Gas turbine with improved blade and vane and flue gas diffuser

Patent metadata

Field	Value
Publication number	US-9719354-B2
Application number	US-201214008513-A
Country	US
Kind code	B2
Filing date	Mar 23, 2012
Priority date	Mar 30, 2011
Publication date	Aug 1, 2017
Grant date	Aug 1, 2017

Abstract

A gas turbine burns the air compressed in a compressor with supplying fuel in a combustor so as to obtain rotary power by supplying the generated combustion gas to a turbine. The turbine includes turbine vane elements and turbine blade elements that are alternately positioned in a direction in which the combustion gas fluidizes in a turbine cylinder having a cylindrical shape, and a flue gas diffuser having a cylindrical shape and connected to a rear portion of the turbine cylinder. The turbine blade element includes a plurality of turbine blades positioned at equal intervals in the circumference direction. The turbine blades have a throat width on a longitudinal end side made larger than a throat width on a longitudinally intermediate portion side. This efficiently restores the pressure of the flue gas. This improves the efficiency of the turbine so that the performance can be improved.

First claim

The invention claimed is:

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.

2. The gas turbine according to claim 1 , wherein the turbine blades of the last stage have the throat width at the blade base end side fixed on a turbine shaft, and the throat width at the blade tip side is made larger than the throat width at the blade base end side.

3. The gas turbine according to claim 1 , wherein the turbine vanes of the last stage have the throat width at the vane base end side substantially the same as the throat width on the vane tip side.

4. The gas turbine according to claim 1 , wherein the turbine vanes and the turbine blades of the last stage both have the throat width at their respective the base end side and the tip side larger than the throat width at their respective the center portion.

Assignees

• Kitagawa Hitoshi
• Sakamoto Yasuro
• Ito Eisaku
• Mitsubishi Hitachi Power Sys

Inventors

• Kitagawa Hitoshi
• Sakamoto Yasuro
• Ito Eisaku

Classifications

• F01D5/142

  of the blades of successive rotor or stator blade-rows · CPC title

• F01D5/14 Primary

  Form or construction (selecting particular materials, measures against erosion or corrosion F01D5/28) · CPC title

• F01D5/145

  Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title

• F01D5/141 Primary

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• F05B2220/302

  in gas turbines · CPC title