B - Operations – Transporting – 64 – C
Patent
B - Operations, Transporting
64
C
60/136
B64C 15/02 (2006.01) F02K 1/00 (2006.01)
Patent
CA 1242589
ABSTRACT OF DISCLOSURE VECTORABLE EXHAUST NOZZLE FOR GAS TURBINE ENGINES A vectorable exhaust nozzle 17 for a gas turbine engine comprises a fixed duct 21 and a cowl 22 pivotably attached to the duct 21 to facilitate rotation of the cowl 22 about a horizontal axis transverse to the exhaust stream issuing from the duct 21. The nozzle 17 further comprises a flap 23 pivotably attached to the lower downstream edge of the duct 21 for rotation about a second horizontal axis transverse to the exhaust stream and an actuation means 28 for rotating the cowl 22 and flap 23. The cowl 22 and flap 23 communicate via at least one link member 24. The actuation means 28 rotates the cowl 22 which, by way of the link members 24, rotates the flap 23 in the same direction. The nozzle 17 defined by the sidewalls 22a and the intercon- necting curved wall 22b of the cowl 22 and the down- stream edge of the flap 23, is thus vectored from a direction facing rearwards to a direction facing down- wards.
488502
Fetherstonhaugh & Co.
Rolls-Royce Plc
LandOfFree
Vectorable exhaust nozzle for gas turbine engines does not yet have a rating. At this time, there are no reviews or comments for this patent.
If you have personal experience with Vectorable exhaust nozzle for gas turbine engines, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Vectorable exhaust nozzle for gas turbine engines will most certainly appreciate the feedback.
Profile ID: LFCA-PAI-O-1178526