System for the admission of air into a working section of a gas turbine engine
Patent 6082669 Issued on July 4, 2000. Estimated Expiration Date: 
May 4, 2018. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.
May 4, 2018. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.Patent References 3503211 3511055 3659424 Attenuation of a closing flap for a secondary air intake opening in an aircraft engine Resiliently coated metallic finger seals Gas turbine engines Thrust reverser for a long duct fan engine Reversible thrust ducted fan propulsion unit Scoop and inlet for auxiliary power units and method Patent #: 4418879 InventorsAssigneeApplicationNo. 071157 filed on 05/04/1998US Classes:244/53BAir intakesExaminersPrimary: Poon, Peter M.Assistant: Ducker, Charles R. Jr. Attorney, Agent or FirmForeign Patent References
International ClassB64B 001/24Foreign Application Priority Data1997-05-07 FRAbstractThe system (13) for admitting external air (12) into a working section (11) of a gas turbine engine through a jacket (10) of the working section is characterised by the combination of doors (15) sliding towards the front (ramps) and rotating doors (14). The ramps (15) are fitted with grooved lateral arms (30) in which run wheels mounted on the doors (14). When they reach an ascending part (33) of the grooves (31) after sufficient movement of the ramps (15) towards the front, they are caused to rise, which opens the doors (14). This system can be used on double flow gas turbine engines for supersonic aircraft. | |
