Aeronautics and astronautics – Retarding and restraining devices – Friction brakes
Reexamination Certificate
2003-02-17
2004-11-30
Poon, Peter M. (Department: 3643)
Aeronautics and astronautics
Retarding and restraining devices
Friction brakes
C060S226200, C239S265190
Reexamination Certificate
active
06824101
ABSTRACT:
FIELD OF THE INVENTION
The present invention relates generally to thrust reversers for jet engines and more particularly to apparatus and methods for mounting cascade support rings to thrust reversers.
BACKGROUND OF THE INVENTION
Thrust reversers are commonly used to reverse the direction of thrust generated by an aircraft jet engine so that the same may be used as a deceleration force for the aircraft. As shown in
FIGS. 1 through 5
, many existing thrust reversers
10
include a fixed structure
12
, a sleeve
14
that is translatable relative to the fixed structure
12
, and a plurality of cascades
16
each of which includes a plurality of vanes
18
. The fixed structure
12
of the thrust reverser
10
includes a torque box
20
, a hinge beam
22
, a latch beam
24
, and a cascade support ring
26
mounted to each cascade
16
.
In addition, the cascades
16
are commonly bolted to the thrust reverser
10
. As shown in
FIGS. 2 and 4
, nut and bolt assemblies
28
are used to attach the fore end portion
30
of each cascade
16
to the torque box
20
. Similarly, nut and bolt assemblies
32
are used to attach the aft end portion
34
of each cascade
16
to its corresponding cascade support ring
26
.
Referring to
FIG. 5
, the upper and lower end portions
36
and
38
of the cascade support rings
26
are, in turn, bolted to the respective hinge and latch beams
22
and
24
, thus forming relatively fixed joints
25
therebetween. More specifically, nut and bolt assemblies
40
are used to attach the end portions
36
and
38
of the cascade support rings
26
to fittings
42
, which are integral to the hinge and latch beams
22
,
24
.
A drill cage or jig is typically used to aid in accurate drilling of the torque box
20
and the cascade support rings
26
with the bolt holes, which are used for attachment of the cascades
16
to the torque box
20
and to the cascade support rings
26
. The corresponding bolt holes in the fore and aft end portions
30
and
34
of the cascades
16
are also precisely located within certain minimal tolerances to ensure a proper connection.
Although the bolted joints
25
used for mounting cascade support rings to the latch and hinge beams have worked well for their intended purpose, the inventor has recognized that it would be even more beneficial if such joints required less assembly time and tooling costs. Accordingly, a need exists in the art for a device and method for more efficiently attaching cascade support rings to latch and hinge beams.
SUMMARY OF THE INVENTION
In order to solve these and other needs in the art, the inventor here of has succeeded in designing an apparatus and method for mounting a cascade support ring to a thrust reverser. In one exemplary embodiment, the thrust reverser includes a hinge beam, a latch beam, and at least one cascade support ring having an upper end portion and a lower end portion. A first fitting disposed at the upper end portion of the cascade support ring. The first fitting includes an engagement portion slidably positioned within a first track defined by the hinge beam. A second fitting is disposed at the lower end portion of the cascade support ring. The second fitting includes an engagement portion slidably positioned within the second track.
In another preferred form, the present invention provides a method of mounting a cascade support ring to a thrust reverser for a jet engine of a mobile platform. In one embodiment, the method comprises: providing an upper end portion of the cascade support ring with a first fitting; providing a lower end portion of the cascade support ring with a second fitting; providing a hinge beam of the thrust reverser with a first track sized to slidably receive therein an engagement portion of the first fitting; providing a latch beam of the thrust reverser with a second track sized to slidably receive therein an engagement portion of the second fitting; and slidably positioning the engagement portions of the first and second fittings within the first and second tracks, respectively.
Further areas of applicability of the present invention will become apparent from the detailed description provided hereinafter. It should be understood that the detailed description and specific examples below, while indicating at least one preferred embodiment of the invention, are intended for purposes of illustration only and are not intended to limit the scope of the invention.
REFERENCES:
patent: 5778659 (1998-07-01), Duesler et al.
patent: 6584763 (2003-07-01), Lymons et al.
patent: 6592074 (2003-07-01), Dehu et al.
Lallement Michael K.
Sternberger Joe
Collins Timothy D
Harness & Dickey & Pierce P.L.C.
Poon Peter M.
The Boeing Company
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