CN107965390B - Fuel distribution device of gas turbine and control method thereof - Google Patents
Fuel distribution device of gas turbine and control method thereof Download PDFInfo
- Publication number
- CN107965390B CN107965390B CN201711369226.9A CN201711369226A CN107965390B CN 107965390 B CN107965390 B CN 107965390B CN 201711369226 A CN201711369226 A CN 201711369226A CN 107965390 B CN107965390 B CN 107965390B
- Authority
- CN
- China
- Prior art keywords
- fuel oil
- fuel
- gas turbine
- starting
- oil
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—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
- F02C7/22—Fuel supply systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—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
- F02C7/22—Fuel supply systems
- F02C7/222—Fuel flow conduits, e.g. manifolds
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—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
- F02C7/22—Fuel supply systems
- F02C7/232—Fuel valves; Draining valves or systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—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
- F02C7/26—Starting; Ignition
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/304—Spool rotational speed
Abstract
The invention discloses a fuel oil distribution device of a gas turbine and a control method thereof, wherein the fuel oil distribution device comprises an acceleration adjusting device and a starting electromagnetic valve, when the starting electromagnetic valve is in a power-off state, fuel oil of the acceleration adjusting device is completely introduced into a main fuel oil way positioned at the downstream of the acceleration adjusting device; when the starting electromagnetic valve is in an electrified state, after the fuel oil passes through the acceleration adjusting device, the right main oil way is closed, and the right branch way is led to the starting fuel oil way through the public port and the normally closed port. The fuel oil distribution device of the gas turbine can enable the fuel oil system to have two fuel oil supply paths, wherein one path supplies oil for the starting oil path and the other path supplies oil for the main fuel oil path, and when the fuel oil supply to the starting oil path is stopped, the fuel oil is completely gathered to the main fuel oil path, so that the acceleration rate of the gas turbine can be improved, and enough fuel oil can be provided for the full load of the rated rotation speed of the gas turbine. The fuel oil distribution device provided by the invention has an exquisite and compact structure, and can improve the reliability of a fuel oil system.
Description
Technical Field
The invention relates to the technical field of fuel systems of gas turbines, in particular to a fuel distribution device of a gas turbine and a control method thereof.
Background
In the past, a single oil way is generally adopted for supplying oil to a combustion chamber in a fuel system of a gas turbine, and a part of the fuel system for supplying oil by adopting double oil ways also consists of two completely independent single oil ways, so that the structure is complex and the reliability is poor. With the increasing requirement on the performance of the gas turbine, the traditional oil supply mode can not meet the fuel oil supply and atomization requirements of various working conditions of the gas turbine, so that the problems of unstable combustion flame, low combustion efficiency, uneven temperature distribution of the outlet of a combustion chamber and the like of the gas turbine are often caused, and even the ignition failure or flameout is caused. Therefore, the valve is a simple and reliable double-oil-way fuel system with a compact structure, has great significance for improving the performance and stably operating the gas turbine, and the fuel distribution device of the valve enables the fuel system to adopt a double-oil-way fuel supply mode and has a compact structure, so that the simplicity and the reliability of the fuel system can be greatly improved.
Valve content
In order to overcome the defects and shortcomings in the prior art, the invention provides a fuel distribution device of a gas turbine and a control method thereof, wherein after the fuel distribution device is arranged in a fuel system, fuel is divided into two paths, one path is supplied to a gas turbine starting nozzle for starting ignition of the gas turbine, the other path is supplied to a gas turbine main fuel nozzle, the gas turbine is operated, and the two paths of fuel can be respectively cut off or opened. The device can obviously optimize the ignition success rate of the gas turbine and the temperature distribution of the outlet of the combustion chamber, and improve the performance and the reliable running time of the gas turbine.
The invention adopts the technical proposal for solving the technical problems that:
a fuel oil distribution device of a gas turbine comprises an acceleration adjusting device and a starting electromagnetic valve, and is characterized in that,
the accelerating and adjusting device is a three-way fuel oil distribution device and comprises an oil inlet, a downward main oil way and a rightward main oil way, wherein the oil inlet is communicated with an upstream fuel oil supply loop through a pipeline, the downward main oil way is divided into a downward branch and a rightward branch, and the downward branch is communicated with a main fuel oil way of the gas turbine;
the starting electromagnetic valve is a three-way electromagnetic valve and comprises a normally closed port, a normally open port and a public port, wherein the normally open port is communicated with a rightward main oil way in the acceleration adjusting device, the normally closed port is communicated with a starting fuel oil way of the gas turbine, and the public port is communicated with a rightward branch way in the acceleration adjusting device.
Preferably, a manual adjusting nut is arranged in the downward main oil path of the acceleration adjusting device and is used for adjusting the oil supply proportion of the downward branch path and the rightward branch path.
Further, a control valve is arranged on the downward branch of the acceleration adjusting device.
Preferably, when the starting electromagnetic valve is in a power-off state, the normally open port is opened, the normally closed port is closed, and the fuel of the acceleration adjusting device is completely introduced into a main fuel oil path positioned downstream of the acceleration adjusting device.
Preferably, when the starting electromagnetic valve is in an electrified state, the normally open port is closed, the normally closed port is opened, the right main oil passage is closed after the fuel passes through the acceleration adjusting device, and the right branch passage is led to the starting fuel oil passage through the public port and the normally closed port.
Further, during the starting of the gas turbine, when the rotational speed of the gas turbine increases to around 4% of the rated rotational speed, the starting solenoid valve is energized, the control valve on the downward branch is closed, and fuel oil is led to the starting fuel oil path through the rightward branch via the common port and the normally closed port; when the rotating speed of the gas turbine rises to the vicinity of 10% of the rated rotating speed, a control valve on the downward branch is opened, and fuel oil is simultaneously led to the main fuel oil way through the downward branch; when the rotational speed of the gas turbine increases to around 96% of the nominal rotational speed, the starting solenoid valve is de-energized and the fuel of the acceleration control device is completely fed to the main fuel line downstream thereof.
According to another aspect of the present invention, the present invention also provides a control method of the above-mentioned fuel dispensing device of a gas turbine, wherein the control method includes the following steps:
SS1, in the process of starting the gas turbine, when the rotating speed of the gas turbine rises to be about 4% of the rated rotating speed, the starting electromagnetic valve is electrified, the control valve on the downward branch is closed, and fuel oil is led to the starting fuel oil path through the right branch through the public port and the normally closed port;
SS2. When the speed of the gas turbine rises to around 10% of the rated speed, the control valve on the downward branch is opened, and the fuel is simultaneously led to the main fuel oil path through the downward branch;
SS3. When the speed of the gas turbine increases to around 96% of the nominal speed, the starting solenoid valve is de-energized and the fuel of the acceleration regulator is completely passed into the main fuel circuit downstream thereof.
The invention relates to a fuel oil distribution device of a gas turbine, which comprises the following working principles:
the fuel enters the device after passing through the parts such as a fuel pump, a fuel filter and a fuel adjusting device in the fuel system, and the fuel is divided into a downward path and a rightward path after passing through the acceleration adjusting device 1. The acceleration adjusting device 1 can adjust the ratio of the fuel oil in the downward and rightward paths by manually adjusting the upper nut to adjust the depth of the needle valve inserted into the orifice plate. The starting electromagnetic valve 2 is a three-way electromagnetic valve and is provided with a normally open port, a normally closed port and a public port, wherein the normally open port is connected with the right oil path port of the acceleration adjusting device 1, the normally closed port is connected with the starting fuel oil path port, and the public port is connected with the right oil path port which is separated from the downward oil path of the acceleration adjusting device 1. When the starting electromagnetic valve is electrified, the normally open port is closed, the normally closed port is opened, and after fuel enters the device and passes through the acceleration adjusting device 1, the rightward oil way is closed, and the downward oil way is opened. The downward oil way is divided into a downward oil way and a rightward oil way, one way is communicated to the starting fuel oil way to the right through a public port and a normally closed port of the starting electromagnetic valve 2, and supplies oil to a starting fuel nozzle for ignition and starting of the gas turbine; one path of the oil is downwards led to the main fuel oil path, and when the electromagnetic valve of the main fuel oil path is opened, the oil is supplied to the main fuel nozzle for the operation of the gas turbine. When the starting electromagnetic valve is powered off, the normally open port is opened, the normally closed port is closed, fuel oil is divided into a downward path and a rightward path after entering the device and passing through the acceleration adjusting device 1, the downward path leads to the main fuel oil path, when the electromagnetic valve of the main fuel oil path is opened, the main fuel oil nozzle supplies oil, and when the electromagnetic valve of the main fuel oil path is opened, the rightward path also leads to the main fuel oil path through the normally open port and the public port of the starting electromagnetic valve 2, and when the electromagnetic valve of the main fuel oil path is opened, the main fuel oil path supplies oil for the main fuel oil nozzle.
In the starting process of the gas turbine, when the rotating speed rises to 4% of the rated rotating speed, the starting electromagnetic valve 2 is electrified, the igniter starts to ignite, fuel enters the combustion chamber from the starting fuel nozzle to be atomized and ignited, when the rotating speed rises to 10% of the rated rotating speed, the electromagnetic valve of the main fuel oil path is opened, fuel enters the combustion chamber through the main fuel nozzle at the same time, when the rotating speed rises to 96% of the rated rotating speed, the starting electromagnetic valve 2 is powered off, the fuel enters the device and then is divided into a downward path and a rightward path after entering the device, the downward oil path leads to the main fuel oil path, and the rightward oil path leads to the main fuel oil path through a normally open port and a public port of the starting electromagnetic valve 2, so that the acceleration rate of the gas turbine is improved. The action of de-energizing the start solenoid valve 2 causes a fuel jump that provides sufficient fuel for full load at the rated speed of the gas turbine.
Compared with the prior art, the fuel oil distribution device of the gas turbine and the control method thereof can enable the fuel oil system to have two fuel oil supply paths, wherein one path supplies oil for the starting nozzle, the other path supplies oil for the main fuel nozzle, and when the fuel oil supply to the starting nozzle is stopped, the fuel oil is completely gathered to the main fuel nozzle, so that the acceleration rate of the gas turbine can be improved, and enough fuel oil can be provided for the full load of the rated rotation speed of the gas turbine. The fuel oil distribution device provided by the invention has an exquisite and compact structure, and can improve the reliability of a fuel oil system.
Drawings
FIG. 1 is a schematic view of a fuel distribution device for a gas turbine according to the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be further described in detail below by referring to the accompanying drawings and examples. It should be noted that the implementation manner not shown or described in the drawings is a manner known to those of ordinary skill in the art. In addition, directional terms such as "upper", "lower", "front", "rear", "left", "right", "top", "bottom", and the like, which are mentioned in the following embodiments, are only directions referring to the drawings. Thus, the directional terminology is used for purposes of illustration and is not intended to be limiting of the invention.
As shown in fig. 1, the fuel oil distribution device of the gas turbine comprises an acceleration adjusting device 1 and a starting electromagnetic valve 2, wherein the acceleration adjusting device 1 is a three-way fuel oil distribution device and comprises an oil inlet 11, a downward main oil path 13 and a rightward main oil path 12, the oil inlet 11 is communicated with an upstream fuel oil supply loop through a pipeline, the downward main oil path 13 is divided into a downward branch path 131 and a rightward branch path 132, and the downward branch path 131 is provided with a control valve and is communicated with a main fuel oil path of the gas turbine; the starting electromagnetic valve 2 is a three-way electromagnetic valve and comprises a normally open port 21, a normally closed port 22 and a public port 23, wherein the normally open port 21 is communicated with a rightward main oil way 12 in the acceleration adjusting device 1, the normally closed port 22 is communicated with a starting fuel oil way of the gas turbine, and the public port 23 is communicated with a rightward branch 132 in the acceleration adjusting device 1.
The fuel enters the device through a fuel pump, a fuel filter, a fuel adjusting device and the like in the fuel system. The acceleration adjusting device 1 can adjust the ratio of the two fuel paths of the downward branch 131 and the rightward branch 132 by manually adjusting the depth of the needle valve inserted into the orifice plate by adjusting the upper nut. When the starting electromagnetic valve 2 is electrified, the normally open port 21 is closed, the normally closed port 22 is opened, the fuel oil enters the device and passes through the acceleration adjusting device 1, the rightward main oil passage 12 is closed, the downward main oil passage 13 is opened, the rightward branch passage 132 is communicated with the starting fuel oil passage through the public port and the normally closed port of the starting electromagnetic valve 2, and supplies oil to the starting fuel oil nozzle for ignition and starting of the gas turbine; the downward main oil path 13 leads to the main oil path, and when the control valve on the branch path is opened, the downward main oil path 13 supplies oil to the main oil path for the operation of the gas turbine. When the starting electromagnetic valve 2 is powered off, the normally open port is opened, the normally closed port is closed, and after fuel enters the device and passes through the acceleration adjusting device 1, the fuel is completely introduced into a main fuel oil path positioned at the downstream of the acceleration adjusting device.
In particular, during the starting process of the gas turbine, when the rotation speed is increased to 4% of the rated rotation speed, the starting electromagnetic valve 2 is electrified, the igniter starts to ignite, fuel enters the combustion chamber from the starting fuel nozzle to be atomized and ignited, when the rotation speed is increased to 10% of the rated rotation speed, the electromagnetic valve of the main fuel oil path is opened, fuel enters the combustion chamber through the main fuel nozzle at the same time, when the rotation speed is increased to 96% of the rated rotation speed, the starting electromagnetic valve 2 is powered off, the fuel enters the device and is divided into a downward path and a rightward path after passing through the acceleration adjusting device 1, the downward path leads to the main fuel oil path, and the rightward path also leads to the main fuel oil path through the normally open port and the common port of the starting electromagnetic valve 2, so that the acceleration rate of the gas turbine is improved. The action of de-energizing the start solenoid valve 2 causes a fuel jump that provides sufficient fuel for full load at the rated speed of the gas turbine.
The fuel oil distribution device of the gas turbine provided by the invention can be characterized in that the fuel oil system is provided with two fuel oil supply ways, one way supplies oil for the starting nozzle and the other way supplies oil for the main fuel oil nozzle, and when the fuel oil supply to the starting nozzle is stopped, the fuel oil is completely gathered to the main fuel oil nozzle, so that the acceleration rate of the gas turbine can be improved, and enough fuel oil can be provided for the full load of the rated rotation speed of the gas turbine. The fuel oil distribution device provided by the invention has an exquisite and compact structure, and can improve the reliability of a fuel oil system.
In addition, the specific embodiments described in the present specification may differ in terms of parts, shapes of components, names, and the like. All equivalent or simple changes of the structure, characteristics and principle according to the inventive concept are included in the protection scope of the present invention. Those skilled in the art may make various modifications or additions to the described embodiments or substitutions in a similar manner without departing from the scope of the invention as defined in the accompanying claims.
Claims (3)
1. A fuel oil distribution device of a gas turbine comprises an acceleration adjusting device and a starting electromagnetic valve, and is characterized in that,
the accelerating and adjusting device is a three-way fuel oil distribution device and comprises an oil inlet, a downward main oil way and a rightward main oil way, wherein the oil inlet is communicated with an upstream fuel oil supply loop through a pipeline, the downward main oil way is divided into a downward branch and a rightward branch, the downward branch is communicated with a main fuel oil way of the gas turbine, and a control valve is arranged on the downward branch;
the starting electromagnetic valve is a three-way electromagnetic valve and comprises a normally-closed port, a normally-open port and a public port, wherein the normally-open port is communicated with a rightward main oil way in the accelerating and adjusting device, the normally-closed port is communicated with a starting fuel oil way of the gas turbine, the public port is communicated with a rightward branch way in the accelerating and adjusting device, and when the starting electromagnetic valve is in an electrified state, the normally-open port is closed, the normally-closed port is opened, the rightward main oil way in the accelerating and adjusting device is closed, the rightward branch way is communicated with the starting fuel oil way of the gas turbine through the public port and the normally-closed port of the starting electromagnetic valve, and fuel oil of the accelerating and adjusting device is introduced into the starting fuel oil way of the gas turbine through the rightward branch way, the public port and the normally-closed port of the starting electromagnetic valve; when the starting electromagnetic valve is in a power-off state, the normally open port is opened, the normally closed port is closed, a rightward main oil passage in the acceleration adjusting device is communicated with a rightward branch passage through the normally open port and the public port of the starting electromagnetic valve, one part of fuel of the acceleration adjusting device directly enters the downward branch passage, and the other part of fuel sequentially passes through the rightward main oil passage, the normally open port and the public port of the starting electromagnetic valve and the rightward branch passage and then enters the downward branch passage, and finally, the fuel is completely introduced into a main fuel oil passage positioned at the downstream;
during the starting process of the gas turbine, when the rotating speed of the gas turbine rises to the vicinity of 4% of the rated rotating speed, the starting electromagnetic valve is electrified, the control valve on the downward branch is closed, and fuel oil is led to the starting fuel oil path through the right branch through the public port and the normally closed port; when the rotating speed of the gas turbine rises to the vicinity of 10% of the rated rotating speed, a control valve on the downward branch is opened, and fuel oil is simultaneously led to the main fuel oil way through the downward branch; when the rotational speed of the gas turbine increases to around 96% of the nominal rotational speed, the starting solenoid valve is de-energized and the fuel of the acceleration control device is completely fed to the main fuel line downstream thereof.
2. The fuel distribution device of a gas turbine according to claim 1, wherein a manual adjusting nut is provided in a downward main oil passage of the acceleration adjusting device for adjusting the oil supply ratio of the downward branch passage and the rightward branch passage.
3. A control method of a fuel distribution device of a gas turbine according to claim 1 or 2, characterized by comprising the steps of:
SS1, in the process of starting the gas turbine, when the rotating speed of the gas turbine rises to be about 4% of the rated rotating speed, the starting electromagnetic valve is electrified, the control valve on the downward branch is closed, and fuel oil is led to the starting fuel oil path through the right branch through the public port and the normally closed port;
SS2. When the speed of the gas turbine rises to around 10% of the rated speed, the control valve on the downward branch is opened, and the fuel is simultaneously led to the main fuel oil path through the downward branch;
SS3. When the speed of the gas turbine increases to around 96% of the nominal speed, the starting solenoid valve is de-energized and the fuel of the acceleration regulator is completely passed into the main fuel circuit downstream thereof.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711369226.9A CN107965390B (en) | 2017-12-18 | 2017-12-18 | Fuel distribution device of gas turbine and control method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711369226.9A CN107965390B (en) | 2017-12-18 | 2017-12-18 | Fuel distribution device of gas turbine and control method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107965390A CN107965390A (en) | 2018-04-27 |
| CN107965390B true CN107965390B (en) | 2023-09-15 |
Family
ID=61995452
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711369226.9A Active CN107965390B (en) | 2017-12-18 | 2017-12-18 | Fuel distribution device of gas turbine and control method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107965390B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11159348A (en) * | 1997-12-01 | 1999-06-15 | Mitsubishi Heavy Ind Ltd | Main nozzle switching control method for oil burning combustor |
| CN101255821A (en) * | 2007-03-02 | 2008-09-03 | 涡轮梅坎公司 | Method of starting a gas turbine helicopter engine, a fuel feed circuit for such an engine, and an engine having such a circuit |
| CN103603727A (en) * | 2013-11-21 | 2014-02-26 | 中国南方航空工业(集团)有限公司 | Start fuel control system of turboshaft engine |
| CN106640379A (en) * | 2016-10-17 | 2017-05-10 | 中国民用航空飞行学院 | Starting and oil-supply system of micro turbine engine and starting and oil-supply method thereof |
| CN207813754U (en) * | 2017-12-18 | 2018-09-04 | 中科合肥微小型燃气轮机研究院有限责任公司 | A kind of gas turbine fuel distribution equipment |
-
2017
- 2017-12-18 CN CN201711369226.9A patent/CN107965390B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11159348A (en) * | 1997-12-01 | 1999-06-15 | Mitsubishi Heavy Ind Ltd | Main nozzle switching control method for oil burning combustor |
| CN101255821A (en) * | 2007-03-02 | 2008-09-03 | 涡轮梅坎公司 | Method of starting a gas turbine helicopter engine, a fuel feed circuit for such an engine, and an engine having such a circuit |
| CN103603727A (en) * | 2013-11-21 | 2014-02-26 | 中国南方航空工业(集团)有限公司 | Start fuel control system of turboshaft engine |
| CN106640379A (en) * | 2016-10-17 | 2017-05-10 | 中国民用航空飞行学院 | Starting and oil-supply system of micro turbine engine and starting and oil-supply method thereof |
| CN207813754U (en) * | 2017-12-18 | 2018-09-04 | 中科合肥微小型燃气轮机研究院有限责任公司 | A kind of gas turbine fuel distribution equipment |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107965390A (en) | 2018-04-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102144131A (en) | Method and system for controlling fuel to a dual stage nozzle | |
| EP0309485B1 (en) | Wide range gaseous fuel combustion system for gas turbine engines | |
| US4833878A (en) | Wide range gaseous fuel combustion system for gas turbine engines | |
| CN107905898B (en) | Fuel system of miniature gas turbine and control method thereof | |
| CN107905899B (en) | Fuel supply system of gas turbine and control method thereof | |
| CN202733905U (en) | Dual-purpose oil-gas burner | |
| CN107965390B (en) | Fuel distribution device of gas turbine and control method thereof | |
| US20130219911A1 (en) | Combustion system for a gas turbine engine and method for directing fuel flow within the same | |
| CN207813754U (en) | A kind of gas turbine fuel distribution equipment | |
| CN110887059A (en) | Gas fuel supply system applied to DLE type combustion cylinder | |
| JP2006077661A (en) | Fuel supply device | |
| CN101569950A (en) | Hydro-oxygen flame cutting method and device | |
| CN214007317U (en) | Engine | |
| CN201121259Y (en) | Cloth velocity control device of injection overflow dyeing machine | |
| JP6256735B2 (en) | Liquid fuel combustion equipment | |
| US6745557B2 (en) | Hydraulic valve arrangement | |
| CN102338396A (en) | Ignition device of cutting torch | |
| CN201731481U (en) | Large regulating ratio gas nozzle pulse combustion system | |
| CN101893235B (en) | Fuel combusting nozzle pulse combusting system with large adjusting ratio | |
| CN205779396U (en) | Combined electromagnetic oil spout supercharging electromagnetism jet hybrid fuel jet device | |
| CN110345472A (en) | One vegetable oil fuel kitchen range | |
| CN210197688U (en) | Oil return system of fuel oil fan heater | |
| CN204227456U (en) | Automatic control combustion machine | |
| CN207080994U (en) | A kind of diesel fuel burner for preventing fuel feeding from lagging | |
| JPS6143224A (en) | Fuel oil system of gas turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |