Patent ID: 9719354
Date: 2017-08-01
CPC Classifications: F01D

Claim:
1. A gas turbine comprising: a compressor for compressing air; a combustor for burning the compressed air with fuel; and a turbine to which generated combustion gas is supplied, wherein the turbine includes turbine vane elements and turbine blade elements that are alternately positioned in a direction in which the combustion gas fluidizes, the turbine vane elements and turbine blade elements being arranged in a turbine cylinder having a cylindrical shape, and an axial flow flue gas diffuser having a cylindrical shape and connected to a rear portion of the turbine cylinder after a last stage of the turbine vane elements or the turbine blade elements, wherein the turbine vane elements include a plurality of turbine vanes positioned at equal intervals in a circumference direction of the turbine cylinder and the turbine blade elements include a plurality of turbine blades fixed at equal intervals in the circumference direction, wherein the turbine vanes extend from a vane base end side to a vane tip end with a vane tip side radially inward of the vane tip end in a radial direction in the turbine cylinder, the turbine vanes at the last stage of the turbine vane elements having a throat width at the vane base end side and at the vane tip side larger than a throat width at a center portion of the turbine vanes, or the turbine blades extend from a blade base end side to a blade tip end with a blade tip side radially inward of the blade tip end in the radial direction in the turbine cylinder, the turbine blades at the last stage of the turbine blade elements having a throat width at the blade base end side and at the blade tip side larger than a throat width at a center portion of the turbine blades, wherein the axial flow flue gas diffuser having a shape configured to restore pressure maintaining an increased total pressure of flue gas exiting the last stage of the turbine vane elements or the turbine blade elements at their respective the tip side and the base end side, wherein the vane tip side is between the center portion of the turbine vanes and the vane tip end, and the vane tip side corresponds to an area close to the vane tip end rather than the center portion of the turbine vanes, wherein the blade tip side is between the center portion of the turbine blades and the blade tip end, and the blade tip side corresponds to an area close to the blade tip end rather than the center portion of the turbine blades, wherein the respective heights of the turbine vane elements and the turbine blade elements increase toward the axial flow flue diffuser, and wherein each of the turbine vanes at the last stage of the turbine vane elements and the turbine blades at the last stage of the turbine blade elements has a maximum height.