Gas turbine engine compressor blade restoration
CA 2405335 C · Owner: General Electric Company · Inventors: Dingwell, William T.; Wilkins, Melvin H.; Corrigan, Sean J.
Overview
Its claims, description and drawings are in the Canadian Patents Database.
Open the CIPO recordAbstract From the Canadian patent
A method of repairing a gas turbine engine compressor blade airfoils includes machining away airfoil material (50) along leading and trailing edges and a radially outer tip of the airfoil to form leading edge trailing edge, and tip cut- backs (66, 68 69). Then beads of welding material (72) are welded onto the leading edge trailing edge, and tip cut-backs (62, 62 64). Then some of the weld material is machined away from the weld bead (70) to obtain desired finished dimensions of the leading and trailing edges and radially outer tip (66 68, 69). Blade material along only radially outermost portions (80) of the leading and trailing edges (LE TE) extending from the tip towards a base of the …
Read the whole patent
Listed from its CIPO record in Patent Yard's archive of Canadian patents past their term. Its claims, description and drawings are in the CIPO record and on Google Patents, and the Claude kit works from them.
Why it's free to use
- Filed September 26, 2002 and granted January 11, 2011. A Canadian patent filed from October 1, 1989 lasts 20 years from filing, so its term ended September 26, 2022.
- A certificate of supplementary protection adds at most two years for a drug, so even that would have ended by September 26, 2024.
- We check Canadian rights only. A patent in its family in another country could still be in force: check its family on Google Patents.
Timeline
Timeline From CIPO dates
Sources & verification
Official CIPO records
Everything on this page comes from the CIPO record linked above. Contains information licensed under the Open Government Licence – Canada.