Patent ID: 6375419
Filing Date: 2002-04-23
Classification: F01D,F04D,Y02T

Abstract:
A flow directing element for a gas turbine engine, the flow directing element being a compressor element having a cambered airfoil with a leading edge, a trailing edge, a chord extending from the leading edge to the trailing edge, a root, a tip, a span extending from the root to the tip and having a pre-established part span location intermediate the root and the tip that defines a juncture between a tip airfoil portion that extends spanwisely from the juncture to the tip and a root airfoil portion, distinct from the tip airfoil portion, that extends spanwisely from the juncture to the root, and a camber, the camber throughout the tip portion being greater than the camber throughout the root portion so that the airfoil turns fluid flowing through the compressor through a turning angle, the turning angle throughout the tip portion being greater than the turning angle throughout the root portion.