Gas turbine engine exhaust mixer

A gas turbine engine exhaust mixer has a plurality of circumferentially distributed alternating inner and outer lobes (42, 44). The outer lobes (44) protrude into the annular bypass passage (24) of the engine, whereas the inner lobes (42) protrude into the main gas path passage (26) of the engine. T...

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Bibliographische Detailangaben
1. Verfasser:	CUNNINGHAM, MARK HUZZARD
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine exhaust mixer has a plurality of circumferentially distributed alternating inner and outer lobes (42, 44). The outer lobes (44) protrude into the annular bypass passage (24) of the engine, whereas the inner lobes (42) protrude into the main gas path passage (26) of the engine. The inner and outer lobes (42, 44) respectively define alternating troughs (46) and crest (48) with radial interconnecting walls (50) therebetween. The mixer has a jagged trailing edge including a plurality of tabs (50) extending from each radial wall (50) between the troughs (46) and the crests (48).