Method for turbine blade and assembly with dovetail arrangement for enlarged rotor groove
A method for a turbine blade assembly for a rotor groove is disclosed. A dovetail of the turbine blade includes a mounting arm and an end surface facing radially inward relative to the rotor axis. An extension insert includes a first end configured to contact the end surface of the dovetail and a second end. A single positioning leg extends radially inward relative to the axis from the second end of the insert. The dovetail and the extension insert are configured to be positioned in the rotor groove to mount the turbine blade to the rotor. The mounting arm engages a radially inward facing rotor hook of the rotor groove and the positioning leg engages one of a radially outward facing surface of the rotor groove and a planar plate shim between the positioning leg and the radially outward facing surface of the rotor groove.
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.
2. The method of claim 1 , wherein providing the rotor groove includes machining the rotor groove to enlarge the second radial distance between the radially inward facing rotor hook and the radially outward facing surface of the rotor groove.
3. The method of claim 1 , wherein adjusting the single positioning leg further comprises:
adjusting the single positioning leg such that the first radial distance between the mounting arm and the radially inner end of the single positioning leg over a second part of the single positioning leg in the at least one of an axial extent and a circumferential extent is less than the second radial distance between the radially inward facing rotor hook and the radially outward facing surface of the rotor groove, and
wherein the mounting further includes positioning at least one planar plate shim between the second part of the single positioning leg and the radially outward facing surface of the rotor groove.
4. The method of claim 1 , wherein the mounting arm engages the radially inward facing rotor hook of the rotor groove, the first part of the single positioning leg engages the radially outward facing surface of the rotor groove, and a second part of the single positioning leg engages a planar plate shim between the single positioning leg and the radially outward facing surface of the rotor groove.
5. The method of claim 1 , wherein adjusting the single positioning leg is done prior to mounting a turbine blade assembly in the rotor groove.