Aircraft engine starter integrated boundary bleed system
CA 2036822 A1 · Owner: General Electric Company · Inventors: Davison, Samuel H.
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 a compressed air supply system generally used for meeting customer or aircraft bleed air requirements. The compressed air supply system comprises an auxiliary compressor, a means for mechanically driving the system from a rotor of the gas turbine rotor, and a cycle varying means, such as a variable speed drive, for operating the auxiliary compressor cycle independently of the aircraft gas turbine engine compressor cycle. The preferred embodiment provides a means for bleeding boundary layer air off the nacelle or another part of the aircraft outer skin and using it as a source of air for the auxiliary compressor. one embodiment includes an air …
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 February 21, 1991. No grant is recorded for it in Canada; had it been granted, its 20-year term would have ended February 21, 2011.
- A certificate of supplementary protection adds at most two years for a drug, so even that would have ended by February 21, 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.