COMPRESSION COWL FOR JET ENGINE EXHAUST

A compression inner core cowling 76 for a jet engine 10 can have a concave annular section 90 of the core cowling 76. The concave section 76 can begin within the expanse of an outer fan cowl 40 and extend aft of the fan cowl 40 toward the tail cone 94, defining an annular bypass section 80 between t...

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Bibliographische Detailangaben
1. Verfasser:	IGLEWSKI, Tomasz
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 compression inner core cowling 76 for a jet engine 10 can have a concave annular section 90 of the core cowling 76. The concave section 76 can begin within the expanse of an outer fan cowl 40 and extend aft of the fan cowl 40 toward the tail cone 94, defining an annular bypass section 80 between the fan cowling 40 and the core cowling 76. The concave geometry of the core cowling 76 reduces the strength of supersonic shock waves generated at the corners 140, 142 of the cowlings 40, 76 adjacent a supersonic airflow stream to increase overall efficiency of the engine 10.