US 11,946,386 B2
Turbine blade tip shroud surface profiles
William Scott Zemitis, Simpsonville, SC (US); and Robert Tomasz Liskiewicz, Warsaw (PL)
Assigned to GE Infrastructure Technology LLC, Greenville, SC (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Jun. 23, 2023, as Appl. No. 18/340,483.
Claims priority of application No. 441606 (PL), filed on Jun. 30, 2022.
Prior Publication US 2024/0003259 A1, Jan. 4, 2024
Int. Cl. F01D 5/14 (2006.01)
CPC F01D 5/141 (2013.01) [F05D 2240/307 (2013.01)] 19 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 spanning between the pressure side and the suction side, and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and
a tip shroud connected with the airfoil along the suction side, the pressure side, the trailing edge and the leading edge, the tip shroud including a forwardmost tip rail extending radially therefrom, the forwardmost tip rail having a forward edge including a suction side origin closest to the suction side of the airfoil and a pressure side origin closest to the pressure side of the airfoil, and a tip rail length defined by a straight line between the pressure side origin and the suction side origin,
wherein the forwardmost tip rail has a suction side scallop surface having a shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE I and originating at the suction side origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by the tip rail length expressed in units of distance, and wherein X, Y and Z values are connected by smooth continuing arcs that are joined smoothly with one another to form the nominal profile that defines the suction side scallop surface.