US 9,810,070 B2
Turbine rotor blade for a turbine section of a gas turbine
David Richard Johns, Simpsonville, SC (US); and Mark Andrew Jones, Greer, SC (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on May 15, 2013, as Appl. No. 13/894,622.
Prior Publication US 2014/0338364 A1, Nov. 20, 2014
Int. Cl. F01D 5/08 (2006.01); F01D 5/18 (2006.01); F01D 5/30 (2006.01)
CPC F01D 5/084 (2013.01) [F01D 5/081 (2013.01); F01D 5/187 (2013.01); F01D 5/3007 (2013.01); F05D 2240/81 (2013.01); F05D 2260/201 (2013.01)] 18 Claims
OG exemplary drawing
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; and
an exhaust outlet that extends through the bottom wall, wherein the exhaust outlet provides for fluid communication out of the cooling plenum.