DEFRGBSE0194957EUROPEAN PATENT APPLICATIONA319870603EP866300321986030671027019850311US1987060319872319860917198638 6F 01D 11/08 A 6F 01D 05:20 BenCompressor blade tip sealfrSystème de réduction des pertes des extrémités des aubes tournants auprès des compresseursdeEinrichtung um die Blattspitzenverluste bei Kompressoren zu vermindernUNITED TECHNOLOGIES CORPORATIONHarter, FranzDEFRGBSE19870603198723

The trench inner wall surrounding the tips (28) of axial flow fan/compressor blades (26) in a turbine type power plant is angularly disposed relative to the gas path wall (20) to allow deeper penetration into the trench and minimize leakage around the tips (28). Gap closure between the inner wall (37) of the trench and tip (28) is contemplated by the contour of the blade/trench.