A flight vehicle has an engine that includes air inlet, an isolator (or diffuser) downstream of the air inlet, and a combustor downstream of the isolator. The isolator includes a bulged region that has at least one dimension, perpendicular to the direction of the air flow from the inlet to the combustor, that is at a local maximum, larger than comparable isolator dimensions both upstream and downstream of the bulged region. The bulged region stabilizes shocks within the isolator, and facilitates flow mixing. The flow diversion of high energy flow around the outermost walls of the bulged section into the center of the flow at the aft end of the isolator, increases mixing of the flow, and results in a more consistent flow profile entering the combustor over a wide range of flight conditions (Mach, altitude, angle-of-attack, yaw) and throttle settings.
FLIGHT VEHICLE AIR BREATHING ENGINE WITH ISOLATOR HAVING BULGED SECTION AND METHOD OF OPERATING SUCH AN ENGINE
LUFTATMENDER FLUGGERÄTANTRIEB MIT ISOLATOR MIT GEWÖLBTEM ABSCHNITT UND VERFAHREN ZUM BETRIEB EINES SOLCHEN ANTRIEBS
MOTEUR AÉROBIE POUR VÉHICULE DE VOL AVEC ISOLATEUR À SECTION BOMBÉE ET PROCÉDÉ D'OPERATION D'UN TEL MOTEUR
2022-03-30
Patent
Electronic Resource
English
IPC: | F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F23R Erzeugen von Verbrennungsprodukten hohen Druckes oder hoher Geschwindigkeit, z.B. Gasturbinenbrennkammern , GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS |
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