阅读说明：本技术 用于燃气轮机的双燃料环形管路系统 (Dual fuel ring line system for a gas turbine ) 是由 刘子健 马振国 于 2021-01-08 设计创作，主要内容包括：本发明涉及一种双燃料管路系统,特别涉及用于燃气轮机的双燃料环形管路系统,包括气体燃料管路系统,还包括液体燃料管路系统；所述液体燃料管路系统与气体燃料管路系统固定在压气机外壳上；液体燃料管路系统与气体燃料管路系统均为环形管路；液体燃料管路系统与气体燃料管路系统接入燃气轮机燃烧筒。本发明所公开的用于燃气轮机的双燃料环形管路系统可以单独给燃气轮机供给气体燃料或液体燃料,并能够实现对燃气轮机进行双燃料供给的切换。(The invention 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 dual-fuel annular pipeline system for the gas turbine can independently supply gas fuel or liquid fuel to the gas turbine and can realize the switching of dual-fuel supply to the gas turbine.)

1. Dual fuel ring 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. The 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. The 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. The 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. The 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. The 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. The 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.

Technical Field

The present invention relates to a dual fuel circuit system, and more particularly to a dual fuel annular circuit system for a gas turbine engine.

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. In order to adapt to different conditions and select different fuel supplies, the invention designs a dual-fuel supply system which can well realize the switching of dual-fuel supply for the gas turbine.

Disclosure of Invention

In order to solve the technical problem, the invention provides a dual-fuel annular pipeline system for a gas turbine, which can realize switching of dual-fuel supply for the gas turbine.

In order to achieve the purpose, the invention adopts the technical scheme that:

a dual fuel loop circuit system for a gas turbine, including a gaseous fuel circuit system and further including a liquid fuel circuit 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 invention has the beneficial effects that:

the dual-fuel annular pipeline system for the gas turbine is designed to supply gas fuel or liquid fuel to the gas turbine independently and realize the switching of dual-fuel supply to the gas turbine.

Drawings

FIG. 1 shows a schematic view of the overall structure of the present invention;

FIG. 2 is a schematic representation 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

Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

Referring to fig. 1, a dual fuel loop circuit system for a gas turbine engine is shown in accordance with the present invention, secured 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 line 12 is divided into a liquid fuel main line 101 and a liquid fuel branch line 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.

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.