OPTIMAL LIFT DESIGNS FOR GAS TURBINE ENGINES

摘要

Turbine assemblies for gas turbine engines are provided. In one embodiment, a turbine assembly 75 includes a row 84 of circumferentially adjacent turbine rotor blades 74, each blade 74 in the row 84 of blades 74 including an airfoil 86 defining a chord (c) extending axially between opposite leading 96 and trailing edges 98 of the airfoil 86. The chords (c) in a mid-span region (s_mid) of each blade are shorter than the chords (c) in span regions adjacent to the blade root 92 and the blade tip (94). In another exemplary embodiment, a turbine assembly 75 includes a row of circumferentially adjacent turbine stator vanes 72, each vane 72 in the row of vanes 72 including an airfoil 100 defining a chord (c) extending axially between opposite leading and trailing edges of the airfoil 100. The chords (c) in a mid-span region of each vane 72 are shorter than the chords (c) in span regions adjacent to the vane root 102 and the vane tip 104. A turbine rotor blade for a gas turbine engine also is provided.