Patent ID: 6802695
Filing Date: 2004-10-12
Classification: F01D,Y02T

Abstract:
An axial flow gas turbine, comprising: in axial succession, a turbine and a turbine exhaust section, the turbine comprising a turbine nozzle containing a low pressure turbine stage having an annular row of stator vanes followed in axial succession by an annular row of rotor blades, wherein the low pressure turbine stage is characterized by the following parameters:a ratio of vane airfoil pitch to vane airfoil axial width at a root end of a vane airfoil (P/W) is in a region of 1.0 to 1.2; a ratio of blade airfoil pitch to blade airfoil axial width at a root end of a blade airfoil (P/W) is in the region of 0.6; a ratio of blade diameter at a tip end of the blade airfoil to blade diameter at the root end of the blade airfoil is in a region of 1.6-1.8; and a ratio of a axial length of the exhaust section to the blade airfoil height (L/H) is no greater than a value in a region of 4:1; said parameters being subject to a predetermined amount of variation.