CN214424589U - Dual-fuel annular pipeline system for gas turbine - Google Patents
Dual-fuel annular pipeline system for gas turbine Download PDFInfo
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- CN214424589U CN214424589U CN202120040956.XU CN202120040956U CN214424589U CN 214424589 U CN214424589 U CN 214424589U CN 202120040956 U CN202120040956 U CN 202120040956U CN 214424589 U CN214424589 U CN 214424589U
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- fuel
- pipeline
- liquid fuel
- gas turbine
- compressed air
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Abstract
The utility model relates to a dual-fuel pipeline system, in particular to a dual-fuel annular pipeline system for a gas turbine, which comprises a gas fuel pipeline system and a liquid fuel pipeline system; the liquid fuel pipeline system and the gas fuel pipeline system are fixed on the compressor shell; the liquid fuel pipeline system and the gas fuel pipeline system are both annular pipelines; the liquid fuel pipeline system and the gas fuel pipeline system are connected into the combustion cylinder of the gas turbine. The utility model discloses a double fuel annular pipeline system for gas turbine can supply with gaseous fuel or liquid fuel for gas turbine alone to can realize carrying out the switching that double fuel supplied with to gas turbine.
Description
Technical Field
The utility model relates to a dual fuel piping system, in particular to dual fuel annular piping system for gas turbine.
Background
The gas turbine is widely applied to various fields such as petrifaction, maritime work, cities and towns, schools, hospitals and the like as the most basic power supply equipment in industry and commerce. The fuel that provides is different under different fields and the environment, if under emergency operating mode, mostly uses diesel oil as fuel, in mill, urban area, mostly uses the natural gas as fuel. Can select different fuel supplies under the different situation in order to adapt to, the utility model designs a system that dual fuel was supplied with, can realize providing the switching that dual fuel was supplied with to gas turbine well.
SUMMERY OF THE UTILITY MODEL
In order to solve the technical problem, the utility model provides a double fuel annular pipeline system for gas turbine can realize providing the switching of double fuel supply to gas turbine.
In order to realize the purpose, the utility model discloses a technical scheme is:
a dual fuel annular line system for a gas turbine, comprising a gaseous fuel line system and further comprising a liquid fuel line system; the liquid fuel pipeline system and the gas fuel pipeline system are fixed on the compressor shell; the liquid fuel pipeline system and the gas fuel pipeline system are both annular pipelines; the liquid fuel pipeline system and the gas fuel pipeline system are connected into the combustion cylinder of the gas turbine.
Further, the liquid fuel pipeline system comprises a liquid fuel inlet, a liquid fuel pipeline, a compressed air inlet, a compressed air pipeline, a three-way electromagnetic valve, a nozzle and a pipe clamp;
the liquid fuel inlet is connected with a liquid fuel pipeline, and the compressed air inlet is connected with a compressed air pipeline;
the liquid fuel pipeline and the compressed air pipeline are connected to the nozzle through a three-way electromagnetic valve;
the liquid fuel pipeline system is fixed on the compressor shell through a pipe clamp.
Further, the liquid fuel pipeline is divided into a liquid fuel main pipeline and a liquid fuel branch pipeline.
Further, the liquid fuel branch pipe is at least 1.
Further, the compressed air pipeline is divided into a compressed air main pipeline and a compressed air branch pipeline.
Further, the number of the compressed air branch pipes is at least 1.
Further, the number of the nozzles is at least 1.
Compared with the prior art, the beneficial effects of the utility model are that:
a dual fuel loop circuit system for a gas turbine is designed to supply gas fuel or liquid fuel to the gas turbine independently and to enable dual fuel supply switching for the gas turbine.
Drawings
Fig. 1 shows a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic view of the liquid fuel piping system of the present invention;
wherein, 1, a gas fuel pipeline system; 2. a liquid fuel piping system; 11. a liquid fuel inlet; 12. a liquid fuel line; 13. a compressed air inlet; 14. a compressed air line; 15. a three-way electromagnetic valve; 16. a nozzle; 17. a pipe clamp; 101. a liquid fuel main line; 102. a liquid fuel branch line; 103. a compressed air main line; 104. a compressed air branch pipe.
Detailed Description
The following describes embodiments of the present invention in detail with reference to the drawings.
As shown in fig. 1, the present invention is a dual fuel annular piping system for a gas turbine engine, which is fixed to a compressor. The dual-fuel annular pipeline system for the gas turbine comprises a gas fuel pipeline system 1 and a liquid fuel pipeline system 2; the liquid fuel pipeline system 2 and the gas fuel pipeline system 1 are both annular pipelines; the liquid fuel line system 2 and the gas fuel line system 1 are connected to the combustion cans of the gas turbine.
As shown in fig. 2, the liquid fuel piping system 2 includes a liquid fuel inlet 11, a liquid fuel piping 12, a compressed air inlet 13, a compressed air piping 14, a three-way solenoid valve 15, a nozzle 16, a pipe clamp 17;
the liquid fuel inlet 11 is connected with a liquid fuel pipeline 12, and the compressed air inlet 13 is connected with a compressed air pipeline 14;
the liquid fuel pipeline 12 and the compressed air pipeline 14 are connected to a nozzle 16 through a three-way electromagnetic valve 15;
the liquid fuel line system 2 is fixed to the compressor housing by means of a pipe clamp 17.
Preferably, the liquid fuel pipeline 12 is divided into a liquid fuel main pipeline 101 and a liquid fuel branch pipeline 102, and the liquid fuel main pipeline 101 is connected with the liquid fuel branch pipeline 102.
Preferably, the liquid fuel branch pipes 102 are 4.
Preferably, the compressed air line 14 is divided into a compressed air main line 103 and a compressed air branch line 104, and the compressed air main line 103 is connected with the compressed air branch line 104.
Preferably, the compressed air branch pipes 104 are 4.
Preferably, there are 4 nozzles 16.
Preferably, the number of the combustion cylinders is 4, and the combustion cylinders are annularly arranged on the gas turbine.
In actual use, when separate liquid fuel supply is required, the gas fuel valve on the gas fuel supply unit is closed first, and the three-way electromagnetic valve 15 is switched to liquid fuel intake; at this time, the gas turbine is supplied with a separate liquid fuel; closing the liquid fuel supply pump and the pneumatic valve when it is necessary to switch from the liquid fuel supply to the gaseous fuel supply; the three-way electromagnetic valve 15 is switched to the compressed air inlet, at the moment, the liquid gas pipeline is closed, the compressed air conducts pipeline purging on the pipeline, then, the gas fuel valve is opened, and the switching to gas fuel supply can be conducted.
When the supply of the single gas fuel is needed, the three-way electromagnetic valve 15 is switched to the inlet of compressed air, and the gas fuel valve is opened, so that the gas turbine is supplied with the single gas fuel; when it is necessary to switch from the gas fuel supply to the liquid fuel supply, the gas fuel valve is closed, the three-way electromagnetic valve 15 is switched to the liquid fuel intake, and the liquid fuel pump and the gas valve are opened, so that the liquid fuel supply can be switched.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in the embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. A dual fuel annular line system for a gas turbine comprising a gas fuel line system (1), characterized in that: also comprises a liquid fuel pipe system (2); the liquid fuel pipeline system (2) and the gas fuel pipeline system (1) are fixed on the shell of the compressor; the liquid fuel pipeline system (2) and the gas fuel pipeline system (1) are both annular pipelines; the liquid fuel pipeline system (2) and the gas fuel pipeline system (1) are connected into a combustion cylinder of the gas turbine.
2. A dual fuel loop circuit system for a gas turbine as claimed in claim 1 wherein: the liquid fuel pipeline system (2) comprises a liquid fuel inlet (11), a liquid fuel pipeline (12), a compressed air inlet (13), a compressed air pipeline (14), a three-way electromagnetic valve (15), a nozzle (16) and a pipe clamp (17);
the liquid fuel inlet (11) is connected with a liquid fuel pipeline (12), and the compressed air inlet (13) is connected with a compressed air pipeline (14);
the liquid fuel pipeline (12) and the compressed air pipeline (14) are connected to a nozzle (16) through a three-way electromagnetic valve (15);
the liquid fuel pipeline system (2) is fixed on the compressor shell through a pipe clamp (17).
3. A dual fuel loop circuit system for a gas turbine as claimed in claim 2 wherein: the liquid fuel pipeline (12) is divided into a liquid fuel main pipeline (101) and a liquid fuel branch pipeline (102).
4. A dual fuel loop circuit system for a gas turbine as claimed in claim 3 wherein: the number of the liquid fuel branch pipelines (102) is at least 1.
5. A dual fuel loop circuit system for a gas turbine as claimed in claim 2 wherein: the compressed air pipeline (14) is divided into a compressed air main pipeline (103) and a compressed air branch pipeline (104).
6. A dual fuel loop circuit system for a gas turbine as claimed in claim 5 wherein: the number of the compressed air branch pipelines (104) is at least 1.
7. A dual fuel loop circuit system for a gas turbine as claimed in claim 2 wherein: the number of the nozzles (16) is at least 1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120040956.XU CN214424589U (en) | 2021-01-08 | 2021-01-08 | Dual-fuel annular pipeline system for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120040956.XU CN214424589U (en) | 2021-01-08 | 2021-01-08 | Dual-fuel annular pipeline system for gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214424589U true CN214424589U (en) | 2021-10-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120040956.XU Active CN214424589U (en) | 2021-01-08 | 2021-01-08 | Dual-fuel annular pipeline system for gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214424589U (en) |
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2021
- 2021-01-08 CN CN202120040956.XU patent/CN214424589U/en active Active
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