Abstract: A harvesting device particularly suited for harvesting artemia cysts. The invention in its various embodiments comprises a frame and a net coupled to the frame. The frame can include a front support frame, a rear support frame and a sledding frame. A net having a first end and a second end can be secured to the front and rear support frames respectively. In certain embodiments, the net has an aspect ratio or 4:1. One or more skids can be coupled to the frame. In certain embodiments, the skids are coupled to the sledding frame. In yet other embodiments, the skids are coupled to the sledding frame at substantially the joining of the front support frame and the sledding frame. The second end of the net can be attached to a conduit in communication with a harvest vessel by a coupling. The harvest vessel can include one or more dewatering stations in communication with the conduit.

Abstract: A device mounted to a vessel for harvesting a subsurface concentration of artemia cysts. In certain embodiments, the device includes a vertically adjustable front net support, a vertically adjustable rear net support and a net having a first end secured to the front net support and a second end secured to the rear net support. A conduit can be coupled to the second end of the net whereby the concentrated artemia cysts are drawn from the second end of net to a processing destination. In certain embodiments, the net has an aspect ratio of at least approximately 4:1. The processing destination could be the vessel or some other destination. In certain embodiments, the vessels are equipped with a dewatering station to which the concentrated cysts are directed for further processing. In some embodiments, the net is secured to a frame which is in turn coupled to the front net support. The front net support can include one or more arms.

Abstract: A turbofan gas turbine engine (10) comprises a compressor rotor (24) carrying a plurality of circumferentially spaced radially extending rotor blades (26) and a casing (28) surrounding the compressor rotor (24) and compressor rotor blades (26). A compressor rotor blade tip seal (48) comprises an annular member (30) secured to and arranged within the casing (28). The annular member (40) has a plurality of circumferentially spaced axially extending corrugations (32) and a plurality of radially spaced circumferentially extending corrugations (34). A lining (40) is secured to and arranged within the annular member (30). The lining (40) is spaced radially from the tips (27) of the compressor rotor blades (26) to form a clearance (29). An actuator (56) is provided to move the annular member (30) and lining (40) radially to control the size of the clearance (29).

Abstract: A turbofan gas turbine engine (10) comprises a compressor rotor (24) carrying a plurality of circumferentially spaced radially extending rotor blades (26) and a casing (28) surrounding the compressor rotor (24) and compressor rotor blades (26). A compressor rotor blade tip seal (48) comprises an annular member (30) secured to and arranged within the casing (28). The annular member (40) has a plurality of circumferentially spaced axially extending corrugations (32) and a plurality of radially spaced circumferentially extending corrugations (34). A lining (40) is secured to and arranged within the annular member (30). The lining (40) is spaced radially from the tips (27) of the compressor rotor blades (26) to form a clearance (29). An actuator (56) is provided to move the annular member (30) and lining (40) radially to control the size of the clearance (29).