US 12,352,182 B1
Turbine blade inner rib profile
Dallin T Hall, Greenville, SC (US)
Filed by GE Infrastructure Technology LLC, Greenville, SC (US)
Filed on Dec. 9, 2024, as Appl. No. 18/973,323.
Int. Cl. F01D 5/18 (2006.01)
CPC F01D 5/187 (2013.01) [F05D 2220/3212 (2013.01); F05D 2250/74 (2013.01); F05D 2260/22141 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A turbine blade comprising:
an airfoil having: a suction side, a pressure side opposing the suction side, a leading edge, a trailing edge, and a first rib separating a portion of an internal space defined between the suction and pressure sides and the leading and trailing edges into at least two internal channels; and
a platform connected with the airfoil along the suction and pressure sides and the leading and trailing edges, the airfoil and the platform including an origin at a junction of the leading edge of the airfoil and the platform;
wherein a portion of the first rib has a shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE I, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances from the origin by multiplying the values by a height of the airfoil expressed in units of distance, and wherein the Cartesian coordinate values of X, Y and Z are connected by smooth continuing arcs to define the nominal profile of the portion of the first rib.