CN102678336A - Machine strap fuel system for gas fuel internal combustion turbine - Google Patents
Machine strap fuel system for gas fuel internal combustion turbine Download PDFInfo
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- CN102678336A CN102678336A CN2011104004953A CN201110400495A CN102678336A CN 102678336 A CN102678336 A CN 102678336A CN 2011104004953 A CN2011104004953 A CN 2011104004953A CN 201110400495 A CN201110400495 A CN 201110400495A CN 102678336 A CN102678336 A CN 102678336A
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Abstract
The invention relates to a machine strap fuel system for a gas fuel internal combustion turbine, and relates to a machine strap fuel system, in particular to a machine strap fuel system for a gas fuel internal combustion turbine. By the machine strap fuel system, the problem that the conventional machine strap fuel system cannot meet requirements of an internal combustion turbine unit on stable running, safety protection, pollutant discharge and the like under different work conditions is solved. According to the machine strap fuel system, gas fuel is connected with the input end of a filter assembly; the output end of the filter assembly is connected with the input end of a stop valve assembly; the output end of the stop valve assembly is connected with the input end of a first gas circuit fuel valve; the output end of the first gas circuit fuel valve is connected with the input end of a first gas circuit; the output end of the stop valve assembly is connected with the input end of a second gas circuit fuel valve; the output end of the second gas circuit fuel valve is connected with the input end of the second gas circuit; and the output end of the stop valve assembly is connected with the input end of an ignition path. The machine strap fuel system is connected with the internal combustion turbine unit and provides fuel for the internal combustion turbine unit.
Description
Technical field
The present invention relates to a kind of machine carrying fuel system, be specifically related to a kind of gas fuel gas turbine machine carrying fuel system.
Background technique
Machine carrying fuel system is that driven compressor is with one of most important subsystem of gas turbine; The stable operation of gas turbine, safety protection, emission performance etc. all will rely on machine carrying fuel system to realize in varying degrees; Machine carrying fuel system not only will be according to the requirement under the Under Different Work Condition of Engine, supplies with according to certain rules and distributes fuel, and fuel flow rate is controlled and measured; Fuel-supplying pressure is monitored; But also to satisfy motor in emergency circumstances to specific (special) requirements such as the quick closedown of its proposition, emptyings, be directly connected to the reliable and stable operation of motor, and pollutant emission level of starting and chamber pressure pulsation level; We can say, machine carrying fuel system be with gas turbine performance the most closely, to the most direct subsystem of gas turbine reliable operation influence.Existing machine carrying fuel system can not satisfy under the different operating modes of gas turbine group requirements such as stable operation, safety protection, pollutant emissions.
Summary of the invention
The present invention can not satisfy the problem that under the different operating modes of gas turbine group stable operation, safety protection, pollutant emission etc. is required for solving existing machine carrying fuel system, and then proposes a kind of gas fuel gas turbine machine carrying fuel system.
The present invention addresses the above problem the technological scheme of taking to be: the present invention includes filter assemblies, shut-off valve assemblies, ignition path, first gas circuit, second gas circuit, the first gas circuit fuel valve, the second gas circuit fuel valve and a plurality of fuel conduit; Said gas fuel is connected with the input end of filter assemblies through fuel conduit; The output terminal of said filter assemblies is connected with the input end of shut-off valve assemblies through fuel conduit; The output terminal of said shut-off valve assemblies is connected with the input end of the first gas circuit fuel valve through fuel conduit; The output terminal of the said first gas circuit fuel valve is connected with the input end of first gas circuit through fuel conduit; The output terminal of said shut-off valve assemblies is connected with the input end of the second gas circuit fuel valve through fuel conduit; The output terminal of the said second gas circuit fuel valve is connected with the input end of second pipeline through fuel conduit, and the output terminal of said shut-off valve assemblies is connected with the input end of ignition path through fuel conduit.
The invention has the beneficial effects as follows: the present invention can satisfy gas turbine group stable operation under different operating modes; Satisfied the performance requirement of gas turbine to emission performance and safety protection, but shut-off valve assemblies of the present invention can guarantee gas turbine quick shutdown in emergency circumstances, the shut-in time of shut-off valve assemblies is not more than 0.1 second; Revealing grade is ANSI ClassVI; Explosive-proof grade of the present invention is UL&CSA Class I, and Division, security level are NEMA RATE 7&9.
Description of drawings
Fig. 1 is a system line schematic representation of the present invention.
Embodiment
Embodiment one: combine Fig. 1 that this mode of execution is described; The said a kind of gas fuel gas turbine machine carrying fuel of this mode of execution system comprises filter assemblies 1, shut-off valve assemblies 2, ignition path 3, first gas circuit 4, second gas circuit 5, the first gas circuit fuel valve 6, the second gas circuit fuel valve 7 and a plurality of fuel conduit 8; Said gas fuel is connected with the input end of filter assemblies 1 through fuel conduit 8; The output terminal of said filter assemblies 1 is connected with the input end of shut-off valve assemblies 2 through fuel conduit 8; The output terminal of said shut-off valve assemblies 2 is connected with the input end of the first gas circuit fuel valve 6 through fuel conduit 8; The output terminal of the said first gas circuit fuel valve 6 is connected with the input end of first gas circuit 4 through fuel conduit 8; The output terminal of said shut-off valve assemblies 2 is connected with the input end of the second gas circuit fuel valve 7 through fuel conduit 8; The output terminal of the said second gas circuit fuel valve 7 is connected with the input end of second pipeline 5 through fuel conduit 8, and the output terminal of said shut-off valve assemblies 2 is connected with the input end of ignition path 3 through fuel conduit 8.
This mode of execution middle filtrator assembly 1, shut-off valve assemblies 2, the first gas circuit fuel valve 6, the second gas circuit fuel 7 all are connected with the PLC control system, and operator can control through the PLC control system in real time.
Embodiment two: combine Fig. 1 that this mode of execution is described, on the shut-off valve assemblies 2 of the said a kind of gas fuel gas turbine machine carrying fuel of this mode of execution system pneumatic control valve 9 is installed.Other composition and annexation are identical with embodiment one.
Embodiment three: combine Fig. 1 that this mode of execution is described, the shut-off valve assemblies 2 of the said a kind of gas fuel gas turbine machine carrying fuel of this mode of execution system and the fuel conduit 8 between the ignition path 3 are provided with pulse power supply solenoid valve controller 10.Other composition and annexation are identical with embodiment one.
Working principle
During unit starting, gas fuel gets into filter assemblies 1 back and gets into shut-off valve assemblies 2 through fuel conduit 8, gets into the starting nozzle that ignition path 3 gets into unit subsequently; Carry out the gas turbine starting ignition, successfully light a fire until motor slow train operating mode, the first gas circuit fuel valve 6 is adjusted aperture under the instruction of automatic control system; To guarantee the required fuel quantity of unit operation; From the above operating mode of slow train, the second gas circuit fuel valve 7 is opened, and this moment, first gas circuit 4 and second gas circuit 5 were carried out the adaptive-flow adjusting respectively under the automatic control system instruction; The emission request of unit can be satisfied, the stable operation of unit can be guaranteed again.
Claims (3)
1. gas fuel gas turbine machine carrying fuel system; It is characterized in that: said a kind of gas fuel gas turbine machine carrying fuel system comprises filter assemblies (1), shut-off valve assemblies (2), ignition path (3), first gas circuit (4), second gas circuit (5), the first gas circuit fuel valve (6), the second gas circuit fuel valve (7) and a plurality of fuel conduit (8); Said gas fuel is connected with the input end of filter assemblies (1) through fuel conduit (8); The output terminal of said filter assemblies (1) is connected with the input end of shut-off valve assemblies (2) through fuel conduit (8); The output terminal of said shut-off valve assemblies (2) is connected with the input end of the first gas circuit fuel valve (6) through fuel conduit (8); The output terminal of the said first gas circuit fuel valve (6) is connected with the input end of first gas circuit (4) through fuel conduit (8); The output terminal of said shut-off valve assemblies (2) is connected with the input end of the second gas circuit fuel valve (7) through fuel conduit (8); The output terminal of the said second gas circuit fuel valve (7) is connected with the input end of second pipeline (5) through fuel conduit (8), and the output terminal of said shut-off valve assemblies (2) is connected with the input end of ignition path (3) through fuel conduit (8).
2. according to the said a kind of gas fuel gas turbine machine carrying fuel of claim 1 system, it is characterized in that: pneumatic control valve (9) is installed on the said shut-off valve assemblies (2).
3. according to the said a kind of gas fuel gas turbine machine carrying fuel of claim 1 system, it is characterized in that: the fuel conduit (8) between said shut-off valve assemblies (2) and the ignition path (3) is provided with pulse power supply solenoid valve controller (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104004953A CN102678336A (en) | 2011-12-06 | 2011-12-06 | Machine strap fuel system for gas fuel internal combustion turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104004953A CN102678336A (en) | 2011-12-06 | 2011-12-06 | Machine strap fuel system for gas fuel internal combustion turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102678336A true CN102678336A (en) | 2012-09-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011104004953A Pending CN102678336A (en) | 2011-12-06 | 2011-12-06 | Machine strap fuel system for gas fuel internal combustion turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102678336A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6079198A (en) * | 1998-04-29 | 2000-06-27 | General Electric Co. | Pressure compensated fuel delivery system for the combustors of turbomachinery |
| CN1526050A (en) * | 2001-07-19 | 2004-09-01 | Method for operating a burner of a gas turbine and a power plant | |
| US20060016198A1 (en) * | 2004-07-23 | 2006-01-26 | Peter Stuttaford | Apparatus and method for providing an off-gas to a combustion system |
| CN101021182A (en) * | 2006-02-15 | 2007-08-22 | 通用电气公司 | Pressure control method and system to reduce gas turbine fuel supply pressure requirements |
| CN101981294A (en) * | 2008-09-29 | 2011-02-23 | 三菱重工业株式会社 | Gas turbine control method and controller |
| CN202325859U (en) * | 2011-12-06 | 2012-07-11 | 中国船舶重工集团公司第七�三研究所 | Fuel system of machine belt of gas fuel gas turbine |
-
2011
- 2011-12-06 CN CN2011104004953A patent/CN102678336A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6079198A (en) * | 1998-04-29 | 2000-06-27 | General Electric Co. | Pressure compensated fuel delivery system for the combustors of turbomachinery |
| CN1526050A (en) * | 2001-07-19 | 2004-09-01 | Method for operating a burner of a gas turbine and a power plant | |
| US20060016198A1 (en) * | 2004-07-23 | 2006-01-26 | Peter Stuttaford | Apparatus and method for providing an off-gas to a combustion system |
| CN101021182A (en) * | 2006-02-15 | 2007-08-22 | 通用电气公司 | Pressure control method and system to reduce gas turbine fuel supply pressure requirements |
| CN101981294A (en) * | 2008-09-29 | 2011-02-23 | 三菱重工业株式会社 | Gas turbine control method and controller |
| CN202325859U (en) * | 2011-12-06 | 2012-07-11 | 中国船舶重工集团公司第七�三研究所 | Fuel system of machine belt of gas fuel gas turbine |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20120919 |