Swing pivot thrust reverser

Details Swing pivot thrust reverser Swing pivot thrust reverser

1999-09-17

2001-07-17

Barefoot, Galen L. (Department: 3644)

Aeronautics and astronautics

Retarding and restraining devices

Friction brakes

C239S265290, C239S265370, C060S226200, C060S230000

Reexamination Certificate

active

06260801

ABSTRACT:

BACKGROUND OF THE INVENTION
The present invention relates generally to aircraft gas turbine engines, and, more specifically, to thrust reversers therefor.
In a turbofan engine, combustion gases are discharged through an exhaust nozzle for providing thrust to propel an aircraft in flight. Upon landing, a thrust reverser is deployed for reversing the direction of exhaust flow for providing a braking thrust force for reducing aircraft ground speed.
A common thrust reverser includes a pair of thrust reverser doors which surround the exhaust nozzle on diametrically opposite sides thereof when stowed or retracted. In this position, the trailing edges or lips of the doors surround the nozzle outlet and provide unobstructed flow therefrom.
The doors are deployed by rotation or pivoting thereof, with the aft lips moving radially inwardly to block the nozzle outlet, and leading edges or lips moved radially outwardly to uncover side outlets of the nozzle. The deployed doors have a clamshell configuration which redirects the exhaust flow radially outwardly through the sides of the nozzle and in an axially forward direction for providing reverse thrust.
In a typical configuration, the individual doors are mounted to the exhaust nozzle at single pivots. The doors may thusly be simply opened and closed by single axis pivoting using a suitable actuator.
However, the doors must be securely locked when stowed to prevent inadvertent deployment during flight. Door locking must be effected with a high level of reliability, which correspondingly substantially increases the complexity, weight, and expense of the thrust reverser. Increased complexity of the thrust reverser increases cost of initial procurement as well as maintenance thereof over its useful life. Increased complexity adds weight to the thrust reverser and correspondingly reduces overall performance of the aircraft.
The Federal Aviation Administration (FAA) has requirements for further increasing thrust reverser reliability. Increased reliability requirements cause a further increase in complexity of conventional single pivot thrust reversers, and further increase cost, weight, and maintenance requirements therefor.
Accordingly, it is desired to provide an improved thrust reverser having increased reliability without corresponding increase in complexity thereof.
BRIEF SUMMARY OF THE INVENTION
A hinge arm for a thrust reverser door may be mounted to an exhaust nozzle using an aft mount. The mount includes a frame for attachment to the nozzle. A swing link has a first pin pivotally joined to the frame, and a second pin for pivotally joining the hinge arm to the link to permit both swinging and pivoting of the hinge arm from the frame. The aft mount thusly permits the reverser doors to be reliably stowed around the nozzle.


REFERENCES:
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patent: 5310117 (1994-05-01), Fage et al.
patent: 5775639 (1998-07-01), Fage

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