CPC F04D 27/0215 (2013.01) [F01D 11/08 (2013.01); F04D 29/526 (2013.01); F04D 29/685 (2013.01); F01D 11/22 (2013.01)] | 20 Claims |
1. A fan case assembly adapted for use with a gas turbine engine, the fan case assembly comprising
a case that extends circumferentially at least partway about a central axis of the fan case assembly to define an outer boundary of a gas path of the gas turbine engine, the case formed to define a plurality of internal channels and a plurality of grooves that extend axially at least partway between an axially forward end of the fan case and an axially aft end of the fan case, the plurality of grooves intersecting the internal channels,
a plurality of drums, each one of the plurality of drums disposed in a corresponding one of the plurality of grooves of the fan case and spaced circumferentially about the central axis, each drum of the plurality of drums shaped to include a passageway that extends through the corresponding drum, each drum of the plurality of drums configured to rotate about a respective drum axis between a closed position in which the passageway of the corresponding drum is positioned to block fluid communication between the passageway and at least one of the internal channels, and an open position in which the passageway of the corresponding drum is positioned to allow fluid communication between the gas path and the at least one internal channel through the passageway, and
a control unit configured to rotate the plurality of drums about the respective drum axis between the closed position and the open position in response to preselected operating conditions to minimize negative effects pressure and swirl distortions in the gas turbine engine to improve stall margin.
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