Aeronautics and astronautics – Retarding and restraining devices – Friction brakes
Reexamination Certificate
2000-10-11
2002-06-11
Poon, Peter M. (Department: 3643)
Aeronautics and astronautics
Retarding and restraining devices
Friction brakes
26
Reexamination Certificate
active
06402092
ABSTRACT:
BACKGROUND OF THE INVENTION
1. Field of the Invention
The present invention relates to a thrust reverser for a turbofan-type engine in which pivotable thrust reverser doors change the direction of the flow of gases passing through an annular duct to provide thrust reversing forces. More particularly, the present invention relates to such thrust reverser doors being mounted on centered pivots connecting to a downstream cowling portion.
2. Related Art
Turbofan-type turbojet engines are well known in the art and comprise an annular duct to the rear of the fan for the purpose of channeling the so-called cold, bypass flow. This annular duct is bounded on the inside by the engine cowling and on the outside by a fan cowling. The annular duct may channel both the bypass flow and the primary exhaust gas flow at a downstream portion, or may channel only the bypass flow. It is known to provide one or more pivotable thrust reversing doors in the annular duct to redirect the cold flow gas laterally outwardly through a lateral opening in the cowling.
FIGS. 1
,
2
and
3
illustrate a known pivoting door-type thrust reverser associated with the fan cowling of a turbofan-type turbojet engine. As illustrated in
FIG. 1
, the upstream portion of the fan cowling which defines the outer limits of the bypass flow duct and which is generally concentrically arranged about the turbojet engine (not shown) comprises an external cowling panel and an internal cowling panel interconnected by a frame
6
. The outer surface of the external cowling panel has an aerodynamic surface over which the air external to the engine passes during aircraft flight in the direction of the arrow
12
. The inner surface of the inner cowling panel defines the outer boundary of the bypass flow duct through which the bypass air flows in the direction of arrow
14
.
The fan cowling also comprises a trust reverser, illustrated generally in
FIG. 1
, and a downstream cowling portion
3
. The thrust reverser comprises a door
7
pivotally attached to the cowling such that it is movable between a closed, forward thrust position, illustrated in FIG.
1
. The door also has an open, reverse thrust position in which the upstream end (toward the left as viewed in
FIG. 1
) of the thrust reverser door
7
is moved outwardly from the cowling, while a downstream portion is moved inwardly into the bypass flow duct airstream so as to redirect at least a portion of the bypass flow through an opening in the fan cowling in a direction that has a reverse thrust component.
An actuator
8
for moving the door
7
between its forward thrust and reverse thrust positions may comprise a hydraulic cylinder mounted to the frame
6
, and have an extendible and retractable piston rod connected to the thrust reverser door
7
.
The thrust reverser door
7
has an outer door panel
9
and an inner door panel
11
joined together by an internal structure. The upstream end of the door
7
may have a deflector
13
to maximize the efficiency of the thrust reverser when the door
7
is in the reverse thrust position. When the door is in the forward thrust position, as illustrated in
FIG. 1
, the outer door panel
9
is substantially flush with the external surfaces of the upstream panel and the downstream cowling portion
3
.
As illustrated in
FIG. 2
, a plurality of thrust reverser doors
7
may be incorporated into the fan cowling, such doors being circumferentially spaced around the periphery of the fan cowling. A beam cowling portion
18
of the fan cowling extends from an upstream cowling portion
4
to the downstream cowling portion
3
. The beam cowling portion provides structural rigidity to the fan cowling and provides pivot mounting points for attaching the doors
7
to the fan cowling. French Patents 1,482,538 and 2,030,034 illustrate typical, known thrust reversers. U.S. Pat. No. 3,605,411 discloses a pivoting door-type thrust reverser in which the deflector mounted on the upstream or forward end of the thrust reverser door is movable to an extended position when the door is in the reverse thrust position.
Typically, the doors are arranged about pivots comprising a fixed structure extending from the cowling along the longitudinal sides of the door side walls. In one embodiment, the doors pivot about cantilevered longitudinal beams extending from the cowling. The described known pivot structures incur major drawbacks because the doors are not rigidly articulated due to the substantial forces exerted on the cantilevered longitudinal beams. Moreover, the known pivot structures add weight to the thrust reverser.
Most door-type thrust reversers have several locking systems to keep the doors locked in the forward thrust position. The primary lock is often situated between the frame of the cowling adjacent to the front side of the reverse thrust opening and located along the longitudinal axis of the thrust reverser door and at the upstream edge of the thrust reverser door. When the thrust reverser door is constrained by a central primary lock located along the longitudinal axis of the door, additional structure is required to reinforce the cowling frame. This configuration may lead to door deformations, in particular along the door corners as a result of flow-exerted pressure which in turn decreases the aerodynamic efficiency of the thrust reverser in a forward position.
SUMMARY OF THE INVENTION
A thrust reverser is disclosed for a turbojet engine having a cowling forming an outer boundary of a gas flow duct through which gases flow from a forward cowling portion to a rear cowling portion. The cowling has at least one reverse thrust opening between the forward cowling portion and the rear cowling portion communicating with the gas flow duct. Two cowling beam portions are located between the forward cowling portion and the rear cowling portion, and subtending the reverse thrust opening. A support fitting is connected to the rear cowling portion at the edge adjacent to the reverse thrust opening and to the two beam portions.
A thrust reverser door is pivotally attached to two door pivots which are supported by the support fitting, mounted parallel to a longitudinal axis of the cowling and spaced from opposite lateral sides of the thrust reverser door. The thrust reverser door is articulated on the two pivots so as to move between a forward thrust position wherein the thrust reverser door covers the at least one reverser thrust opening, and a reverse thrust position wherein the at least one reverse thrust opening is uncovered and the thrust reverser door directs at least a portion of the gases flowing through the duct through the one reverse thrust opening.
Further, a locking system is disclosed for an aircraft jet engine thrust reverser door that is located along the side of the thrust reverser door and adjacent to the beam cowling portion. The locking system is arranged to lock with the beam portion such that the locking system locks thrust reverser door in a forward position. By locating the locking system along the side of the thrust reverser door adjacent to the beam portion, the drawbacks of the known locking systems are obviated.
An object of the present invention is to avoid substantial loads acting on the cowling beam portions during a reverse thrust position by eliminating supporting pivots on cantilevered longitudinal beams and providing a locking system along the side of the thrust reverser door adjacent to the cowling beam portion. Further, the overall weight of the thrust reverser system is reduced compared to known systems.
REFERENCES:
patent: 3605411 (1971-09-01), Maison et al.
patent: 5120004 (1992-06-01), Matthias
patent: 5548954 (1996-08-01), de Cambray et al.
patent: 5930991 (1999-08-01), Fournier et al.
patent: 6094908 (2000-08-01), Baudu et al.
patent: 0 846 854 (1998-06-01), None
patent: 1482538 (1967-05-01), None
patent: 2030034 (1970-10-01), None
patent: 2769953 (1997-10-01), None
patent: 2769953 (1999-04-01), None
Jean Michel Christian Marie
Vicogne Laurent Marcel
Collins Timothy D.
Hispano Suiza Aerostructures
Poon Peter M.
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