COMPOSITE BLADE WITH UNI-TAPE AIRFOIL SPARS

摘要

A gas turbine engine composite blade (10) includes an airfoil (12) having pressure and suction sides (41, 43) extending outwardly in a spanwise direction (S) from a blade root (20) along a span (S) to a blade tip (47). A core section (50) of the blade (10) including composite quasi-isotropic plies (52) extends spanwise outwardly through the blade (10). One or more spars (54, 56) including a stack (62) of uni-tape plies (63) having predominately a 0 degree fiber orientation with respect to the span (S) and extending spanwise outwardly through the root (20) and a portion (53) of the airfoil (12) towards the tip (47). Spars may include pressure and suction side spars (54, 56) sandwiching a chordwise extending portion (58) of the core section (50) in the airfoil (12) and which be located near or along the pressure and suction sides (41, 43) respectively. Chordwise extending portion (58) may be centered about a maximum thickness location (61) of the airfoil (12). Spars (54, 56) may have height (H), width (W), and thickness (T) that avoids flexural airfoil modes.