Patent Leaderboard
USPTO Patent Rankings Data through Dec 31, 2025
Home › Adjustable two dimensional nozzle for aircraft jet engines

Adjustable two dimensional nozzle for aircraft jet engines

US Patent 4778109 · Granted Oct 18, 1988

Assignee

Inventors

View full patent text on Google Patents →

More Patents by These Inventors

Cooling system for a turbomachine speed reducer2001
Axisymmetric, directable and adjustable turbojet-engine exhaust nozzle2001
Turbojet engine thrust reverser and exhaust nozzle assembly2001
System for the admission of air into a working section of a gas turbine engine2000
Variable geometry turbojet engine exhaust nozzle1999
Turbojet equipped with a deicing system on the intake case1997
Gas turbine engine rotor blading sealing device1997
Supersonic nozzle for a turbojet engine1996
Supersonic nozzle, in particular for a turbojet engine1996
Nozzle for a jet engine containing an adjustable convergent-divergent portion1996
Inter-blade platform for a bladed disc of a turbomachine rotor1995
Integral composite gas turbine afterburner structure1994