US 12,435,637 B2
Method for turbine blade and assembly with dovetail arrangement for enlarged rotor groove
Federico Cervetto, Zurich (CH); Salvador Mata López, Guanajuato (MX); and Steven Sebastian Burdgick, Schnectady, NY (US)
Assigned to GE Infrastructure Technology LLC, Greenville, SC (US)
Filed by GE Infrastructure Technology LLC, Greenville, SC (US)
Filed on May 13, 2024, as Appl. No. 18/662,043.
Application 18/662,043 is a division of application No. 18/295,413, filed on Apr. 4, 2023, granted, now 12,018,590.
Prior Publication US 2024/0337194 A1, Oct. 10, 2024
Int. Cl. F01D 5/30 (2006.01)
CPC F01D 5/303 (2013.01) [F05D 2220/30 (2013.01); F05D 2230/60 (2013.01)] 5 Claims
OG exemplary drawing
 
1. A method, comprising:
providing a rotor groove defined in a rotor having an axis, wherein the rotor groove extends in a circumferential direction of the rotor, and wherein the rotor groove includes a radially inward facing rotor hook and a radially outward facing surface;
on a turbine blade including a dovetail having a mounting arm and a single positioning leg extending from a radially inward facing end surface of the dovetail, adjusting the single positioning leg such that a first radial distance between the mounting arm and a radially inner end of the single positioning leg over a first part of the single positioning leg in at least one of an axial extent and a circumferential extent matches a second radial distance between the radially inward facing rotor hook and the radially outward facing surface of the rotor groove; and
mounting the dovetail of the turbine blade in the rotor groove.