公开(公告)号：US20170138202A1

公开(公告)日：2017-05-18

申请号：US14941706

申请日：2015-11-16

Applicant: General Electric Company

Inventor： Aspi Rustom Wadia ,  Lyle Douglas Dailey ,  Christopher Ryan Johnson ,  Daniel Mollmann

IPC: F01D5/14 ,  F01D9/04

CPC classification number: F01D5/141 ,  F01D9/041 ,  F05D2220/32 ,  F05D2240/125 ,  F05D2240/307 ,  Y02T50/672 ,  Y02T50/673

Abstract: Turbine assemblies for gas turbine engines are provided. In one embodiment, a turbine assembly includes a row of circumferentially adjacent turbine rotor blades, each blade in the row of blades including an airfoil defining a chord extending axially between opposite leading and trailing edges of the airfoil. The chords in a mid-span region of each blade are shorter than the chords in span regions adjacent to the blade root and the blade tip. In another exemplary embodiment, a turbine assembly includes a row of circumferentially adjacent turbine stator vanes, each vane in the row of vanes including an airfoil defining a chord extending axially between opposite leading and trailing edges of the airfoil. The chords in a mid-span region of each vane are shorter than the chords in span regions adjacent to the vane root and the vane tip. A turbine rotor blade for a gas turbine engine also is provided.