Method and leading edge replacement insert for repairing a turbine engine blade
US7841834B1 · kind B1 · utility
Assignee
Inventor
Key dates
| Filing date | Jan 26, 2007 |
| Grant date | Nov 30, 2010 |
| Priority date | — |
| Expiry date | Apr 19, 2029 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/303
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A replaceable leading edge insert for a rotor blade and a process for replacing a damaged leading edge portion of a blade on an integrally bladed rotor. The insert is a fibrous reinforced composite insert with a scarf joint to secure the insert to the blade. The insert includes an aft extending portion that engages with the opposed surface of the blade to hold the insert against radial displacement from the blade during operation. in one embodiment, a plurality of teeth extend from the lower portion of the insert and engage similar teeth on the rotor blade. When the insert is bonded to the rotor blade, the teeth add additional holding force against radial displacement should the bond weaken. The process includes removing a damaged portion from the blade leading edge such that a bonding surface remains for a standard shaped replaceable leading edge insert to fit on. The insert is bonded to the rotor blade to form a completed airfoil portion.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.