Aircraft engine electrically powered boundary layer bleed system
CA 2046765 A1 · Owner: Coffinberry, George A. · Inventors: Coffinberry, George A.
Overview
Its claims, description and drawings are in the Canadian Patents Database.
Open the CIPO recordAbstract From the Canadian patent
An aircraft gas turbine engine is provided with an electrically powered boundary layer air bleed apparatus for bleeding boundary layer air off the nacelle and the wing or another part of the aircraft outer skin in order to reduce boundary layer or surface drag and using the boundary layer air as a source of compressed air and cooling air for the aircraft's environmental control system (ECS). A more particular embodiment of the invention provides means for ducting a portion of the boundary layer air to be further used to produce thrust and reduce base pressure drag in low pressure regions of the aircraft and engine.
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 July 11, 1991. No grant is recorded for it in Canada; had it been granted, its 20-year term would have ended July 11, 2011.
- A certificate of supplementary protection adds at most two years for a drug, so even that would have ended by July 11, 2013.
- 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.