Compressor with offset diffuser for integral bleed

A compressor system is provided with an impeller disposed to rotate in a compressor chamber. A diffuser extends around the impeller to collect fluid leaving the impeller. Main flow is discharged from the diffuser through an exit providing an opening that extends circumferentially around the compress...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	Hoover, Robert, Sangston, Keith, Zonneveld, Paul, Ockenfels, Greg
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT PUMPS PARACHUTES PERFORMING OPERATIONS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A compressor system is provided with an impeller disposed to rotate in a compressor chamber. A diffuser extends around the impeller to collect fluid leaving the impeller. Main flow is discharged from the diffuser through an exit providing an opening that extends circumferentially around the compressor. A bleed annulus extends around the compressor and has a consistent cross-sectional area. A bleed port that opens the diffuser to the bleed annulus and that is configured to divert a bleed flow of the fluid from the main flow before discharge through the exit. The bleed port has a circumference around the compressor and a flow size that varies around the circumference. Variation in the flow size of the bleed port maintains a uniform flow distribution around the exit.