Abstract: A disclosed embodiment provides an acoustic panel having a composite laminate panel having a back sheet layer, a face sheet layer, and a core layer disposed therebetween. The core layer has one or more depressions at an interface between the core layer and the face sheet layer, with the face sheet having a generally uniform thickness across the composite laminate panel. A hole extends through the composite laminate panel at the depressions, and a bolt assembly extends through the hole such that it is countersunk.

Abstract: A vane includes a composite airfoil having a single dovetail root extending chordwise between or near leading and trailing edges of the airfoil. The root is connected to the airfoil and is slidably received in a dovetail slot in an inner vane mount. The dovetail slot has a triangular slot cross section and a flat slot bottom and flat slot pressure and suction side crush faces corresponding to pressure and suction sides of the airfoil. The root has a triangular root cross section, a flat root bottom, and flat dovetail root pressure and suction side crush faces. A biasing means urges the root bottom of the dovetail root away from the slot bottom and presses and preloads the dovetail root pressure and suction side crush faces against the slot pressure and suction side slot crush faces.

Abstract: A vane includes a composite airfoil having one or more pockets and one or more spars received therein respectively. The spars extending radially away from a bridge of a vane mount supporting airfoil. The spars may be integrally formed with the bridge. The spars may be adhesively bonded to the composite airfoil within the pockets. A passage may extend between an airfoil base and an airfoil tip. A gas turbine engine annular fan frame includes an annular row of the composite outlet guide vanes extending radially between and connecting radially inner and outer rings of the fan frame.

Abstract: A vane includes a composite airfoil having one or more outer pockets and one or more outer spars received therein respectively. The outer spars extending radially inwardly from an outer bridge of the outer vane mount outwardly supporting airfoil. The spars may be integrally formed with the bridge and adhesively bonded to the composite airfoil within the pockets with a passage extending between an airfoil base and an airfoil tip. A metallic leading edge tip may be disposed along the leading edge of the composite airfoil. A gas turbine engine annular fan frame incorporates the vanes in an annular row of composite outlet guide vanes extending radially between and connecting radially inner and outer rings of the fan frame.

Abstract: A vane includes a composite airfoil having chordwise spaced apart forward and aft dovetail feet at or near leading and trailing edges of the airfoil. Each foot includes a shank connecting a dovetail root to an airfoil base and each root is slidably received in a dovetail slot in an inner vane mount. The dovetail slot has a triangular slot cross section and a flat slot bottom and flat slot pressure and suction side crush faces corresponding to pressure and suction sides of the airfoil. The dovetail root having a triangular root cross section and a flat root bottom and flat dovetail root pressure and suction side crush faces. A biasing means urges the root bottom of the dovetail roots away from the slot bottom and presses and preloads the dovetail root pressure and suction side crush faces against the slot pressure and suction side slot crush faces.

Abstract: A disclosed embodiment provides an acoustic panel having a composite laminate panel having a back sheet layer, a face sheet layer, and a core layer disposed therebetween. The core layer has one or more depressions at an interface between the core layer and the face sheet layer, with the face sheet having a generally uniform thickness across the composite laminate panel. A hole extends through the composite laminate panel at the depressions, and a bolt assembly extends through the hole such that it is countersunk.

Abstract: A vane includes a composite airfoil having one or more outer pockets and one or more outer spars received therein respectively. The outer spars extending radially inwardly from an outer bridge of the outer vane mount outwardly supporting airfoil. The spars may be integrally formed with the bridge and adhesively bonded to the composite airfoil within the pockets with a passage extending between an airfoil base and an airfoil tip. A metallic leading edge tip may be disposed along the leading edge of the composite airfoil. A gas turbine engine annular fan frame incorporates the vanes in an annular row of composite outlet guide vanes extending radially between and connecting radially inner and outer rings of the fan frame.

Abstract: A vane includes a composite airfoil having one or more pockets and one or more spars received therein respectively. The spars extending radially away from a bridge of a vane mount supporting airfoil. The spars may be integrally formed with the bridge. The spars may be adhesively bonded to the composite airfoil within the pockets. A passage may extend between an airfoil base and an airfoil tip. A gas turbine engine annular fan frame includes an annular row of the composite outlet guide vanes extending radially between and connecting radially inner and outer rings of the fan frame.

Abstract: A vane includes a composite airfoil having a dovetail root extending chordwise between or near leading and trailing edges of the airfoil. The root is connected to the airfoil and is slidably received in a dovetail slot in an inner vane mount. The dovetail slot has a triangular slot cross section and a flat slot bottom and flat slot pressure and suction side crush faces corresponding to pressure and suction sides of the airfoil. The root has a triangular root cross section, a flat root bottom, and flat dovetail root pressure and suction side crush faces. A biasing means urges the root bottom of the dovetail root away from the slot bottom and presses and preloads the dovetail root pressure and suction side crush faces against the slot pressure and suction side slot crush faces.

Abstract: A vane includes a composite airfoil having chordwise spaced apart forward and aft dovetail feet at or near leading and trailing edges of the airfoil. Each foot includes a shank connecting a dovetail root to an airfoil base and each root is slidably received in a dovetail slot in an inner vane mount. The dovetail slot has a triangular slot cross section and a flat slot bottom and flat slot pressure and suction side crush faces corresponding to pressure and suction sides of the airfoil. The dovetail root having a triangular root cross section and a flat root bottom and flat dovetail root pressure and suction side crush faces. A biasing means urges the root bottom of the dovetail roots away from the slot bottom and presses and preloads the dovetail root pressure and suction side crush faces against the slot pressure and suction side slot crush faces.