Shrouded turbofan bleed duct

A bleed duct (42) is configured for bleeding fan air from the fan bypass duct (32) in a turbofan aircraft engine (10). The bleed duct (42) includes a tubular conduit (48) having an inlet (50) and outlet (52) at opposite ends. The conduit (48) is configured in flow area for recovering pressure from s...

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Bibliographische Detailangaben
1. Verfasser:	KRAFT ROBERT EUGENE,GIBBENS NELSON DIRK,HETICO ROLF ROBERT,GROLL WILLIAM CHARLES,BAILEY WILLIAM ANDREW,STOKER JAMES EDWARD
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OFGENERAL APPLICATION GAS-TURBINE PLANTS HEAT EXCHANGE IN GENERAL HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS,IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A bleed duct (42) is configured for bleeding fan air from the fan bypass duct (32) in a turbofan aircraft engine (10). The bleed duct (42) includes a tubular conduit (48) having an inlet (50) and outlet (52) at opposite ends. The conduit (48) is configured in flow area for recovering pressure from speeding fan air bled therethrough. A shroud (60,68,70,72,74) extends forwardly from the duct inlet (50) for suppressing dynamic pressure oscillations inside the conduit (48) without degrading the pressure recovery.