Turbine airfoil with integrated impingement and serpentine cooling circuit
CA 2548339 C · Owner: Lee, Ching-Pang · Inventors: Lee, Ching-Pang
Overview
Its claims, description and drawings are in the Canadian Patents Database.
Open the CIPO recordAbstract From the Canadian patent
An airfoil (18) for a gas turbine engine includes a generally radially- extending first cooling channel (40) disposed between pressure and suction sidewalls (20 22) adjacent the leading edge (24) of the airfoil (18) and a generally radially- extending second cooling channel (40B) disposed aft of the first cooling channel (40A). The second cooling channel (40B) is closed off at an outer end thereof and is disposed in fluid communication with a forward inlet (41) an inner end thereof. The first and second cooling channels (40A 40B) are separated by a partition (38A) having a plurality of impingement holes (44) therein. A generally axially extending end channel (43) is disposed radially …
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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 May 25, 2006 and granted July 7, 2015. A Canadian patent filed from October 1, 1989 lasts 20 years from filing, so its term ended May 25, 2026.
- Certificates of supplementary protection extend only drug patents, and it isn't classified as one.
- 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.