OPTIMAL LIFT DESIGNS FOR GAS TURBINE ENGINES

摘要

Turbine assemblies for gas turbine engines are provided. In one embodiment, aturbine assembly includes a row of circumferentially adjacent turbine rotorblades, eachblade in the row of blades including an airfoil defining a chord extendingaxially betweenopposite leading and trailing edges of the airfoil. The chords in a mid-spanregion of eachblade are shorter than the chords in span regions adjacent to the blade rootand the bladetip. In another exemplary embodiment, a turbine assembly includes a row ofcircumferentially adjacent turbine stator vanes, each vane in the row of vanesincluding anairfoil defining a chord extending axially between opposite leading andtrailing edges ofthe airfoil. The chords in a mid-span region of each vane are shorter than thechords inspan regions adjacent to the vane root and the vane tip. A turbine rotor bladefor a gasturbine engine also is provided.