Fluid sprinkling – spraying – and diffusing – Reaction motor discharge nozzle – With addition of secondary fluid upstream of outlet
Reexamination Certificate
1999-07-19
2001-01-30
Freay, Charles G. (Department: 3746)
Fluid sprinkling, spraying, and diffusing
Reaction motor discharge nozzle
With addition of secondary fluid upstream of outlet
C060S264000
Reexamination Certificate
active
06179225
ABSTRACT:
BACKGROUND OF THE INVENTION
1. Field of the Invention
The invention relates to an exhaust nozzle of variable cross-section mounted at the downstream end of a stationary, cross-sectionally circular outlet of a turbojet-engine hot-gas exhaust duct.
2. Discussion of Related Art
Some military aircraft equipped with turbojet engines must carry out missions in subsonic as well as supersonic flight. Such turbojet engines are typically fitted with an after-burner system and with either an axially symmetrical nozzle or substantially two-dimensional exhaust nozzle.
The nozzle must have a variable cross-section if used on afterburner-fitted gas-turbine engines.
In order to gain more thrust at normal full power and at full power with afterburning, a composite nozzle has been developed overtime with converging and diverging variable cross-sections. The kinematics and technology of these converging/diverging nozzles are complex and they are heavy.
In most cases the exhaust nozzle is restricted at its converging portion to allow comparatively simple engineering while achieving satisfactory results.
It is this kind of axially symmetric nozzle which is the object of the present invention.
BRIEF SUMMARY OF THE INVENTION
More specifically the invention relates to converging, axially symmetric nozzle for an aircraft turbojet engine, where this nozzle comprises a conical shell affixed to the end portion of the turbojet engine, an inner ring of so-called hot flaps mounted on the distal end of the conical shell, an external ring of so-called cold flaps mounted on the distal end of an annular assembly located between the conical shell and an external cowl, said outer ring of cold flaps extending downstream in the direction of the flow of the exhaust gases beyond the external cowl and the inner hot-flap ring. Further, the invention relates to first a control means supported on the conical shell to drive the hot flaps pivotally connected at their upstream ends to the conical shell, and second control means supported on the annular assembly to drive the cold flaps that are pivotally attached at their upstream ends to the annular assembly.
The objective of the invention is to reduce the infrared signature of this kind of nozzle by providing simple means to introduce fresh ambient or external air into the flow of exhaust gases for certain nozzle configurations in order to lower the flow and its temperature.
Each cold flap comprises an inner skin hingedly mounted on the annular assembly and which includes a plurality of inner orifices, and further each cold flap includes an outer skin radially spaced from the inner skin, wherein the two skins converge toward the trailing edge of the flap, and wherein the annular structure is axially displaceable when driven by a third control means between a first position whereat the outer skins are situated in alignment with the external cowl and a second position whereat the outer skins are located downstream of the external cowl and constitute a scoop for injecting external air into the flow of exhaust gases through the orifices of the inner skins in order to reduce the infrared signature of the exhausted gases.
Complementary orifices may be provided in the trailing edge of each cold flap.
The invention further includes the following improvements:
the first control means comprises a first axially displaceable control ring connected by linkrods to the hot flaps and driven by a plurality of first linear actuators anchored on the conical shell;
the second control means comprise a second axially displacement ring driven by a plurality of two linear actuators anchored on the annular structure;
the second control ring comprises a plurality of studs fitted with cam rollers rolling in follower apertures of the inner skins of the cold flaps;
the conical shell is connected at its upstream end to a cylindrical shell extending downstream and including a guide to axially guide the annular assembly, the third control means comprising a plurality of third linear actuators anchored on the upstream end of the cylindrical shell.
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Bouiller Philippe Pierre
Bourquin Pierre-Yves
Kettler Daniel
Ruis Jean-Pierre
Bacon & Thomas PLLC
Evora Robert Z.
Freay Charles G.
Societe Nationale d'Etude et de Construction de Moteurs d&a
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