CN207740085U - A kind of gas turbine fuel system - Google Patents
A kind of gas turbine fuel system Download PDFInfo
- Publication number
- CN207740085U CN207740085U CN201721771553.2U CN201721771553U CN207740085U CN 207740085 U CN207740085 U CN 207740085U CN 201721771553 U CN201721771553 U CN 201721771553U CN 207740085 U CN207740085 U CN 207740085U
- Authority
- CN
- China
- Prior art keywords
- fuel
- valve
- pressure
- oil
- gas turbine
- 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
Landscapes
- Feeding And Controlling Fuel (AREA)
Abstract
The utility model discloses a kind of gas turbine fuel systems, are respectively to start fuel nozzle and main fuel nozzle fuel feeding using double oil circuits fuel system, can greatly improve combustion stability, efficiency of combustion and combustor exit temperature distributing homogeneity.The constructional simplicity of fuel system can be greatly improved using Fuel On Board pump, accelerating adjuster and moving electromagnetic valve etc., the environmental suitability that fuel system can be greatly improved using rotating speed and height compensation device etc. can greatly improve the service life of starting fuel nozzle and fuel system using cleaning valve etc. is started.Gas turbine fuel system provided by the utility model is significant to the simplifying the structure of gas turbine fuel system, lightweight, easy-maintaining and high reliability.
Description
Technical field
The utility model is related to gas turbine fuel system fields, particularly, are related to a kind of miniature gas turbine Fuel System
System.
Background technology
Miniature gas turbine is the small-sized Thermal Motor that a kind of newly-developed gets up, single-machine capacity ranging from 25~
300kW is mainly made of compressor, combustion chamber, turbine, retarder and fuel system, oil system etc..Miniature gas turbine
Generating set has the series of advantages such as high efficiency, low noise, low stain, small weight, small size and more integrated dilatations,
The national economy such as electric power, power field and national security etc. play an important roll and strategic importance.Develop micro-gas-turbine
Machine the relevant technologies are of great significance to China's energy, electric power, aviation, ship, vehicle and military affairs etc..
Gas turbine fuel system belongs to gas turbine important system composition, and combustion needed for gas turbine is provided by rule
Oil ensures gas turbine normal starting and maintenance gas turbine constant speed operating under any operating mode in working range, and outward
Boundary provides power.Existing fuel system is mainly by fuel pump, fuel filter, fuel oil regulating device, fuel solenoid valve and fuel nozzle
Deng composition, single oil circuit is generally used to give gas turbine fuel feeding, the fuel delivery and atomization that cannot be satisfied each operating mode of gas turbine need
It asks, frequently results in the problems such as combustion chambers burn flame instability, efficiency of combustion are low and combustor exit temperature is unevenly distributed, even
Lead to loss of ignition or flame-out, it is also by two completely self-contained single oil circuit groups partly to use the fuel system of double oil circuits fuel feeding
At complicated, equipment is various, poor reliability, cannot meet gas turbine fuel system lightweight now, easy-maintaining and high
The design requirement of reliability.Therefore, performance of a kind of simple and reliable, the compact-sized fuel system of utility model to gas turbine
It improves and stable operation is significant.
Utility model content
For the drawbacks described above and deficiency of the prior art, the utility model is intended to provide a kind of miniature gas turbine Fuel System
System is respectively to start fuel nozzle and main fuel nozzle fuel feeding using double oil circuits fuel system, can greatly improve combustion stability,
Efficiency of combustion and combustor exit temperature distributing homogeneity；Using Fuel On Board pump, accelerating adjuster and moving electromagnetic valve etc.
The structural compactness that fuel system can be greatly improved can greatly improve the ring of fuel system using rotating speed and height compensation device etc.
Border adaptability can greatly improve the service life of starting fuel nozzle and fuel system using cleaning valve etc. is started.
The utility model is that technical solution used by solving its technical problem is：
A kind of gas turbine fuel system, including fuel oil pump assembly, fuel oil regulating device, torque-motor, speed regulating control box,
Moving electromagnetic valve, fuel cut-off valve are played, cleaning valve is started, starts fuel nozzle, main fuel nozzle, which is characterized in that
-- the fuel oil pump assembly includes fuel pump；
-- the fuel oil regulating device include pressure safety valve, speed regulating control valve, accelerating adjuster, pressure-difference valve,
Rotating speed and altimetric compensation device, wherein
The pressure safety valve is arranged in the outlet of fuel pump bypass, to return to part fuel oil from bypass
The fuel inlet of the fuel pump, to maintain the fuel outlet pressure stability of fuel pump；
The speed regulating control valve is arranged in the downstream of the fuel pump, and the exposed junction of spool passes through a lever mechanism and institute
Torque-motor mechanical connection is stated, the torque-motor is communicated to connect with the speed regulating control box；
The accelerating adjuster is arranged in the downstream of the speed regulating control valve, and the accelerating adjuster is a three way type
Fuel distribution equipment, including the working connection to the right of an oil inlet, a downward working connection and one, the oil inlet and the speed regulating control
The oil outlet of valve is connected to, and the downward working connection is divided into as downward branch path and branch path to the right, the working connection to the right and institute
The normally opened port connection of moving electromagnetic valve, the common end of the branch path to the right and described moving electromagnetic valve of the downward working connection are stated
Mouth connection, downward branch path are connected to the oil inlet of the pressure-difference valve；
The oil inlet of the pressure-difference valve is connected to the downward branch path of the accelerating adjuster, oil outlet with it is described
The inlet communication of fuel cut-off valve, the pressure-difference valve include valve body and valve core link rod, and oil inlet is arranged on the right side of valve body,
The left side setting spring of valve body simultaneously introduces the charge oil pressure after the fuel pump, and the right hand top of the valve core link rod stretches out valve body
Connect with the diaphragm of the rotating speed and altimetric compensation device, the left bottom of the valve core link rod bear the fuel pump for oil pressure
Power and spring force, the right hand top of the valve core link rod bear the input pressure and the rotating speed and height of the accelerating adjuster
Spend the thrust of the diaphragm of compensator；
The rotating speed and altimetric compensation device include the diaphragm of shell and setting in the housing, the upper end right side of the diaphragm
Setting spring simultaneously introduces pressure after compressor, and bellows, the bellows and ambient air are arranged on the right side of the lower end of the diaphragm
Pressure and spring force after compressor are born in the upper end right side of connection, the diaphragm, and bellows is born on the right side of the lower end of the diaphragm
The upper end left side of pressure, the diaphragm is connect with the valve core link rod of the pressure-difference valve；
-- the import of the fuel cut-off valve is connected to the oil outlet of the pressure-difference valve, and outlet is sprayed with the main fuel
Mouth is connected to；
-- described moving electromagnetic valve is three-way electromagnetic valve, including normally closed port, the normally opened port and the common end
Mouthful, the normally opened port is connected to the working connection to the right in the accelerating adjuster, and the normally closed port starts clearly with described
The fuel inlet of clean valve is connected to, and the public port is connected to the branch path to the right in the accelerating adjuster；
-- the starting cleaning valve includes valve body and spool, and the left end of valve body sets fuel inlet, and right end is equipped with compressor
Pressure inlets afterwards, the peripheral wall of valve body are equipped with the port being connected to the starting fuel nozzle, the starting are born on the left of spool
Input pressure after solenoid valve, spool right side are arranged spring, pressure and spring force after compressor are born on the right side of spool.
Preferably, the fuel pipe inlet road of the fuel pump is provided with supercharging device.
Preferably, the fuel pump is positive displacement gear pump, is mounted on the front end of gas turbine reduction case, and by firing
Gas-turbine retarder band turns.
Preferably, the shell of the fuel oil regulating device is equipped with fuel oil mechanical position limitation block, to limit the Lever machine
The hunting range of structure then limits the open range of the speed regulating control valve.
Further, when the unexpected off-load of gas turbine, the minimum fuel oil position of the fuel oil mechanical position limitation block need to keep one
Fixed flow maintains burning, the maximum fuel position of the fuel oil mechanical position limitation block that gas turbine need to be enable to deal with unexpected add
It carries, and gas turbine surge can be prevented.
Preferably, it is equipped with manual adjusting nut in the downward working connection of the accelerating adjuster, divides downwards to adjust
The fuel feeding ratio of branch and to the right branch path.
Preferably, the fuel oil stop valve is two-way formula fuel cut-off valve, is a normally close valve, when it is powered, valve
It opens, fuel oil flows into the main fuel nozzle, if can lead to gas turbine orderly shutdown to fuel cut-off valve power-off.
Preferably, when described moving electromagnetic valve is in off-position, normally opened port is opened, and normally closed port shutdown is described
The fuel oil of accelerating adjuster is passed through the pressure-difference valve downstream completely.
Preferably, when described moving electromagnetic valve is in energized state, normally opened port shutdown, normally closed port is opened, fuel oil
After the accelerating adjuster, working connection is closed to the right, and downward branch path is connected to the pressure-difference valve, is divided to the right
Branch leads to the fuel inlet for starting cleaning valve through the public port and normally closed port.
Preferably, in starting cleaning valve, when spool be in right end, the fuel inlet in left side and towards described
Channel between dynamic fuel nozzle is connected, and pressure inlets and is closed towards the channel started between fuel nozzle after the compressor on right side
It closes；When spool is in left end, after the compressor on right side pressure inlets and towards it is described starting fuel nozzle between channel connect
It is logical, it the fuel inlet in left side and is closed towards the channel started between fuel nozzle.
Compared with the existing technology, the miniature gas turbine fuel system of the utility model, using double oil circuits fuel system point
Fuel nozzle and main fuel nozzle fuel feeding Wei not be started, combustion stability, efficiency of combustion and combustor exit temperature can be greatly improved
Spend distributing homogeneity.The knot of fuel system can be greatly improved using Fuel On Board pump, accelerating adjuster and moving electromagnetic valve etc.
Structure simplicity can greatly improve the environmental suitability of fuel system using rotating speed and height compensation device etc., be cleaned using starting
Valve etc. can greatly improve the service life for starting fuel nozzle and fuel system.Gas turbine fuel oil provided by the utility model
System is significant to the simplifying the structure of gas turbine fuel system, lightweight, easy-maintaining and high reliability.
Description of the drawings
Fig. 1 is the structural schematic diagram of the miniature gas turbine fuel system of the utility model；
Fig. 2 is the schematic diagram of the miniature gas turbine fuel system of the utility model；
Fig. 3 is the structural schematic diagram for starting cleaning valve.
Specific implementation mode
To make the purpose of this utility model, technical solution and advantage be more clearly understood, develop simultaneously implementation referring to the drawings
The utility model is further described in example.It should be noted that the realization method for not being painted or describing in attached drawing, for institute
Belong to form known to a person of ordinary skill in the art in technical field.In addition, the direction term mentioned in following embodiment, such as "upper",
"lower", "front", "rear", "left", "right", "top", "bottom" etc. are only the directions of refer to the attached drawing.Therefore, the direction term used is
For illustrating not to be used for limiting the utility model.
As shown in Fig. 1~2, the miniature gas turbine fuel system of the utility model, function is for miniature gas turbine
Start, accelerate and the operation of permanent rotating speed provides suitable fuel oil, including fuel oil pump assembly 1, fuel oil regulating device 2, torque-motor 3,
Speed regulating control box 4, rise moving electromagnetic valve 5, fuel cut-off valve 6, start cleaning valve 7, start fuel nozzle 8, main fuel nozzle 9,
The components such as various pipelines form.
Fuel oil pump assembly 1 is made of fuel pump 11 and fuel filter 12.Fuel pump 11 is a positive displacement gear pump, is mounted on
On the left of the front end of gas turbine reduction case, the drive shaft of fuel pump is inserted into the spindle portion of fuel oil control driving gear, quilt
Fuel pump transmission gear in retarder is turned by spline band.It is exported above 11 shell of fuel pump, there are one metals to filter for installation
The fuel filter 12 of core, the fuel oil that the fuel outlet discharge on pump case may be leaked from pump drive sealing or pressure-difference valve needle.
Fuel oil regulating device 2 includes pressure safety valve 21, speed regulating control valve 22, accelerating adjuster 23, pressure-difference valve
24, the components such as rotating speed and altimetric compensation device 25.
Fuel oil enters fuel pump 11 after supercharging device is pressurized from fuel inlet, is filtered by fuel filter 12, into fuel oil
Pressure safety valve 21 in regulating device 2, import of the pressure safety valve 21 by part fuel oil from bypass back to fuel pump 11, from
And the outlet pressure of fuel pump 11 is maintained to stablize.
Fuel oil flows through speed regulating control valve 22 after fuel filter 12, speed regulating control valve 22 exposed junction connection there are one lever
Mechanism 26, which is mechanically connected with torque-motor 3, to execute the opening degree instruction of torque-motor 3, torque-motor 11
Opening degree instruction sent out by speed regulating control box 4.Fuel oil mechanical position limitation block 27 is equipped on the shell of fuel oil regulating device 2, to
The hunting range of lever mechanism is limited, the open range of speed regulating control valve 22 is then limited, when the unexpected off-load of gas turbine, fuel oil
The flow that the minimum fuel oil position of mechanical position limitation block 27 need to keep certain maintains burning, the maximum fuel of fuel oil mechanical position limitation block 27
Position need to enable gas turbine deal with unexpected load, and can prevent gas turbine surge.
Fuel oil flows through accelerating adjuster 23 after speed regulating control valve 22, and accelerating adjuster 23 is a three way type fuel oil point
With device, fuel oil is divided into two-way downwards and to the right, downward oil circuit is divided into as two-way downwards and to the right, can be by adjusting manually
Its needle-valve of nut adjustment is inserted into orifice plate depth to adjust downward and two-way fuel oil to the right ratio in downward oil circuit.Fuel oil passes through
It is divided into downward after accelerating adjuster 23 and two-way, oil circuit to the right is connected with the normally opened port 51 for playing moving electromagnetic valve 5 to the right.To
Under oil circuit be divided into be connected with the public port 53 of moving electromagnetic valve 5 with two-way oil circuit to the right, oil circuit to the right downwards,
Downward oil circuit guiding fuel oil flows to the pressure-difference valve 24 in fuel oil regulating device.
It is three-way electromagnetic valve to play moving electromagnetic valve 5, has normally opened port 51, normally closed port 52 and public port 53.It is normally opened
Port 51 is connected with the oil circuit port for flowing through after accelerating adjuster 23 to the right, normally closed port 52 and the combustion for starting cleaning valve 7
Oil inlet is connected, and the port of oil circuit to the right that the oil circuit downward with accelerating adjuster 23 is flowed through of public port 53 is divided into out is connected.
It is in off-position when playing moving electromagnetic valve 5, normally opened port 51 is opened, and normally closed port 52 is closed, and fuel oil is by accelerating
After regulating device 23, it is divided into downwards with two-way to the right, downward oil circuit is towards the pressure-difference valve 24 in fuel oil regulating device, to the right
Oil circuit has passed through the normally opened port 51 of moving electromagnetic valve 5 and public port 53 also leads down into pressure-difference valve in fuel oil regulating device
24。
Fuel pressure and spring force after fuel pump 11 are born in 24 left side of pressure-difference valve, and accelerated regulating device is born on right side
The diaphragm of fuel pressure and rotating speed and altimetric compensation device 25 after 23 under is to the thrust of its valve core link rod, and spool is in left and right sides
It can be moved left and right under differential pressure action, to control the fuel flow communication mouth aperture of pressure-difference valve 24.
Pressure and spring force after compressor are born in the diaphragm upper end of rotating speed and altimetric compensation device 25, and bellows pressure is born in lower end
Power (i.e. environment atmospheric pressure), acting on the pressure difference of diaphragm top and bottom can make diaphragm rotate, to pressure-difference valve 24
There are one thrusts for valve core link rod.In certain height above sea level, environment atmospheric pressure is certain, and gas turbine starts in accelerator, pressure
Mechanism of qi outlet pressure is stepped up, and is acted on the pressure of 25 diaphragm upper end of rotating speed and altimetric compensation device and can be stepped up, makes diaphragm
Top and bottom pressure difference is stepped up, and then diaphragm will increase the thrust of the valve core link rod of pressure-difference valve 24 so that pressure difference
The spool of regulating valve 24 moves to the left, and the fuel flow communication mouth aperture of pressure-difference valve 24 increases.Similarly, work as gas turbine rotary speed
Decline, the fuel flow communication mouth aperture of pressure-difference valve 24 reduces.When gas turbine is in different altitude height starting operation, with
The increase of height above sea level, compressor pressure ratio is constant under the same rotating speed of gas turbine, and pressure before pressure=compressor after compressor
(environment atmospheric pressure) * pressure ratios, act on pressure-environment atmospheric pressure after pressure difference=compressor of diaphragm top and bottom=
(pressure ratio -1) * environment atmospheric pressures act on rotating speed and height that is, as the increase of height above sea level, environment atmospheric pressure decline
25 diaphragm top and bottom pressure difference of compensator reduces, and then diaphragm can reduce the thrust of the valve core link rod of pressure-difference valve 24,
The fuel flow communication mouth aperture of pressure-difference valve 24 reduces.Similarly, when height above sea level decline, the fuel flow communication mouth of pressure-difference valve 24
Aperture increases.
Fuel oil flows to fuel cut-off valve 6 after the pressure-difference valve 24 of fuel oil regulating device, and fuel oil stop valve 6 is two-way formula
Fuel cut-off valve is a normally close valve, and when it is powered, valve is opened, and fuel oil is able to flow into main fuel nozzle 9, if giving fuel oil
The power-off of shut-off valve 6 can lead to gas turbine orderly shutdown.
It is in energized state when playing moving electromagnetic valve 5, normally opened port 51 is closed, and normally closed port 52 is opened, and fuel oil is by accelerating
After regulating device 23, oil circuit is closed to the right, and downward oil circuit is divided into as two-way, downward oil circuit lead to fuel oil tune downwards and to the right
Pressure-difference valve 24 in regulating device, oil circuit has passed through the public port 53 of moving electromagnetic valve 5 to the right and normally closed port 52 leads to starting
Clean the fuel inlet of valve 7.
As shown in figure 3, the fuel pressure after playing moving electromagnetic valve 5 is born in the spool left side for starting cleaning valve 7, right side is held
Pressure and spring force after by compressor, under the differential pressure action of both sides, spool can move left and right.When spool is in right end, fuel oil
It import and is connected towards the channel started between fuel nozzle 8, pressure inlets and towards starting between fuel nozzle 8 after compressor
Channel close.When spool is in left end, after compressor pressure inlets and towards start fuel nozzle 8 between channel connect
It is logical, it fuel inlet and is closed towards the channel started between fuel nozzle 8.It is in energized state when playing moving electromagnetic valve 5, because of fuel oil
Pressure is more than pressure and spring force after compressor, and the spool for starting cleaning valve 7 is in right end position, and fuel oil is lived through starting cleaning
Door 7, which leads to, starts fuel nozzle 8.It is in off-position when playing moving electromagnetic valve 5, cleaning 7 fuel oil interface of valve is started and does not fire
Oil supply, the spool for starting cleaning valve 7 are in left position after compressor under pressure and spring-force driven dual, after compressor
Gas flow starts fuel nozzle 8, blows away the excess oil started in fuel nozzle, plays cleaning nozzle.
In the starting stage that gas turbine starts, starts motor and drive gas turbine accelerated service, 11 rotating speed phase of fuel pump
It should increase, fuel pump 11 starts to increase fuel feeding at this time.When rotating speed rises to the 4% of rated speed, plays moving electromagnetic valve 5 and is powered,
Igniter starts to strike sparks, and fuel oil is atomized and is ignited into combustion chamber from fuel nozzle 8 is started.When rotating speed rises to rated speed
10% when, fuel cut-off valve 6 be powered, main fuel through main fuel nozzle 9 enter combustion chamber, speed regulating control valve 22 is in speed governing at this time
It is opened by torque-motor 3 under the instruction of control box, adjusts aperture.In gas turbine starts accelerator, pressed after compressor
Power is stepped up, and just needs the more fuel oils of spray at this time, this is realized by rotating speed and altimetric compensation device 25.When on rotating speed
It is raised to the 78% of rated speed, igniter stops sparking, starts motor and powers off and disengage.When rotating speed rises to rated speed
When 96%, plays moving electromagnetic valve 5 and power off, the oil circuit after the accelerated regulating device of fuel oil 23 to the right has passed through the normally open end of moving electromagnetic valve 5
Mouth 51 and public port 53 also lead to the pressure-difference valve 24 of fuel oil regulating device so that the fuel oil pressure on 24 right side of pressure-difference valve
Power increases, and spool moves to the left, and the fuel flow communication mouth aperture of pressure-difference valve 24 increases, and leads to the fuel oil of main fuel nozzle 9
Amount increases, to improve the acceleration rate of gas turbine.Moving electromagnetic valve 5 is played to power off when rotating speed reaches 96% rated speed, this
A action can cause fuel oil step so that fuel system can provide enough fuel oils for gas turbine rated speed full load.
If gas turbine reaches 96% rotating speed not yet in 60 seconds, control system can make gas turbine stop.When gas turbine at
Work(accelerates to 100% rotating speed of rated speed, and speed regulating control box can reduce the voltage of torque-motor 3, and speed regulating control valve 22 is set
In unloaded oil mass position, which can be always maintained at until load.When gas turbine loads, speed regulating control box 4 sends out instruction
Torque-motor 3 is allowed to increase the aperture of speed regulating control valve 22.When gas turbine rotary speed is higher than rated speed, control system receives
Corresponding signal then sends out the aperture that instruction allows torque-motor 3 to reduce speed regulating control valve 22, to drop by speed regulating control box 4
Low gas turbine rotary speed, vice versa.
Gas turbine fuel system provided by the utility model is respectively to start fuel nozzle using double oil circuits fuel system
With main fuel nozzle fuel feeding, combustion stability, efficiency of combustion and combustor exit temperature distributing homogeneity can be greatly improved.Using
Fuel On Board pump, accelerating adjuster and moving electromagnetic valve etc. can greatly improve the constructional simplicity of fuel system, using rotating speed
The environmental suitability that fuel system can be greatly improved with height compensation device etc. can have been greatly improved using cleaning valve etc. is started
The service life of dynamic fuel nozzle and fuel system.Gas turbine fuel system provided by the utility model is to gas turbine fuel oil
The simplifying the structure of system, lightweight, easy-maintaining and high reliability are significant.
Furthermore, it is necessary to illustrate, the specific embodiment described in this specification, the shape of parts and components is named
Title etc. can be different.The equivalent or simple change that all structure, feature and principles according to described in the utility model patent concept are done,
It is included in the protection domain of the utility model patent.Those skilled in the art of the present invention can be to being retouched
The specific embodiment stated does various modifications or additions or substitutes by a similar method, without departing from the utility model
Structure or beyond the scope defined by this claim, all should belong to the protection range of the utility model.
Claims (8)
1. a kind of gas turbine fuel system, including fuel oil pump assembly, fuel oil regulating device, torque-motor, speed regulating control box, rise
Moving electromagnetic valve, fuel cut-off valve start cleaning valve, start fuel nozzle, main fuel nozzle, which is characterized in that
-- the fuel oil pump assembly includes fuel pump；
-- the fuel oil regulating device includes pressure safety valve, speed regulating control valve, accelerating adjuster, pressure-difference valve, rotating speed
With altimetric compensation device, wherein
The pressure safety valve is arranged in the outlet of fuel pump bypass, described to return to part fuel oil from bypass
The fuel inlet of fuel pump, to maintain the fuel outlet pressure stability of fuel pump；
The speed regulating control valve is arranged in the downstream of the fuel pump, and the exposed junction of spool passes through a lever mechanism and the power
Square motor is mechanically connected, and the torque-motor is communicated to connect with the speed regulating control box；
The accelerating adjuster is arranged in the downstream of the speed regulating control valve, and the accelerating adjuster is a three way type fuel oil
Distributor, including the working connection to the right of an oil inlet, a downward working connection and one, the oil inlet and the speed regulating control valve
Oil outlet is connected to, and the downward working connection is divided into as downward branch path and branch path to the right, the working connection to the right and described
The normally opened port of moving electromagnetic valve is connected to, and the branch path to the right of the downward working connection and the public port of described moving electromagnetic valve connect
Logical, downward branch path is connected to the oil inlet of the pressure-difference valve；
The oil inlet of the pressure-difference valve is connected to the downward branch path of the accelerating adjuster, oil outlet and the fuel oil
The inlet communication of shut-off valve, the pressure-difference valve include valve body and valve core link rod, and oil inlet is arranged in the right side of valve body, valve body
Left side setting spring and introduce the charge oil pressure after the fuel pump, the right hand top of the valve core link rod stretches out valve body and institute
Rotating speed is stated to connect with the diaphragm of altimetric compensation device, the left bottom of the valve core link rod bear the fuel pump charge oil pressure and
The right hand top of spring force, the valve core link rod bears the input pressure of the accelerating adjuster and the rotating speed is mended with height
Repay the thrust of the diaphragm of device；
The rotating speed and altimetric compensation device include the diaphragm of shell and setting in the housing, are arranged on the right side of the upper end of the diaphragm
Spring simultaneously introduces pressure after compressor, and bellows is arranged on the right side of the lower end of the diaphragm, and the bellows is connected to ambient air,
Pressure and spring force after compressor are born on the right side of the upper end of the diaphragm, and ripple pipe pressure is born on the right side of the lower end of the diaphragm,
It is connect with the valve core link rod of the pressure-difference valve on the left of the upper end of the diaphragm；
-- the import of the fuel cut-off valve is connected to the oil outlet of the pressure-difference valve, and outlet connects with the main fuel nozzle
It is logical；
-- described moving electromagnetic valve is three-way electromagnetic valve, including normally closed port, the normally opened port and the public port, institute
It states normally opened port to be connected to the working connection to the right in the accelerating adjuster, valve is cleaned in the normally closed port with the starting
Fuel inlet connection, the public port is connected to the branch path to the right in the accelerating adjuster；
-- the starting cleaning valve includes valve body and spool, and the left end of valve body sets fuel inlet, and right end is pressed after being equipped with compressor
Power import, the peripheral wall of valve body are equipped with the port being connected to the starting fuel nozzle, the starting electromagnetism are born on the left of spool
Input pressure after valve, spool right side are arranged spring, pressure and spring force after compressor are born on the right side of spool.
2. gas turbine fuel system according to claim 1, which is characterized in that the fuel inlet pipeline of the fuel pump
On be provided with supercharging device.
3. gas turbine fuel system according to claim 1, which is characterized in that the fuel pump is positive displacement gear
Pump is mounted on the front end of gas turbine reduction case, and is turned by gas turbine retarder band.
4. gas turbine fuel system according to claim 1, which is characterized in that on the shell of the fuel oil regulating device
Equipped with fuel oil mechanical position limitation block, to limit the hunting range of the lever mechanism, opening for the speed regulating control valve is then limited
Spend range.
5. gas turbine fuel system according to claim 1, which is characterized in that the downward master of the accelerating adjuster
Manual adjusting nut is equipped in oil circuit, to adjust downward branch path and to the right the fuel feeding ratio of branch path.
6. gas turbine fuel system according to claim 1, which is characterized in that the fuel oil stop valve fires for two-way formula
Oil cut-off valve is a normally close valve, and when it is powered, valve is opened.
7. gas turbine fuel system according to claim 1, which is characterized in that when described moving electromagnetic valve is in power-off
When state, normally opened port is opened, normally closed port shutdown.
8. gas turbine fuel system according to claim 1, which is characterized in that be powered when described moving electromagnetic valve is in
When state, normally opened port shutdown, normally closed port is opened.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721771553.2U CN207740085U (en) | 2017-12-18 | 2017-12-18 | A kind of gas turbine fuel system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721771553.2U CN207740085U (en) | 2017-12-18 | 2017-12-18 | A kind of gas turbine fuel system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207740085U true CN207740085U (en) | 2018-08-17 |
Family
ID=63118422
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721771553.2U Active CN207740085U (en) | 2017-12-18 | 2017-12-18 | A kind of gas turbine fuel system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207740085U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107905898A (en) * | 2017-12-18 | 2018-04-13 | 中科合肥微小型燃气轮机研究院有限责任公司 | A kind of miniature gas turbine fuel system and its control method |
-
2017
- 2017-12-18 CN CN201721771553.2U patent/CN207740085U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107905898A (en) * | 2017-12-18 | 2018-04-13 | 中科合肥微小型燃气轮机研究院有限责任公司 | A kind of miniature gas turbine fuel system and its control method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107905898A (en) | A kind of miniature gas turbine fuel system and its control method | |
| US3048014A (en) | Combustion chamber for jets and similar engines | |
| CN102482989B (en) | Turbocharger system for air-throttled engines | |
| US2786331A (en) | Fuel feed and power control for gas turbine engines | |
| CN103967622B (en) | The starting oil-feeding control system of miniature gas turbine | |
| RU2009143924A (en) | METHOD FOR GAS ENGINE AND GAS ENGINE CONTROL | |
| CN111788431B (en) | Combustor assembly fuel control | |
| US2693675A (en) | Jet engine fuel control system | |
| CN103237971B (en) | Method for running fixed gas turbine, for device that the operation of gas turbine is adjusted and generating equipment | |
| CN207740085U (en) | A kind of gas turbine fuel system | |
| US3722218A (en) | Air boost fuel atomizing system | |
| CN104696988A (en) | Combustion chamber of gas turbine and operation method of combustion chamber | |
| US2770945A (en) | Jump-type flow divider for gas turbine power plant fuel system | |
| US3124933A (en) | Leroy stram | |
| GB690168A (en) | Improvements in or relating to ignition systems of gas-turbine engines | |
| CN207813754U (en) | A kind of gas turbine fuel distribution equipment | |
| US2780055A (en) | Igniter control for engines | |
| GB2086482A (en) | Priming device for burner manifolds of gas turbine engines | |
| US2829489A (en) | Repeating cycle igniter control | |
| GB601275A (en) | Charge forming device for internal combustion engines | |
| US2807135A (en) | Free piston power plant with afterburner | |
| CN203604053U (en) | Ground gas turbine | |
| US2884997A (en) | Gas turbine fuel system including a starting accumulator | |
| CN111457583B (en) | Pressure-increasing heating and bathing two-purpose stove | |
| PL115975B1 (en) | Apparatus for controllin fuel supply to supercharged self-ignition engines |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |