General Electric Company

William Charles Groll

William Andrew Bailey

Robert Eugene Kraft

Rolf R Hetico

Hyoun-woo Shin

Nelson Dirk Gibbens

James Edward Stoker

Rolf Robert Hetico

An apparatus and method for suppressing dynamic instability in a bleed duct of a gas turbine engine includes a fan bypass duct configured to permit a flow of air through the gas turbine engine. The fan bypass duct defines a fan duct surface, and the bleed duct has an inlet in fluid communication with the fan bypass duct and a flow control valve having an opened position and a closed position. A flow diverter is positioned on the fan duct surface proximate the inlet of the bleed duct and diverts the flow of air from the inlet when the flow control valve is closed, while permitting a portion of the flow of air to enter the inlet when the flow control valve is opened.

Apparatus and method for suppressing dynamic pressure instability in bleed duct

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.

Shrouded turbofan bleed duct

The present invention provides a system and method for collecting data from a Laser Doppler Anemometer of the type including a probe mounted to a controllable traversing system. Velocity and position data is collected from the probe while it is continuously in motion, and displayed in real time. If at any point the data is of unacceptable quality, the data collection process is stopped, the probe is moved to a last known good position, and the data collection process is restarted.

Data aquisition system and method for a laser doppler anemometer

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North Bend, OH, United States of America

William Charles Groll