Abstract: The cantilevered stator vanes of the compressor section of the gas turbine engine are treated by including a rotating hub having a by-pass passage for removing the low momentum fluid from the main air stream adjacent to the tips of the stator vanes in the compressor and returning it back into the main air stream after having treated the air while avoiding penalties and excessive heating. A plurality of vanes are circumferentially spaced in the by-pass passage for removing vortices and streamlining the flow before injected the air back into the airstream. The vane passage hub treatment is fabricated in a single cast piece in one embodiment, in a three ring configuration in another embodiment and in a segmented ring configuration in still another embodiment.

Abstract: The cantilevered stator vanes of the compressor section of the gas turbine engine are treated by including a rotating hub having a by-pass passage for removing the low momentum fluid from the main air stream adjacent to the tips of the stator vanes in the compressor and returning it back into the main air stream after having treated the air while avoiding penalties and excessive heating. A plurality of vanes are circumferentially spaced in the by-pass passage for removing vortices and streamlining the flow before injected the air back into the airstream. The vane passage hub treatment is fabricated in a single cast piece in one embodiment, in a three ring configuration in another embodiment and in a segmented ring configuration in still another embodiment.

Abstract: A racquet string is provided that integrates a non-circular string substrate with a solid lubricant. The combination of lubrication with an elongated shape allows woven racquet strings to be easily displaced while striking a ball, yet able to rebound quickly to their originally strung positions. These features improve spin control, reduce racquet vibration, improve ball rebound consistency, and lengthen string life.

Abstract: To enhance stall margin without degrading engine performance the case of the fan of a fan-jet engine is treated by incorporating a passageway to remove flow from the main flow stream. The location and amount of the low momentum flow relative to the rotor being removed is critical. The flow is removed at a judicious location downstream of the leading edge of the rotor blade and returned at a judicious location upstream of the point of removal. The amount of removed flow must be no greater than 8% of the total flow in the fan rotor. Anti-swirl vanes in the passageway and discreetly sized inlet and outlet passages of the passageway return the flow to the main stream at an increased velocity. The intake is so designed that it selectively removes only the weak low momentum flow relative to the rotor and encourages the strong mainstream flow to remain in the main gas stream.

Abstract: The outer shroud of an axial flow compressor is treated to remove the low momentum flow adjacent the tips of the compressor blades in a judiciously located and sized passageway that removes the low momentum flow relative to the rotor blades at a location downstream of the blades' leading edge and returned at a location upstream of the point of removal. It being critical that no more than 12% of the total flow in the compressor rotor is removed for treatment. Anti-swirl vanes in the passageway serve to remove or reverse the swirl component from the removed low momentum flow. The intake is so designed that it selectively removes only the weak low momentum flow relative to the rotor and encourages the strong mainstream flow to remain in the main gas stream.