Turbojet engine comprising an afterburner duct cooled by a variable-throughput ventilation stream

An afterbody for a turbojet engine is disclosed. The afterbody includes an afterburner casing, a thermal protection liner, and a diaphragm-forming assembly interposed between the liner and the casing. The diaphragm-forming assembly defines a flow area which is traversed by a ventilation stream. The...

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Bibliographische Detailangaben
Hauptverfasser:	BUNEL JACQUES MARCEL ARTHUR, CORTES THIERRY ANDRE EMMANUEL, VAGNER FABIENNE, PAGE ALAIN PIERRE
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COMBUSTION ENGINES ENGINE PLANTS IN GENERAL GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE WEAPONS
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Beschreibung
Zusammenfassung:	An afterbody for a turbojet engine is disclosed. The afterbody includes an afterburner casing, a thermal protection liner, and a diaphragm-forming assembly interposed between the liner and the casing. The diaphragm-forming assembly defines a flow area which is traversed by a ventilation stream. The diaphragm-forming assembly includes two annular plates overlapping one another, each being perforated with a plurality of apertures and being mounted on the liner and the casing respectively. The apertures jointly define the flow area of the assembly. Furthermore, the assembly is designed such that the expansion of the liner causes an angular displacement of the plate with respect to the plate, leading to an increase in the size of the flow area.