Turbine exhaust structure and gas turbine

Patent metadata

Field	Value
Publication number	US-9845689-B2
Application number	US-201214008434-A
Country	US
Kind code	B2
Filing date	Mar 22, 2012
Priority date	Mar 29, 2011
Publication date	Dec 19, 2017
Grant date	Dec 19, 2017

Abstract

In a turbine exhaust structure and a gas turbine, a turbine casing ( 26 ) formed in an annular shape to constitute a combustion gas passage A is provided. An exhaust diffuser ( 31 ) formed in an annular shape to constitute a flue gas passage (B) is connected to the turbine casing ( 26 ) to constitute a configuration. By providing a pressure loss body ( 61 ) in the exhaust diffuser ( 31 ), efficient pressure recovery can be carried out, which improves turbine efficiency, thereby enabling improvement of the performance.

First claim

The invention claimed is:

1. A turbine exhaust structure including a casing formed in an annular shape around a central axis to constitute a combustion gas passage, in which an exhaust diffuser formed in an annular shape to constitute a flue gas passage is connected to the casing, comprising:
a pressure loss body which is formed in a ring shape and provided in the exhaust diffuser,
wherein the pressure loss body includes a porous member arranged in the flue gas passage of the exhaust diffuser, and
an axial thickness of an outer circumference side and an axial thickness of an inner circumference side of the porous member are formed to be thinner than an axial thickness of a middle portion.

2. The turbine exhaust structure according to claim 1 , wherein a support structure penetrating the exhaust diffuser in a radial direction is provided, and the pressure loss body is arranged in a downstream side of the support structure in a flow direction of a flue gas.

3. A gas turbine in which a fuel is supplied to the compressed air, compressed in a compressor, in a combustor to create combustion, and the produced combustion gas is supplied to a turbine to obtain rotational power,
comprising the turbine exhaust structure according to claim 1 .

4. A turbine exhaust structure including a casing formed in an annular shape to constitute a combustion gas passage, in which an exhaust diffuser formed in an annular shape to constitute a flue gas passage is connected to the casing, comprising:
a pressure loss body which is formed in a ring shape and provided in the exhaust diffuser,
wherein the pressure loss body includes a plurality of heat transfer tubes which are formed in a ring shape and in which heat is exchanged between a flue gas and a heat exchange medium flowing inside the plurality of heat transfer tubes, and a plurality of spokes which support the plurality of heat transfer tubes to the exhaust diffuser, and
a pressure loss of a radially outer side and a pressure loss of a radially inner side are set to be smaller than a pressure loss of a radially middle side.

5. A gas turbine in which a fuel is supplied to the compressed air, compressed in a compressor, in a combustor to create combustion, and the produced combustion gas is supplied to a turbine to obtain rotational power, comprising the turbine exhaust structure according to claim 4 .

6. A turbine exhaust structure according to claim 4 , wherein the plurality of heat transfer tubes are disposed such that at least one of a gap between adjacent ones of the plurality of heat transfer tubes in a radially outer portion of the exhaust diffuser and a gap between adjacent ones of the plurality of heat transfer tubes in a radially inner portion of the exhaust diffuser become larger than a gap between adjacent ones of the plurality of heat transfer tubes in a radially middle portion of the exhaust diffuser.

7. A turbine exhaust structure including a casing formed in an annular shape to constitute a combustion gas passage, in which an exhaust diffuser formed in an annular shape to constitute a flue gas passage is connected to the casing, comprising:
a pressure loss body which is formed in a ring shape and provided in the exhaust diffuser,
wherein the pressure loss body includes a porous member arranged in the flue gas passage of the exhaust diffuser, and
an opening ratio of an area in an outer circumference portion and an opening ratio of an area of an inner circumference portion of the porous member are greater than an opening ratio of an area of a middle circumference portion of the porous member.

8. A gas turbine in which a fuel is supplied to the compressed air, compressed in a compressor, in a combustor to create combustion, and the produced combustion gas is supplied to a turbine to obtain rotational power, comprising the turbine exhaust structure according to claim 7 .

Assignees

• Kitagawa Hitoshi
• Sakamoto Yasuro
• Ito Eisaku
• Mitsubishi Heavy Ind Ltd

Inventors

• Kitagawa Hitoshi
• Sakamoto Yasuro
• Ito Eisaku

Classifications

• F05D2260/213

  by the provision of a heat exchanger within the cooling circuit · CPC title

• F01D9/02 Primary

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F05D2250/52

  Outlet · CPC title

• F02C7/00 Primary

  Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) · CPC title

• F01D25/30 Primary

  Exhaust heads, chambers, or the like · CPC title