CN107893702B - Fuel oil adjusting device of gas turbine - Google Patents
Fuel oil adjusting device of gas turbine Download PDFInfo
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- CN107893702B CN107893702B CN201711367899.0A CN201711367899A CN107893702B CN 107893702 B CN107893702 B CN 107893702B CN 201711367899 A CN201711367899 A CN 201711367899A CN 107893702 B CN107893702 B CN 107893702B
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- valve core
- gas turbine
- fuel
- bushing
- oil
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- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
The invention discloses a fuel oil adjusting device of a gas turbine, which has the functions of adjusting the fuel oil supply amount of a fuel oil system when the gas turbine starts, accelerates and runs at a constant rotating speed, and gradually increases the rotating speed when the gas turbine runs, and a centrifugal flyweight component can push a valve core downwards due to the action of centrifugal force. Under the action of the supporting force of the elastic body, the lever force is smaller than the supporting force of the elastic body at low rotating speed, and the flow area of the valve core matched with the bushing is 0; when the rotating speed reaches a certain degree, the valve core moves downwards, and the flow area matched with the valve core bushing gradually becomes larger. When the gas turbine reaches the rated rotation speed, the flow area of the valve core matched with the bushing reaches the maximum value. When the gas turbine exceeds the rated rotation speed, the valve core continuously moves downwards, but the flow area of the valve core matched with the bushing is gradually reduced, so that the rotation speed of the gas turbine is reduced, and the aim of preventing the gas turbine from over-rotating is fulfilled.
Description
Technical Field
The invention relates to the field of gas turbine fuel systems, in particular to a gas turbine fuel adjusting device of a gas turbine fuel system.
Background
The fuel system of the gas turbine is an important system component of the gas turbine, and provides fuel required by the gas turbine according to a rule, so that the gas turbine can be normally started in a working range, can be maintained to operate at a constant speed under any working condition, and can provide power for the outside. The accuracy of the fuel supply of the fuel system directly determines the starting success and the rotational speed stability of the gas turbine, and the accuracy of the fuel supply depends on the performance of the fuel adjusting device of the gas turbine.
The fuel supply amount of the fuel regulating device of the gas turbine is determined by the flow area of the regulating valve core of the metering valve matched with the bushing type hole and the fuel pressure difference flowing through the flow area. When the working condition is fixed, the pressure difference of the fuel oil flowing through the flow area is fixed, the fuel oil supply quantity is determined by the flow area, different flow areas can be obtained by changing the position of the valve core, and the valve core adjusting mechanism is needed to realize how to drive the adjusting valve core to be at the required position. The valve core adjusting mechanism widely used at present is driven by a motor and a servo mechanism, and the motor is driven by the aspects of heat dissipation, service life, control precision and the like of a motor, so that the use requirement of a gas turbine on a gas turbine fuel adjusting device can not be met; the servo drive mechanism is subject to low temperature adaptability and pollution resistance, and cannot meet the use requirements.
Disclosure of Invention
In view of the above-mentioned drawbacks and shortcomings of the prior art, the present invention is directed to a fuel oil adjusting device for a gas turbine, which has the function of adjusting the fuel oil supply amount of a fuel oil system when the gas turbine is started, accelerated and operated at a constant rotational speed, and providing a proper fuel oil for the gas turbine, and which can improve the fuel oil supply precision, response speed and service life of the fuel oil system, and has the advantages of compact and exquisite structure and excellent usability.
The invention adopts the technical proposal for solving the technical problems that:
the fuel oil adjusting device of the gas turbine comprises a shell, a driving head component, a centrifugal flyweight component, a valve core, an elastic body and a tension plate which are arranged in the shell, and is characterized in that,
the upper part of the shell is provided with an oil inlet, the outer side of the bottom is fixedly provided with a valve core sliding sleeve, and a valve core bushing with adjustable height, an opening at the top and a closed bottom is arranged in the valve core sliding sleeve;
the driving end at the top of the driving head assembly extends out of the shell and is mechanically connected with an external power source, and the bottom of the driving head assembly is mechanically connected with the top of the centrifugal flyweight assembly;
the valve core is a rod-shaped part with a valve core top plate at the top and an oil duct at the inside, the upper surface of the valve core top plate is propped against the top lower surface of the centrifugal flyweight assembly, an elastic body is arranged between the valve core top plate and the tension plate, the valve core penetrates through a central through hole of the tension plate to extend into an inner cavity of the valve core bushing and can slide up and down along the inner wall of the valve core bushing, an oil inlet communicated with the inner oil duct is arranged on the circumferential side wall of the top of a rod body of the valve core, an oil outlet matched with the inner oil duct is arranged on the circumferential side wall of the bottom of the rod body, an oil through hole matched with the oil outlet of the valve core is arranged on the circumferential side wall of the valve core bushing, and correspondingly, a fuel outlet matched with the oil through hole of the valve core bushing is also arranged on the circumferential side wall of the valve core sliding sleeve;
when the rotating speed of the driving head assembly is lower than a preset value, the flow area of the valve core matched with the valve core bushing is kept to be 0; when the rotating speed of the driving head assembly reaches the preset value and gradually increases to the rated rotating speed, the flow area of the valve core matched with the valve core bushing gradually increases from 0 to the maximum opening; when the rotating speed of the driving head assembly exceeds the rated rotating speed, the flow area of the valve core matched with the valve core bushing is gradually reduced from the maximum opening degree, wherein the rated rotating speed of the driving head assembly corresponds to the rated rotating speed of the gas turbine.
Preferably, the oil inlet at the upper part of the shell is communicated with an upstream oil supply device through a pipeline.
Preferably, the fuel supply means comprises a fuel pump and a fuel filter provided at the outlet of the fuel pump.
Preferably, the drive end of the top of the drive head assembly extends out of the housing to mechanically couple with a drive shaft of a fuel pump.
Preferably, the valve core sliding sleeve is of a cylindrical barrel structure with an opening at the top and a closed bottom.
Preferably, a rated rotation speed adjusting screw is arranged on the shell, and the top end of the rated rotation speed adjusting screw is propped against the bottom of the tension plate to adjust the height of the tension plate in the shell.
Preferably, an accelerating adjusting screw is arranged at the bottom of the valve core bushing, and the top end of the accelerating adjusting screw is propped against the bottom of the valve core bushing to adjust the height of the valve core bushing in the valve core sliding sleeve.
Preferably, the bottom of the drive head assembly mechanically snaps into an annular recess in the top of the centrifugal flyweight assembly.
Preferably, an elastomer seat is arranged on the upper surface of the tension plate, the lower end of the elastomer is supported on the elastomer seat, and a through hole with a shape and size matched with the central through hole of the tension plate is arranged on the elastomer seat.
Preferably, the valve core passes through the through hole of the elastomer seat and the central through hole of the tension plate and then stretches into the inner cavity of the valve core bushing.
Preferably, the fuel outlet on the circumferential side wall of the valve core sliding sleeve is communicated with the downstream component through a fuel pipeline.
Preferably, the elastic body is a spring.
Compared with the prior art, the fuel oil adjusting device of the gas turbine has the functions of adjusting the fuel oil supply amount of the fuel oil system when the gas turbine is started, accelerated and operated at a constant rotating speed, and providing proper fuel oil for the gas turbine.
Drawings
FIG. 1 is a schematic view of a fuel regulator of 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 gas turbine fuel oil adjusting device of the present invention comprises a housing 1, a driving head assembly 2, a centrifugal flyweight assembly 3, a valve core 4, an elastic body 5 and a tension plate 6, which are arranged in the housing 1. The upper portion of the housing 1 is provided with a fuel inlet, the fuel inlet is communicated with an upstream fuel supply device (such as a fuel pump and a fuel filter) through a pipeline, a valve core sliding sleeve 10 with an opening at the top and a closed bottom is fixedly arranged on the outer side of the bottom of the housing 1, and a valve core bushing 8 with an adjustable height and an opening at the top and a closed bottom is arranged in the valve core sliding sleeve 10. The driving end at the top of the driving head assembly 2 extends out of the shell 1 to be mechanically connected with a power source, the bottom of the driving head assembly 2 is mechanically connected with the centrifugal flyweight assembly 3, and in fig. 1, the bottom of the driving head assembly 2 is mechanically clamped with the annular recess at the top of the centrifugal flyweight assembly 3. The valve core 4 is a rod-shaped part with a valve core top plate arranged at the top and an oil duct arranged inside, the upper surface of the valve core top plate is propped against the top lower surface of the centrifugal flyweight assembly 3, an elastic body 5 is arranged between the valve core top plate and the tension plate 6, the valve core 4 penetrates through a central through hole of the tension plate 6 and stretches into an inner cavity of the valve core bushing 8 and can slide up and down along the inner wall of the valve core bushing 8, an oil inlet communicated with the inner oil duct is arranged on the circumferential side wall of the top of a rod body of the valve core 4, an oil outlet matched with the oil duct is arranged on the circumferential side wall of the bottom of the rod body, an oil through hole matched with the oil outlet of the valve core 4 is arranged on the circumferential side wall of the valve core bushing 8, and correspondingly, a fuel outlet matched with the oil through hole of the valve core bushing 8 is also arranged on the circumferential side wall of the valve core sliding sleeve 10.
In addition, a rated rotation speed adjusting screw 7 is arranged on the shell 1, and the top end of the rated rotation speed adjusting screw 7 is propped against the bottom of the tension plate 6 to adjust the height of the tension plate 6 in the shell 1. The bottom of the valve core bushing 8 is provided with an acceleration adjusting screw 9, and the top end of the acceleration adjusting screw 9 is propped against the bottom of the valve core bushing 8 to adjust the height of the valve core bushing 8 in the valve core sliding sleeve 10.
The invention relates to a fuel oil adjusting device of a gas turbine, which comprises the following working principles:
after passing through the upstream oil supply device (such as a fuel pump and a fuel filter), the fuel enters the device through a fuel inlet on the shell 1 and fills the inner cavity of the shell 1, the fuel in the inner cavity of the shell 1 enters an inner oil duct of the valve core 4 through an oil inlet hole on the valve core 4, and then flows out through a flow area matched with an oil outlet at the tail end of the valve core 4 and an oil outlet hole of the valve core bushing 8.
The gas turbine fuel oil adjusting device provided by the invention is generally matched with a gear type fuel oil pump, the fuel oil pump is arranged on a casing of a gas turbine speed reducer, a driving shaft of the fuel oil pump is rotated by the gas turbine speed reducer through a spline, and a driving head assembly 2 of the device is connected with the driving shaft of the fuel oil pump and is rotated by the driving head assembly. When the gas turbine operates, the rotation speed gradually rises, the rotation speed of the driving head assembly 2 carrying the centrifugal flyweight assembly 3 correspondingly increases, and the centrifugal flyweight assembly 3 can exert downward force on the valve core 4 due to the centrifugal force. Under the action of the supporting force of the elastic body, the lever force is smaller than the supporting force of the elastic body at low rotating speed, the balance cannot be changed, namely the valve core 4 cannot move downwards, the flow area matched with the valve core bushing 8 is 0, and the fuel cannot flow out from the fuel outlet of the device; however, when the rotation speed reaches a certain degree, the lever force is larger than the original supporting force of the elastic body, the balance is broken, the elastic body 5 needs to be continuously compressed to increase the supporting force to ensure the balance, the valve core 4 moves downwards at the moment, the flow area matched with the valve core bushing 8 gradually increases, and more fuel flows out from the fuel outlet of the device. When the gas turbine reaches the rated rotation speed, the flow area of the valve core 4 matched with the valve core bushing 8 reaches the maximum value, and the fuel quantity flowing out of the fuel outlet of the device reaches the maximum value correspondingly. When the gas turbine exceeds the rated rotation speed, the valve core 4 continues to move downwards, but the flow area of the valve core 4 matched with the valve core bushing 8 gradually becomes smaller, and the fuel quantity flowing out of the fuel outlet of the device is correspondingly reduced at the moment, so that the rotation speed of the gas turbine is reduced, and the aim of preventing the gas turbine from over-rotating is fulfilled.
The device can finely adjust the upper and lower positions of the tension plate 6 by manually adjusting the rated rotation speed adjusting screw 7, so as to adjust the supporting force of the elastic body on the valve core 4, correspondingly adjust the lever force for enabling the valve core 4 to move downwards, namely adjust the centrifugal force of the centrifugal flyweight assembly 3, and different centrifugal forces of the centrifugal flyweight assembly 3 correspond to different rotation speeds of the gas turbine. The device can finely adjust the position of the valve core bushing 8 by manually adjusting the acceleration adjusting screw 9, so that the flow area of the valve core 4 matched with the valve core bushing 8 reaches the maximum value when the gas turbine reaches the rated rotation speed.
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 (11)
1. The fuel oil adjusting device of the gas turbine comprises a shell, a driving head assembly, a centrifugal flyweight assembly, a valve core, an elastic body and a tension plate, wherein the driving head assembly, the centrifugal flyweight assembly, the valve core, the elastic body and the tension plate are arranged in the shell, the elastic body is a spring,
the upper part of the shell is provided with an oil inlet, the outer side of the bottom is fixedly provided with a valve core sliding sleeve, and a valve core bushing with adjustable height, an opening at the top and a closed bottom is arranged in the valve core sliding sleeve;
the driving end at the top of the driving head assembly extends out of the shell and is mechanically connected with an external power source, and the bottom of the driving head assembly is mechanically connected with the top of the centrifugal flyweight assembly;
the valve core is a rod-shaped part with a valve core top plate at the top and an oil duct at the inside, the upper surface of the valve core top plate is propped against the top lower surface of the centrifugal flyweight assembly, an elastic body is arranged between the valve core top plate and the tension plate, the valve core penetrates through a central through hole of the tension plate to extend into an inner cavity of the valve core bushing and can slide up and down along the inner wall of the valve core bushing, an oil inlet communicated with the inner oil duct is arranged on the circumferential side wall of the top of a rod body of the valve core, an oil outlet matched with the inner oil duct is arranged on the circumferential side wall of the bottom of the rod body, an oil through hole matched with the oil outlet of the valve core is arranged on the circumferential side wall of the valve core bushing, and correspondingly, a fuel outlet matched with the oil through hole of the valve core bushing is also arranged on the circumferential side wall of the valve core sliding sleeve;
when the rotating speed of the driving head assembly is lower than a preset value, the flow area of the valve core matched with the valve core bushing is kept to be 0; when the rotating speed of the driving head assembly reaches the preset value and gradually increases to the rated rotating speed, the flow area of the valve core matched with the valve core bushing gradually increases from 0 to the maximum opening; when the rotating speed of the driving head assembly exceeds the rated rotating speed, the flow area of the valve core matched with the valve core bushing is gradually reduced from the maximum opening degree, wherein the rated rotating speed of the driving head assembly corresponds to the rated rotating speed of the gas turbine.
2. The gas turbine fuel adjustment device according to claim 1, wherein the oil inlet of the upper portion of the housing communicates with an upstream oil supply device through a pipe.
3. The gas turbine fuel conditioning assembly of claim 2 wherein the fuel supply assembly includes a fuel pump and a fuel filter disposed at an outlet of the fuel pump.
4. A gas turbine fuel adjustment device according to claim 3, wherein the drive end of the top portion of the drive head assembly extends out of the housing to mechanically connect with a drive shaft of a fuel pump.
5. The gas turbine fuel regulator of claim 1, wherein the valve core sliding sleeve has a cylindrical barrel structure with an open top and a closed bottom.
6. The gas turbine fuel adjustment device according to claim 1, wherein a rated rotation speed adjustment screw is provided on the housing, and a tip of the rated rotation speed adjustment screw is abutted against a bottom of the tension plate for adjusting a height of the tension plate in the housing.
7. The gas turbine fuel adjustment device according to claim 1, wherein an acceleration adjustment screw is provided at the bottom of the spool bushing, and the tip of the acceleration adjustment screw is abutted against the bottom of the spool bushing to adjust the height of the spool bushing in the spool sliding sleeve.
8. The gas turbine fuel adjustment device of claim 1, wherein the bottom of the drive head assembly mechanically engages an annular recess in the top of the centrifugal flyweight assembly.
9. The fuel oil adjusting device of the gas turbine according to claim 1, wherein an elastic body seat is arranged on the upper surface of the tension plate, the lower end of the elastic body is supported on the elastic body seat, and a through hole with a shape and a size matched with those of the central through hole of the tension plate is arranged on the elastic body seat.
10. The gas turbine fuel adjustment device according to claim 1, wherein the spool extends into the inner cavity of the spool bushing after passing through the through hole of the elastomer seat and the center through hole of the tension plate.
11. The gas turbine fuel regulator of claim 1, wherein the fuel outlet on the circumferential sidewall of the spool sleeve communicates with downstream components via a fuel line.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711367899.0A CN107893702B (en) | 2017-12-18 | 2017-12-18 | Fuel oil adjusting device of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711367899.0A CN107893702B (en) | 2017-12-18 | 2017-12-18 | Fuel oil adjusting device of gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107893702A CN107893702A (en) | 2018-04-10 |
| CN107893702B true CN107893702B (en) | 2023-05-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711367899.0A Active CN107893702B (en) | 2017-12-18 | 2017-12-18 | Fuel oil adjusting device of gas turbine |
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| CN (1) | CN107893702B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109488463B (en) * | 2018-11-21 | 2021-03-26 | 中国航发西安动力控制科技有限公司 | Centrifugal counterweight mechanism for fluid pipeline |
| CN114251091B (en) * | 2022-02-10 | 2023-12-15 | 国能神东煤炭集团有限责任公司 | Cooling device for cutting part of coal mining machine |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB736394A (en) * | 1951-09-13 | 1955-09-07 | Fairey Aviat Co Ltd | Improvements relating to gas turbine ignition apparatus |
| GB731538A (en) * | 1952-05-30 | 1955-06-08 | W H Allen Sons & Company Ltd | Improvements in and relating to spill burner fuel supply systems |
| US3159036A (en) * | 1963-04-11 | 1964-12-01 | Caterpillar Tractor Co | Engine speed limiting means responsive to lubricating oil pressure |
| DE2411342C2 (en) * | 1974-03-09 | 1982-08-05 | Mtu Motoren- Und Turbinen-Union Friedrichshafen Gmbh, 7990 Friedrichshafen | Device for limiting the speed of an internal combustion engine as a function of the lubricating oil pressure |
| US4355610A (en) * | 1980-03-28 | 1982-10-26 | Caterpillar Tractor Co. | Servo boosted governor control for engines |
| CN207673441U (en) * | 2017-12-18 | 2018-07-31 | 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 oil regulating device |
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2017
- 2017-12-18 CN CN201711367899.0A patent/CN107893702B/en active Active
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| CN107893702A (en) | 2018-04-10 |
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