# US 12,110,809 B1 · Turbine blade and assembly with dovetail arrangement for enlarged rotor groove > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,110,809 B1 - Document ID: US12110809B1 - Status: Granted - Kind: B1 - Application number: 18/295,408 - Filed: 2023-04-04 - Published: 2024-10-10 - Granted: 2024-10-08 - Earliest claimed: 2023-04-04 - Assignees: GE Infrastructure Technology LLC - Applicants: General Electric Company - Inventors: Federico Cervetto; Salvador Mata López; Steven Sebastian Burdgick - Web page: https://patentgrep.com/patent/US12110809B1 ## CPC - F01D 5/303: {in a circumferential slot} - F01D 5/3038: {the slot having inwardly directed abutment faces on both sides} - F01D 5/32: Locking, e.g. by final locking blades or keys - F01D 5/005: {Repairing methods or devices} - F01D 5/3092: {Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers (F01D5/288 takes precedence)} - F05D 2220/30: in turbines - F05D 2260/31: Retaining bolts or nuts - F05D 2260/36: by a form fit connection, e.g. by interlocking - F05D 2300/12: Light metals - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract 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. At least one 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 positioning leg(s) engage one of a radially outward facing surface of the rotor groove and a planar plate shim between the positioning leg(s) and the radially outward facing surface of the rotor groove. ## Claims ### Claim 1 A turbine blade assembly for a rotor groove defined in a rotor having an axis, the turbine blade assembly comprising: a turbine blade including an airfoil and a dovetail coupled to the airfoil, the dovetail including a mounting arm and an end surface facing radially inward relative to the axis; and an extension insert including a first end configured to contact the end surface of the dovetail and a second end, the second end including at least one positioning leg extending radially inward relative to the axis, wherein the dovetail and the extension insert are configured to be positioned in the rotor groove to mount the turbine blade to the rotor, and wherein the at least one positioning leg includes a plurality of positioning legs extending radially inward relative to the axis, wherein at least two of the plurality of positioning legs have different lengths. ### Claim 2 (depends on 1) The turbine blade assembly of claim 1, wherein the mounting arm engages a radially inward facing rotor hook of the rotor groove and the least one positioning leg engages one of a radially outward facing surface of the rotor groove and a shim plate between the at least one positioning leg and the radially outward facing surface of the rotor groove. ### Claim 3 (depends on 1) The turbine blade assembly of claim 1, wherein the extension insert has a radial extent larger than 4 millimeters. ### Claim 4 (depends on 3) The turbine blade assembly of claim 3, further comprising at least one shim plate between the at least one positioning leg and the radially outward facing surface of the rotor groove, the at least one shim plate having a radial extent of no greater than 1.5 millimeters. ### Claim 5 (depends on 1) The turbine blade assembly of claim 1, further comprising a fixation element locking a position of the extension insert relative to the dovetail of the turbine blade. ### Claim 6 (depends on 5) The turbine blade assembly of claim 5, wherein the fixation element includes a male-female coupler. ### Claim 7 (depends on 6) The turbine blade assembly of claim 6, wherein a female portion of the male-female coupler is defined in the end surface of the dovetail, and a male portion of the male-female coupler extends from the first end of the extension insert and is configured to seat within the female portion in the end surface to lock a position of the extension insert relative to the dovetail of the turbine blade. ### Claim 8 (depends on 5) The turbine blade assembly of claim 5, wherein the fixation element includes a fastener coupling the end surface of the dovetail and the first end of the extension insert together. ### Claim 9 (depends on 1) The turbine blade assembly of claim 1, wherein the extension insert includes a lighter material than a material of the airfoil and the dovetail. ### Claim 10 (depends on 1) A turbine system comprising a turbine including at least one turbine blade assembly of claim 1. ### Claim 11 (depends on 1) The turbine blade assembly of claim 1, further comprising a shim plate positioned between the at least one positioning leg and a radially outward facing surface of the rotor groove. ### Claim 12 A turbine blade for a rotor groove defined in a rotor having an axis, comprising: an airfoil; and a dovetail coupled to the airfoil, the dovetail having a mounting arm and a single positioning leg extending radially inward relative to the axis from a radially inward facing end surface of the dovetail, wherein a first radial distance between the mounting arm and a radially inner end of the single positioning leg matches a second radial distance between a radially inward facing rotor hook and a radially outward facing surface of the rotor groove. ### Claim 13 (depends on 12) A turbine system comprising a turbine including at least one turbine blade of claim 12.