Shrouded turbofan bleed duct
AssigneeGeneral Electric Company
InventorsRobert Eugene Kraft, Nelson Dirk Gibbens, Rolf Robert Hetico, William Charles Groll, William Andrew Bailey, James Edward Stoker
Life of this patent
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Abstract
A bleed duct is configured for bleeding fan air from the fan bypass duct in a turbofan aircraft engine. The bleed duct includes a tubular conduit having an inlet and outlet at opposite ends. The conduit is configured in flow area for recovering pressure from speeding fan air bled therethrough. A shroud extends forwardly from the duct inlet for suppressing dynamic pressure oscillations inside the conduit without degrading the pressure recovery.
Claims35
A turbofan engine comprising:
- a fan powered by a core engine including a multistage compressor therein, and a fan bypass duct surrounding said core engine;
- a bleed system including a primary bleed circuit for bleeding pressurized air from said compressor joined in flow communication with a heat exchanger, and a secondary bleed circuit for bleeding fan air from said fan bypass duct joined in flow communication with said heat exchanger;
- and
- said secondary bleed circuit includes a bleed conduit having a duct inlet facing forwardly inside said bypass duct, and duct outlet joined by a valve to said heat exchanger, and an acoustic suppression shroud extending forwardly from said duct inlet inside said bypass duct with a side opening at said duct inlet for suppressing pressure oscillations inside said bleed conduit when said valve is closed.
A turbofan bleed duct for a turbofan engine having a fan bypass duct surrounding a core engine, said bleed duct comprising:
- a tubular conduit having an annular duct inlet at a forward end configured to face forwardly inside said bypass duct and an annular duct outlet at an opposite aft end, and configured in flow area therebetween for recovering pressure from speeding fan air bled therethrough;
- and
- an acoustic suppression shroud extending forwardly from said duct inlet with a side opening thereat to suppress dynamic pressure oscillations inside said conduit.
A turbofan bleed duct for a turbofan engine having a fan bypass duct surrounding a core engine, said bleed duct comprising:
- a tubular conduit having an annular duct inlet at a forward end configured to face forwardly inside said bypass duct and an annular duct outlet at an opposite aft end, and configured in flow area therebetween for recovering pressure from speeding fan air bled therethrough;
- and
- an acoustic suppression shroud extending forwardly from said duct inlet coaxially in line-of-sight alignment therewith to provide both a shroud inlet at the forward end of said shroud and a side opening at said duct inlet.
Dependencies are inferred from the claim text.