Patent ID: 9004850
Filing Date: 2015-04-14
Classification: F01D,F02C,F04D,F05D,Y02T

Abstract:
1. A compressor for a gas turbine engine, the compressor comprising: an annular inlet duct having an annular hub side wall and an annular shroud side wall extending around the hub side wall spaced apart therefrom; at least one rotor having an array of blades mounted on a rotatable shaft, the blades extending across a flow path in fluid communication and in alignment with the inlet duct; and a plurality of circumferentially spaced apart inlet guide vanes extending across the inlet duct from the hub side wall to the shroud side wall, each vane being pivotable about a pivot axis thereof, each vane defining an airfoil portion with opposed leading and trailing edges, the airfoil portion being twisted such that at each location of the airfoil portion along the pivot axis, an angle is defined between a respective chord extending between the leading and trailing edges and a same reference plane containing the pivot axis and extending radially with respect to the compressor, the angle varying from a minimum value near the hub side wall to a maximum value near the shroud side wall, the angle being measured along a direction of rotation of the rotor.