Patent ID: 6935118
Filing Date: 2005-08-30
Classification: B23K,B64D,F02K,F05D,Y10T

Abstract:
1. An aircraft gas turbine engine exhaust nozzle basesheet comprising: a plurality of basesheet segments extending between longitudinally extending spaced apart basesheet leading and trailing edges, respectively, of the basesheet, right and left hand basesheet side edges, respectively, extending longitudinally between the basesheet leading and trailing edges, each basesheet segment having a panel body defined between a pair of segment side edges longitudinally extending between segment leading and trailing edges, respectively, stiffeners comprising leading and trailing edge ribs at the segment leading and trailing edges of aft and forward ones of the basesheet segments, respectively, extending widthwise across the panel body between the segment side edges, the leading and trailing edge ribs joined together only at intermediate sections of the stiffeners centered between left and right hand expansion sections, respectively, of the stiffener, forwardly extending side trailing edge flanges of the trailing edge ribs in the left and right hand expansion sections of the stiffeners connected substantially parallel to the panel bodies of the basesheet segments by a hem at the segment leading edges, forwardly extending side leading edge flanges of the leading edge ribs in the left and right hand expansion sections of the stiffeners connected substantially parallel to the panel bodies of the basesheet segments by jogs in the leading edge ribs at the segment leading edges, and the side leading edge flanges having rolled over tabs bent inwardly towards the panel bodies.