Turbojet engine thrust reverser and exhaust nozzle assembly

Details Turbojet engine thrust reverser and exhaust nozzle assembly Turbojet engine thrust reverser and exhaust nozzle assembly

2000-02-03

2001-02-13

Casaregola, Louis J. (Department: 3746)

Power plants

Reaction motor

Interrelated reaction motors

C239S265370

Reexamination Certificate

active

06185926

ABSTRACT:

BACKGROUND OF THE INVENTION
1. Field of the Invention
The present invention relates to a thrust-reversing rear exhaust structure of a turbojet engine, especially a twin-structure, variable-cycle bypass engine to propel a civilian supersonic airplane.
2. Description of the Related Art
In gas-jet exhaust assemblies as that of the present invention, a primary nozzle of variable cross-section is fitted with several flaps and situated downstream of a primary duct. A primary gas flow is exhausted from the primary nozzle during operation of the engine. A secondary nozzle of variable cross-section is also fitted with several flaps and situated downstream of a secondary duct enclosing the primary duct. The secondary duct extends rearward beyond the exhaust orifice of the primary duct. A secondary gas flow is exhausted from the secondary nozzle during operation of the engine.
A fairing encloses the secondary duct. The fairing is fitted with a throat, the so-called pickup throat, downstream of the exhaust orifice of the secondary nozzle. The throat is followed by a diverging portion.
A thrust reverser is provided comprising two identical eyelids which are pivotable on the fairing on either side of an axial plane of symmetry. The eyelids are able to assume either an active position, namely thrust-reversal, wherein they transversely project into the gas jet downstream of the fairing in order to deflect the gas jet forwardly, or an inactive position, namely forward-thrust, wherein they are situated in the extension of the fairing.
The assemblies also include means for driving the flaps of the primary and secondary nozzles and means for driving the eyelids.
Such an exhaust assembly uses the thrust-reverser eyelids in a manner known per se and which is utilized in the civilian Concorde plane. The eyelids are each pivotably mounted about a transverse axis near an axial plane of symmetry to allow control of the engine's exhaust cross-section as a function of flight modes. The width of the slit separating the upstream end of each eyelid from the downstream end of the fairing is a function of the pivot angle of the eyelids, the angle varying with the flight modes. An air flow issuing from the end of the fairing enters this slit and mixes with the gas flows.
SUMMARY OF THE INVENTION
The objective of the present invention is to create a novel eyelid kinematics which allows optimizing operation in supersonic cruise and other flight modes.
The objective of the invention is attained by an exhaust assembly in which each of two eyelids are mounted to the fairing by two lateral linkrods which are freely pivotable relative to the fairing about a transverse axis situated near the axial plane of symmetry. The eyelids are retained by at least one inner actuator anchored on the fairing and connected to a point on the respective eyelid relatively near the axial plane of symmetry. Each linkrod is retained by at least one outer actuator anchored on the fairing and connected to a point on the respective eyelid relatively further away from the axial plane of symmetry. The outer and inner actuators comprise a driving mechanism for the two eyelids.
Advantageously, actuating the inner actuators allows one to attain the required configurations for a forward-thrust mode and actuating the outer actuators allows one to attain the required configurations for a thrust-reversal mode.
When operating in the forward-thrust mode, the length of the external linear actuators is held substantially constant so as to act as additional linkrods. In such case, the eyelids have only one degree of freedom.
Preferably, each eyelid is retained by two synchronized inner actuators and by two synchronized outer actuators which are arranged on each side of an axial plane of symmetry of the respective eyelid.
The fairing preferably subtends a surface of revolution around a longitudinal axis of the primary duct.
In another feature of the invention, the primary nozzle comprises a plurality of controlled hot flaps alternating with a plurality of follower hot-flaps and the secondary nozzle comprises a plurality of driven cold flaps alternating with a plurality of follower cold-flaps.
A drive system for the hot and cold flaps comprises an axially displaceable drive ring situated around the cold flaps, a plurality of levers and a plurality of linkrods. The levers each have a first end, a second end and a middle portion. The first end hinges on the control ring and the middle portion hinges on the driven cold flaps. The linkrods connect the controlled hot flaps to the second ends of the levers.


REFERENCES:
patent: 2735264 (1956-02-01), Jewett
patent: 3734411 (1973-05-01), Wolf et al.
patent: 3856239 (1974-12-01), Leibach
patent: 4052007 (1977-10-01), Willard
patent: 4129269 (1978-12-01), Fage
patent: 4392615 (1983-07-01), Madden
patent: 4641782 (1987-02-01), Woodward
patent: 5050803 (1991-09-01), Wakeman et al.
patent: 5097661 (1992-03-01), Lain et al.
patent: 5794433 (1998-08-01), Peters et al.
patent: 2602274 (1988-02-01), None

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