor blade as in claim 4, wherein the impingement plate includes a plurality of impingement cooling holes that provide for fluid communication between the first cooling chamber and the second cooling chamber. 6. The turbine rotor blade as in claim 4, further comprising one or more baffles that extend between the bottom wall and the impingement plate within the cooling plenum substantially proximate to at least one of the forward wall, the aft wall or the pair of opposing side walls. 7. The turbine rotor blade as in claim 6, further comprising one or more impingement cooling holes that extend through the baffle, wherein the impingement cooling holes are in fluid communication with the first cooling chamber. 8. A turbine section of a gas turbine, comprising: a rotor shaft;a rotor disk coupled to the rotor shaft, the rotor disk including a slot, the rotor disk defining a cooling flow outlet that extends through the slot;a turbine rotor blade that extends radially outward from the rotor disk, the turbine rotor blade comprising: a mounting portion disposed within the slot;an airfoil portion that extends radially outward from the mounting portion;a cooling circuit that extends between the mounting portion and the airfoil portion, wherein the cooling circuit is in fluid communication with the cooling flow outlet;a platform portion disposed radially between the mounting portion and the airfoil portion, the platform portion having a bottom wall, a top wall, a forward wall, an aft wall and a pair of opposing side walls;a cooling plenum defined within the platform portion, the cooling plenum further defining the cooling circuit, wherein the cooling plenum is at least partially defined between the forward wall, the aft wall and between the pair of opposing side walls within the platform portion; and an exhaust outlet that extends through the bottom wall, wherein the exhaust outlet provides for fluid communication out of the first cooling chamber towards the rotor disk. 9. The turbine section as in claim 8, further comprising one or more exhaust outlets that provide for fluid communication through one or more of the pair of opposing side walls, the top wall, the forward wall or the aft wall. 10. The turbine section as in claim 8, wherein the top wall includes an inner side disposed within the cooling plenum, the turbine rotor blade further comprising an impingement plate that extends within the cooling plenum substantially parallel to the inner side, wherein the impingement plate defines a first cooling chamber and a second cooling chamber within the cooling plenum. 11. The turbine section as in claim 10, wherein the impingement plate includes a plurality of impingement cooling holes that provide for fluid communication between the first cooling chamber and the second cooling chamber to impinge a flow of a cooling medium onto the inner side. 12. The turbine section as in claim 10, further comprising a baffle that extends between the bottom wall and the impingement plate within the cooling plenum substantially proximate to at least one of the forward wall, the aft wall or the pair of opposing side walls. 13. The turbine section as in claim 10, further comprising one or more impingement cooling holes that extend through the baffle, wherein the impingement cooling holes are in fluid communication with the first cooling chamber. 14. A turbine rotor blade, comprising: a mounting portion that partially defines a cooling circuit within the turbine rotor blade;an airfoil portion that extends radially outward from the mounting portion, the airfoil portion further defining the cooling circuit;a platform portion disposed radially between the mounting portion and the airfoil, the platform portion having a bottom wall, a top wall, a forward wall, an aft wall and a pair of opposing side walls;a cooling plenum defined within the platform portion, the cooling plenum further defining the cooling circuit, wherein the cooling plenum is at least partially defined between the forward wall, the aft wall and between the pair of opposing side walls,wherein the top wall includes an inner side disposed within the cooling plenum, the turbine rotor blade further comprising an impingement plate that extends within the cooling plenum substantially parallel to the inner side, wherein the impingement plate defines a first cooling chamber and a second cooling chamber within the cooling plenum, and wherein the impingement plate is disposed within both a pressure side portion and a suction side portion of the platform portion. 15. The turbine rotor blade as in claim 14, further comprising a shank portion that extends between the mounting portion and the airfoil portion, the shank portion being at least partially encased within the cooling plenum. 16. The turbine rotor blade as in claim 14, wherein the impingement plate includes a plurality of impingement cooling holes that provide for fluid communication between the first cooling chamber and the second cooling chamber. 17. The turbine rotor blade as in claim 14, further comprising one or more baffles that extend between the bottom wall and the impingement plate within the cooling plenum substantially proximate to at least one of the forward wall, the aft wall or the pair of opposing side walls. 18. The turbine rotor blade as in claim 17, further comprising one or more impingement cooling holes that extend through the baffle, wherein the impingement cooling holes are in fluid communication with the first cooling chamber.