Thrust reverser with turning vanes capable of being superposed

Details Thrust reverser with turning vanes capable of being superposed Thrust reverser with turning vanes capable of being superposed

2000-07-11

2001-07-10

Kim, Ted (Department: 3746)

Power plants

Reaction motor

Interrelated reaction motors

C060S230000, C244S11000H, C239S265290, C239S265310

Reexamination Certificate

active

06256980

ABSTRACT:

BACKGROUND OF THE INVENTION
1. Field of the Invention
The present invention relates to a thrust reverser for a bypass turbojet-engine, and more particularly, a thrust reverser having rotatable pivoting flaps closing an annular gas flow duct and stationary baffle portions radially offset with movable baffle portions redirecting a gas flow.
2. Related Art
Turbofan-type turbojet engines typically comprise a turbojet engine encased in a cowling wherein the engine drives a fan usually located at the front portion of the engine. The fan blades are enclosed in a fan cowling so that at least a portion of the is fan cowling is spaced from the engine cowling to define a generally annular gas flow duct. The annular gas flow duct channels the air impelled by the rotation of the fans.
As shown in
FIGS. 1 and 2
, it is known to position a thrust reverser so as to act against the gases flowing through the annular duct.
FIG. 1
illustrates a thrust reverser in a forward thrust position having a displaceable structure (
7
) with an inner surface spaced from an outer surface (
16
) of an engine cowling so as to form an annular gas flow duct (
17
). In the forward thrust position, a flap (
12
) covers a plurality of thrust reverser baffles (
20
) housed within the displaceable structure (
7
) by forming a portion of the inner surface of the displaceable structure (
7
).
FIG. 2
illustrates the thrust reverser in
FIG. 1
in a reverse thrust position wherein the displaceable structure (
7
) is axially displaced downstream to clear a passageway in the fan cowling for the flow deflected between the stationary structure (
6
) and an upstream edge of the displaceable structure (
7
). The flap (
12
) rotates so that one edge is adjacent with the outer surface (
16
) of the engine cowling to block the annular duct (
17
) and the flow is outwardly deflected from the passageway by the thrust reverser baffles (
20
).
European patent 0,109,219 A and U.S. Pat. No. 3,500,645 disclose typical designs using thrust reverser baffles. In these instances, baffles are rigidly connected to a non-translatable part of the fan cowling so that in a reverse thrust mode, a pivotable flap redirects the gas in the annular duct and the baffles effectively divert the exhausted gas through a passageway in the fan cowling. However, in such designs, the integration of thrust reverser baffles dictate the length of the displaceable structure which may increase the weight and require increased storage space in the jet engine cowling.
SUMMARY OF THE INVENTION
A thrust reverser is disclosed for a turbofan jet engine having a stationary structure defining an upstream part of a fan cowling and an axially displaceable, annular structure located downstream of the stationary structure. The displaceable structure forms a downstream external part of the fan cowling and a downstream part of a radial inner surface spaced from an outer surface of an engine cowling so as to form an annular gas flow duct. During a reverse thrust position, the displaceable structure is axially displaced to the rear to clear a passageway in the fan cowling for the flow deflected between the stationary structure and an upstream edge of the displaceable structure. A plurality of flaps form a portion of the inner surface of the displaceable structure during a forward thrust position, and in reverse thrust position, the flaps pivotably rotate about a stationary pivot so that their first edges are adjacent to the outer surface of the engine cowling effectively blocking the gas flow in the annular duct. A plurality of thrust reverser baffle portions are supported by the stationary structure and are covered by the flaps during the forward thrust position, and during the reverse thrust position, the thrust reverser baffle portions are within the passageway such that the thrust reverser baffle portions redirect the gas flow deflected by the flaps in a reverse thrust direction.
A turbofan thrust reverser according to the invention enables efficient forward and reverse thrust performances without incurring the drawbacks of the known designs. The plurality of thrust reverser baffle portions comprise two types: a stationary baffles portion and at least one movable baffle portion. The plurality of thrust reverser baffle portions are radially offset and substantially parallel in both the forward and reverse thrust positions. The stationary baffle portion is connected by a first end to the stationary structure and a second end is located downstream the stationary structure. The at least one movable baffle portion is movable with respect to the stationary baffle portion, and in the reverse thrust position, the at least one moveable baffle portion is displaced downstream so that the plurality of baffle portions are longitudinally juxtaposed.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1
is a partial, longitudinal, cross-sectional view illustrating a thrust reverser with a rigidly mounted flow deflecting baffle in the forward thrust position;
FIG. 2
is a partial, longitudinal, cross-sectional view illustrating a thrust reverser with a rigidly mounted flow deflecting baffle in the reverse thrust position;
FIG. 3
is a partial, longitudinal, cross-sectional view illustrating a thrust reverser with a plurality of flow deflecting baffles in the forward thrust position;
FIG. 4
is a partial, longitudinal, cross-sectional view illustrating a thrust reverser with a plurality of flow deflecting baffles in the reverse thrust position; and
FIG. 5
is a further partial, longitudinal cross-sectional view illustrating another thrust reverser with a plurality of flow deflecting baffles in the forward thrust position.


REFERENCES:
patent: 3248878 (1966-05-01), Clark et al.
patent: 3330505 (1967-07-01), Sedlmaier
patent: 3500645 (1970-03-01), Hom
patent: 3581841 (1971-06-01), Raynes
patent: 3655150 (1972-04-01), Haberkorn et al.
patent: 3981451 (1976-09-01), Prior et al.
patent: 0 109 219 A2 (1984-05-01), None
patent: 0 809 010 A1 (1997-11-01), None

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