Patent ID: 8182204
Filing Date: 2012-05-22
Classification: F01D,F02C,F04D

Abstract:
1. A gas turbine engine comprising an annular gas path duct having an inner duct wall and an outer duct wall, the gas path duct having: a plurality of struts extending radially between the inner duct wall and the outer duct wall, the plurality of struts having an aerodynamic shape; a plurality of airfoil vanes located circumferentially around the duct, the airfoil vanes extending radially between the inner duct wall and the outer duct wall, the airfoil vanes having leading edges disposed downstream of leading edges of the plurality of struts relative to a direction of gas flow through the gas turbine engine; a plurality of aerodynamic deflectors extending radially between the inner duct wall and the outer duct wall, the plurality of aerodynamic deflectors located circumferentially around the duct, a said aerodynamic deflector being circumferentially located between a said strut and an adjacent said vane; and wherein the leading edges of the plurality of struts define a first radially extending plane and the leading edges of the airfoil vanes define a second radially extending plane, and wherein leading edges of the plurality of aerodynamic deflectors are axially positioned between said first and second radially extending planes.