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 (smid) 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.