United States Patent: Fournier Et Al
United States Patent: Fournier Et Al
United States Patent: Fournier Et Al
Fournier et al.
US 6,516,606 B2
Feb. 11,2003
4,585,189 A
4/1986
5,369,954 A
* 12/1994
5,941,061 A
FR
(*)
* cited by examiner
Notice:
86 09838
1/1988
(57)
(30)
(51)
(52)
239/265 .11
(58)
244/54; 239/265.11
(56)
ABSTRACT
References Cited
* 10/1967
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axis more or less coincident With the axis of the said engine.
piece.
afterbody.
In knoWn afterbodies of this type, the CNA (common
noZZle assembly) is either ?xed, via radial arms, to a primary
noZZle, itself secured to the turbine housing, or ?xed to the
15
hinge.
lengthWays bulk;
45
able advantage.
When the thrust reverser acts only on the cold ?oW, there
When the thrust reverser acts both on the cold How and on
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10
mixed hot and cold ?oWs duct interior surface 16. Thrust
reverser doors 17 are installed in the fairing 10a, b, to act on
the cold ?oW.
reverser fairing are each formed of tWo halves, 9a, 9b and
10a, 10b, respectively, but the common noZZle or CNA 6 is
made as a single part. The tWo half-coWlings 9a, 9b and the
25
prior art;
FIG. 2 is a vieW similar to that of FIG. 1, modi?ed by the
incorporation of a ?rst embodiment of the present invention
35
5.
DETAILED DESCRIPTION
15
55
single piece.
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5
Which are mounted so as to be hinged by means of hinges to
and tWo series of hinges 36a, 36b are aligned along these
15
?oW only.
gases originating respectively from the fan duct and from the
aeroengine combustion chamber, the said noZZle having a
45
plane.
55
both a duct for cold gases and a duct for mixed hot and cold
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gases.
10