ROCKET MOTOR COMBUSTION CHAMBER HAVING VARIABLE-COMPOSITION FINS

A rocket engine combustion chamber (1) extending along a longitudinal axis A may have a longitudinal envelope, the longitudinal envelope having a longitudinal inner wall (10) made of a first alloy, which is a copper alloy, and that is extended over its radially outer face (15) by a plurality of fins...

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Bibliographische Detailangaben
1. Verfasser:	GUICHARD, Didier
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING COMBINED OPERATIONS COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MACHINE TOOLS MECHANICAL ENGINEERING METAL-WORKING NOT OTHERWISE PROVIDED FOR OTHER WORKING OF METAL PERFORMING OPERATIONS TRANSPORTING UNIVERSAL MACHINE TOOLS WEAPONS
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Beschreibung
Zusammenfassung:	A rocket engine combustion chamber (1) extending along a longitudinal axis A may have a longitudinal envelope, the longitudinal envelope having a longitudinal inner wall (10) made of a first alloy, which is a copper alloy, and that is extended over its radially outer face (15) by a plurality of fins (20) extending radially outwards, each of the fins presenting a proximal portion (22), a middle portion (25), and a distal portion (28), and having an outer shell (30) surrounding the inner wall (10) and the fins (20), the shell (30) being made of a third alloy distinct from the first alloy. The proximal portion (22) is made of the first alloy, and the distal portion (28) is made of a second alloy that is an alloy distinct from the first alloy.