Patent ID: 7758303
Filing Date: 2010-07-20
Classification: F01D,F02K,Y02T

Abstract:
1. A FLADE counter-rotating fan aircraft gas turbine engine comprising: axially spaced-apart forward and aft counter-rotatable fans circumferentially disposed about a centerline, at least one row of FLADE fan blades having radially outer airfoils disposed radially outwardly of and drivingly connected to one of the forward and aft counter-rotatable fans having radially inner airfoils, an annular shroud disposed between the radially inner and outer airfoils, the radially inner and outer airfoils extending radially inwardly and outwardly respectively from the annular shroud, a core engine and in flow receiving relationship with and located downstream of the radially inner airfoils, and a bypass duct surrounding the core engine and in flow receiving relationship with and located downstream of the radially outer airfoils, inner and outer chords extending between inner and outer leading and trailing edges of inner and outer airfoil cross-sections of the radially inner and outer airfoils respectively, inner and outer stagger angles between the inner and outer chords respectively at the annular shroud and the centerline, and the inner and outer stagger angles being different.