Patent ID: 8439626
Filing Date: 2013-05-14
Classification: F01D,Y02T

Abstract:
1. An assembly of airfoils in a compressor of a turbine engine, the assembly comprising at least three axially stacked rows of airfoils: a middle airfoil row, a first upstream airfoil row, and a first downstream airfoil row; wherein: further comprising a second upstream airfoil row, which borders the first upstream airfoil row and comprises the second row of airfoils in the upstream direction from the middle airfoil row; and a third upstream airfoil row, which borders the second upstream airfoil row and comprises the third row of airfoils in the upstream direction from the middle airfoil row; wherein the third upstream airfoil row, the first upstream airfoil row, and the first downstream airfoil row have substantially the same number of similarly shaped airfoils; wherein the third upstream airfoil row, the first upstream airfoil row, and the first downstream airfoil row each comprise a row of rotor blades, which rotate at substantially the same speed during operation; wherein the second upstream airfoil row comprises a row of stator blades, which remain substantially stationary during operation; and wherein at least 90% of the airfoils of the third upstream airfoil row and at least 90% of the airfoils of the first upstream airfoil row comprise a clocking relationship of between 25% and 75% pitch.