CN209053695U - Gas turbine engine systems - Google Patents
Gas turbine engine systems Download PDFInfo
- Publication number
- CN209053695U CN209053695U CN201821506887.1U CN201821506887U CN209053695U CN 209053695 U CN209053695 U CN 209053695U CN 201821506887 U CN201821506887 U CN 201821506887U CN 209053695 U CN209053695 U CN 209053695U
- Authority
- CN
- China
- Prior art keywords
- motor
- gas turbine
- fuel
- oil
- mist
- 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
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
A kind of gas turbine engine systems include gas turbine, fuel system, control system and for starting the inspiration motor of the gas turbine.Fuel system is connect with the combustion chamber, to supply fuel oil to combustion chamber.Control system includes motor control loop, which controls inspiration motor by motor control loop.Wherein, motor control loop includes motor-drive circuit, and motor-drive circuit control when inspiring motor to run with electric motor mode inspires the operation of motor.The gas turbine engine systems steadily can safely start, and steadily run.
Description
Technical field
The utility model relates to a kind of gas turbine engine systems, and particularly, gas turbine therein can be miniature gas turbine,
The miniature gas turbine more particularly can be used as smoke generator.
Background technique
Gas turbine is a kind of internal combustion type motive power machine device.The operation logic of gas turbine is, by fuel combustion products
As working medium, it is made to be continuously flowed into the impeller of gas turbine, impeller rotation, to convert machine for the chemical energy of fuel
Tool energy.
Currently used gas turbine can be divided into heavy duty gas turbine, lightweight gas turbine and micro- according to structure type
Type gas turbine etc., and the gas turbine of these types can be applied to a variety of occasions, such as start as aero-engine, ship
It machine or applies in generating set, etc..Wherein, miniature gas turbine can be used as aero-engine etc., or also be used as
Smoke generator, to be applied to military field.
Shown in the schematic diagram of the structural principle of conventional gas turbine as shown in figure 1.Wherein, the main portion of gas turbine 100
Dividing includes compressor 10, turbine 20 and combustion chamber 30, by axis between the compression impellor of compressor 10 and the turbine wheel of turbine 20
40 are connected.In the process of running, compressor 10 is started by external power source first, thus compressor 10 is from the big of surrounding
Air is sucked in gas, and is compressed it.Compressed air is transported in combustion chamber 30.In this way, compressed air and penetrating are fired
Combustion reaction occurs for the fuel burnt in room, generates high-temperature fuel gas.High-temperature fuel gas flows into turbine 20, and expansion work, pushes whirlpool
Wheel rotation is taken turns, turbine wheel then passes through axis 40 and compression impellor is driven to rotate together.High-temperature fuel gas after burning is in band action pneumatic
While machine, there are also output mechanical work of the extra energy as gas turbine.The mechanical work can be used to generate electricity, as aircraft
Or propulsive force of ship etc..
The advantages of gas turbine, is, can be easy to carry out the integrated dilatation of more gas turbines, be suitable for pluralities of fuel,
Specific fuel consumption is low, and low noise in operational process, discharge is low, with small vibration, maintenance rate is low, and can carry out to gas turbine long-range
Remote control and diagnosis, etc..
To gas turbine, especially miniature gas turbine starting optimization and guarantee that its long-time steady operation is this field
The problem of middle concern.Specifically, the range of speeds of especially miniature gas turbine is big, when acceleration and shutdown when starting
Deceleration time is all shorter, it is therefore desirable to can efficiently control stable operation of unit, and prevent during starting and running
Gas turbine surge or resonance, this is gas turbine, particularly for miniature gas turbine urgent problem to be solved.
Utility model content
The utility model is to solve the problems of above prior art and make.The purpose of this utility model is
A kind of gas turbine engine systems including gas turbine and its control device are provided, which can steadily start,
And even running during operation.
The gas turbine engine systems of the utility model include: gas turbine, which includes compressor, turbine and be located at
Combustion chamber between compressor and turbine, the compression impellor of compressor and the turbine wheel of turbine are linked together by main shaft,
Wherein, it is provided with igniter in combustion chamber, has jet pipe in the downstream connection of turbine；
Fuel system, fuel system are connect with combustion chamber, to supply fuel oil to combustion chamber；
Wherein, the gas turbine engine systems further include:
Motor is inspired, inspires the output shaft of motor to be connected with main shaft, and can run with electric motor mode, is fired in starting
Main axis is driven when gas-turbine；And
Motor control loop inspires motor to connect to power supply through motor control loop, wherein motor control loop includes electricity
Drive circuit, motor-drive circuit control when inspiring motor to run with electric motor mode inspire the operation of motor；
Electronic control unit, electronic control unit controls motor control loop, and then controls the operation for inspiring motor.
By the control to motor is inspired, circuit is especially driven by motor to the inspiration motor run under electric motor mode
Control, it can be ensured that inspire motor start gas turbine with security and stability.In this process, the surge of gas turbine is prevented
And/or the generation of resonance.In other words, the gas turbine engine systems of the utility model enhance the operating, outstanding of gas turbine therein
It is the stationarity and safety of its starting operating, and then can protect components therein.
Preferably, above-mentioned motor-drive circuit acquisition inspires the counter electromotive force of the machine winding of motor, as to inspiration
The control parameter of motor.
For gas turbine with inspiring for motor, which can also preferably be run with generator mode.It is right
Ying Di, motor control loop further include regulator rectifier circuit, wherein in the generator mode, regulator rectifier circuit will inspire electricity
The electricity that machine issues is changed into the direct current of burning voltage.By the setting of the regulator rectifier circuit, solves the hair for inspiring motor
Electric continuation of the journey problem, effectively increases the service life of the gas turbine.
The fuel system of gas turbine can include: fuel tank, fuel feed pump, fuel feed pump be connected to fuel tank and combustion chamber it
Between, and fuel pump is provided on fuel feed pump, fuel pump is for fuel oil to be pumped into combustion chamber from fuel tank；And oil return pipe,
Oil return pipe is connected between fuel tank and combustion chamber, and trigger valve is provided on oil return pipe；Wherein, electronic control unit can
Control at least one of fuel pump and trigger valve.
Further, the micro-control valve being additionally provided on the oil return pipe, micro-control valve are arranged in parallel with trigger valve.In this structure
In, oil return pipe includes two-way oil return in parallel, and wherein micro-control valve can be used to control the amount of fuel to flow back from combustion chamber, or from another
For one side, micro-control valve control participates in the amount of fuel of burning in a combustion chamber, so that the running speed of gas turbine is controlled,
And then control the operating condition of gas turbine.
Preferably gas turbine engine systems can further include smoking device.Gas turbine therein is used as smoke generator as a result,.Its
In, which includes: at least one mist oil burner nozzle, which is arranged on jet pipe；Mist fuel tank holds in mist fuel tank
Receiving has the mist for smoke oily；And mist oil pump, mist oil pump are connected between mist oil burner nozzle and mist fuel tank, to be sprayed via mist oil
Mouth sprays mist oil into jet pipe.
Gas turbine engine systems may also include lubricating system, which provides lubricating oil to gas turbine.
In the present invention, electronic control unit can control the lubricating oil in mist oil pump, and/or acquisition lubricating system
Pressure simultaneously controls lubricating system based on lubricating oil pressure.
The operation method of the above-mentioned gas turbine engine systems of the utility model is as follows:
A. the power supply for inspiring motor is connected；
B. when electronic control unit receives enabling signal, electronic control unit starts motor-drive circuit, Jin Eryou
Motor-drive circuit, which is opened, inspires motor, inspires motor to drive the main axis of gas turbine, thus drives compression impellor and whirlpool
Take turns wheel rotation；
C. when the revolving speed of main shaft reaches the first revolving speed, fuel system supplies fuel oil to combustion chamber, and is carried out by igniter
Igniting so that fuel oil and the air phase reaction that is sucked by compression impellor and burn, the high-temperature fuel gas promotion turbine leaf for generation of burning
Wheel rotation；
D. when the revolving speed of main shaft reaches the second revolving speed, electronic control unit controls motor-drive circuit, and cutting inspires electricity
The power supply of machine, and close igniter；
E. when electronic control unit receives stopping signal, electronic control unit control fuel system stops to combustion chamber
Supply fuel oil.
In this way, being can ensure that first in gas turbine startup stage, combustion gas is steadily safely driven by inspiration motor
Turbine starts initial launch.
Wherein, motor-drive circuit acquisition inspires the counter electromotive force of the machine winding of motor, as to inspiration motor
Control parameter.
Preferably above-mentioned first revolving speed is 3500~4000rpm, such as preferably can be 3800rpm；And/or above-mentioned second
Revolving speed is 5500~8000rpm, such as preferably can be 7000rpm.
Preferably, in stepb, if main shaft does not reach the first revolving speed within the first predetermined time, alarm is triggered, electricity
Sub-control unit cutting inspires the power supply of motor.It can play the role of misoperation protection as a result,.First predetermined time can root
Factually border is set, for example, first predetermined time is 10~30s, preferably, in a kind of specific situation, this is first predetermined
Time is 20s.
Specifically, in the step a of this method or in stepb, according to the geographical environment tune where gas turbine engine systems
Save the aperture of micro-control valve.In step c, electronic control unit is on valve, and starts fuel pump, is fired with pumping to combustion chamber
Oil.In step d, trigger valve is closed, so that the fuel oil being supplied in combustion chamber dramatically increases, so that the speed of mainshaft is increased to volume
Determine revolving speed.
Preferably, trigger valve is first kept open in step d, until the revolving speed of main shaft is increased to third revolving speed, connect
Trigger valve continue to be kept open within second scheduled time, then turn off trigger valve.In this way, can be reached in gas turbine
To before rated speed, slow train warming-up first is carried out to the gas turbine, to be conducive to the subsequent stable operation of gas turbine.
In a kind of actual situation, it preferably can be 13000rpm that third revolving speed, which is 12000~13000rpm,；And/or
Second predetermined time was 5~20s, preferably can be 5s.
As described above, inspiring motor that can also run with generator mode, therefore, in above-mentioned step d, when main shaft
After revolving speed is more than the 4th revolving speed of gas turbine, gas turbine, which drives, inspires motor to run with generator mode, also, by electricity
Sub-control unit starts regulator rectifier circuit, is exported in the form of stable DC by the electric power that motor will be inspired to issue.
The gas turbine of the utility model also acts as smoke generator.In this way, gas turbine engine systems just will also include it is above
Disclosed smoking device.In this way, when electronic control unit receives smoke signal, electronic control is single in the step d of method
Member starting mist oil pump, it is oily from mist fuel tank to jet pipe pumping mist.That is, electronic control unit can also control smoke process.
Structure and corresponding operation method by the above-mentioned gas turbine engine systems of the utility model, solve combustion gas wheel
Machine stablizes the problem of being safely operated when starting using motor is inspired, and improves the continuation of the journey inspired under electric power generation mode
Ability extends the service life of gas turbine.Moreover, being effectively protected the combustion gas wheel by steadily starting gas turbine
Components in machine system further increase the service life of the gas turbine in this way.
Detailed description of the invention
Fig. 1 shows the structural schematic diagram of existing gas turbine.
Fig. 2 shows the schematic diagrams of the gas turbine engine systems of the utility model.
Fig. 3 shows the schematic diagram that motor is inspired used in the utility model gas turbine engine systems.
Specific embodiment
Specific embodiment of the present utility model is described in detail below in conjunction with Fig. 2~Fig. 3.It is to be appreciated that attached
Shown in figure is only the preferred embodiment of the utility model, does not constitute the limitation to the scope of the utility model.This
The technical staff in field various to the utility model progress on the basis of embodiment shown in the drawings can obviously repair
Change, modification, equivalence replacement, these all fall within the scope of the present invention.
Fig. 2 shows the schematic block diagrams of the gas turbine engine systems 100 of the utility model.It can be seen in fig. 2 that the combustion
Gas turbine system 100 include gas turbine, the gas turbine include compressor 110, turbine 120 and be located at compressor 110 and whirlpool
Combustion chamber 130 and jet pipe, the compression impellor of compressor 110 and the turbine wheel of turbine 120 between wheel 120 pass through main shaft
It links together, so that compressor 110 and turbine 120 link.Combustion chamber 130 includes fuel nozzle 132, is used for combustion chamber
130 internal spray fuel oils.Preferably, may be provided with multiple fuel oil sprays being annularly arranged circumferentially about in combustion chamber 130
Mouth 132.Also, combustion chamber 130 is also connected with igniter 131, which sprays into inside combustion chamber 130 for lighting
Fuel oil.
When the gas turbine of gas turbine engine systems 100 is used as smoke generator, smoke dress is also connected in the downstream of turbine 120
140 are set, specifically the mist oil burner nozzle of such as smoking device 140 is connected on the jet pipe in 120 downstream of turbine.Smoking device
140 further include mist fuel tank 142 and the mist oil pump 141 being connected between mist fuel tank 142 and mist oil burner nozzle, and mist oil pump 141 is by mist
Smoke in fuel tank 142 is ejected into jet pipe with mist oil by mist oil burner nozzle, is mixed and is sprayed with the combustion gas stream in jet pipe
Jet pipe, and then form smog.
Gas turbine engine systems 100 include fuel system, to supply fuel oil to combustion chamber 130.As shown in Figure 2, Fuel System
System includes fuel tank 154, and fuel feed pump 155 and oil return pipe 156 are connected between fuel tank 154 and combustion chamber 130.Wherein, exist
Fuel pump 151 is installed on fuel feed pump 155, is pumped for the fuel nozzle 132 to combustion chamber 130, for example towards combustion chamber 130
Fuel oil.
Preferably, oil return pipe 156 is divided to for two branches, to be formed as two-way oil return.Wherein, it is in series in a branch
Trigger valve 153 is in series with micro-control valve 152 in another branch.When (micro-control valve 152 is complete at this time in the open state for trigger valve 153
Open), the common oil return of two-way branch, recirculating oil quantity is maximum at this time, and the oil mass that atomizer 132 is ejected to combustion chamber 130 is minimum, and burning supplies
Can be also minimum, the revolving speed of gas turbine is minimum, so that gas turbine is in state at a slow speed.When trigger valve 153 is in close state
When, only it is provided with the branch oil return all the way of micro-control valve 152.At this point, when adjusting micro-control valve 152 so that returning in corresponding branch
When oil mass reduces, the amount of fuel that atomizer 132 is ejected to combustion chamber 130 increases, when amount of fuel reaches the optimal amount of oil-gas ratio,
The burning energy supply of fuel oil is also maximum, at this time gas turbine rotary speed highest.
As a result, after closing trigger valve 153, it can be burnt in other words to participation to recirculating oil quantity by adjusting micro-control valve 152
Amount of fuel be adjusted, to obtain required revolving speed, tail spray temperature, extraction flow etc..For example, with micro-control valve is adjusted
152 aperture and be allowed to increase, then recirculating oil quantity increase, thus turned down participate in burning amount of fuel, thus gas turbine turn
Speed reduces.
As it can be seen that the spirit that the operating condition of gas turbine is adjusted can be further increased by setting micro-control valve 152
Activity.
It further include lubricating system 170 in gas turbine engine systems 100, for bearing, the electricity on such as gas turbine main shaft
The components such as the bearing of arbor provide lubricating oil.The lubricating system may include grease pump, for pumping lubricating oil to bearing, may be used also
Including scavenge oil pump, for recycling lubricating oil from gas turbine.
Enlightening motor 111 is set in gas turbine engine systems 100, the output shaft of the inspiration motor 111 and gas turbine
Main shaft is connected.The inspiration motor 111 can switch between electric motor mode and generator mode.When starting gas turbine,
It inspires motor 111 to serve as motor, drives the main shaft of gas turbine, and after the revolving speed of gas turbine reaches certain revolving speed,
It inspires motor 111 by main shaft drives, is run with generator mode.
In the present invention, gas turbine engine systems 100 further include control system, for controlling the gas turbine engine systems
100 starting, operation and parking etc..The control system may include electronic control unit (ECU) 160, remote manipulator 161, store
Battery pack 180, motor-drive circuit 181, regulator rectifier circuit 182 etc..
Wherein, motor control loop is used to control the operation for inspiring motor 111.Specifically, as shown in Fig. 2, the motor
Control loop includes motor-drive circuit 181 and regulator rectifier circuit 182.Motor-drive circuit 181 uses square wave or sine wave
Mode is controlled starter/generator 111 and is run with electric motor mode.Preferably, motor 111 is inspired to pass through motor-drive circuit 181 and whole
Stream voltage regulator circuit 182 is connect with extraneous power supply or power grid.For example, in the illustrated example shown in fig. 2, motor 111 is inspired to pass through electricity
Drive circuit 181 and regulator rectifier circuit 182 are connected with battery group 190, so as to receive electric power from battery group 190
(electric motor mode) or (generator mode) is charged to battery group 190.
Specifically, motor-drive circuit 181 preferably senses the counter electromotive force for inspiring the machine winding of motor 111, uses
Make to inspire the location information judgment basis of motor 111, also, the characteristic that ECU160 is loaded according to the operation of gas turbine, setting
The acceleration time of 111 driving spindle of motor is inspired, as will be described in detail below, and to motor-drive circuit 181
Power tube characteristic be adaptively adjusted.By this series of setting, motor-drive circuit 181 can be realized gas turbine
Smooth starting under the drive for inspiring motor 111.
After gas turbine reaches certain revolving speed, ECU160 control inspires motor 111 to enter generator operational mode.This
When, regulator rectifier circuit 182 connects rectifier bridge and inspires the route of motor 111, will inspire motor by voltage regulator circuit therein
111 electric power issued are changed into stable DC source, such as by the electrical power stabilization for inspiring motor 111 to issue in 28V or so, should
Electric power can charge to battery group 190, while can also meet the operation power demand of entire gas turbine engine systems 100, such as fire
The power demand of oil pump 151, mist oil pump 141, each control circuit etc..
Fig. 3 shows a kind of preferable structure of the inspiration motor 111 of the utility model.As shown in figure 3, the motor 111
With stator 112 and rotor 113.Wherein, stator 112 includes stator core (being preferably made of silicon steel sheet), in stator iron
Coil is wound on core, to form stator winding.Rotor 113 then includes at least one, preferably a plurality of magnet (such as permanent magnetism
Body), and rotor 113 is mounted on the machine shaft 114 of motor 111.
As shown in figure 3, rotor 113, specifically form rotor 113 each magnet be arranged in the one of machine shaft 114
Near end, and at least one bearing 115 is then set near the other end of machine shaft 114, preferably as shown in Figure 3 two
A bearing 115 being spaced from.Machine shaft 114 and the rotor of 114 adjacent one end of machine shaft is set as a result,
113 are supported in cantilever fashion.
Further, electronic control unit (ECU) 160 is additionally provided in gas turbine engine systems 100, which uses
In the operation of all parts of control gas turbine engine systems 100, and preferably, ECU 160 can also have both signal acquisition, logic control
The functions such as system, signal output.For example, ECU 160 can acquire the revolving speed of gas turbine main shaft, in lubricating system lubricating oil pressure
The signals such as the supply voltage that power, Xiang Qidong motor 111 are powered.In addition, ECU 160, which also can receive, comes from such as remote manipulator
161 control signal etc..Based on these signals, ECU 160 controls each component in gas turbine engine systems 100, such as
Control lubricating oil system 170, fuel pump 151, mist oil pump 141, micro-control valve 152, trigger valve 153, igniter 131, motor driven
Circuit 181, regulator rectifier circuit 182 etc..
Specifically, corresponding sensor is set at the component that ECU 160 to be controlled, with sensing and to ECU 160
Corresponding parameter signal is fed back, ECU 160 controls corresponding component based on these signals.For example, in rectifying and voltage-stabilizing
Voltage sensor (at " V " in Fig. 2) is set at circuit 182, which detects the voltage number after rectified pressure stabilizing
It is worth and sends ECU 160 to.For another example pressure sensor (at " Ph " in Fig. 2) is provided at lubricating oil system 170,
The pressure sensor senses the lubricating oil pressure in lubricating oil system 170, and sends the pressure to ECU 160.In addition, firing
Also settable speed probe (at " N " in Fig. 2, it is of course also possible to which rotor other positions are arranged in) on the main shaft of gas-turbine,
ECU 160 can obtain the revolving speed of main shaft according to the signal of speed probe, and control accordingly the operation of gas turbine, than
The operation for inspiring motor 111 or control fuel system are such as controlled to the fuel feeding of combustion chamber 130.
Additionally, also settable data monitoring and record system 162, for monitoring and recording received by ECU 160
Various signals.
The progress control method of the gas turbine engine systems 100 of the utility model is described in detail below.
In the booting preparation stage, extraneous power supply is connected first, such as connect the switch of battery group 190, to be ready to
Power supply is provided to electric control system.
In the booting preparation stage, preferably, can be adjusted according to the geographical location circumstances where the gas turbine engine systems 100
Save the aperture of micro-control valve 152.Geographical location circumstances herein refer to the height above sea level in location, atmospheric conditions etc..To micro-control
The adjusting of 152 aperture of valve can be to be carried out manually by operator, can also be carried out automatically according to preset program.
When gas turbine engine systems 100 receive start command, is inspiring motor 111 to open, driving the master of gas turbine
Axis rotation.In the case where 152 aperture of micro-control valve is automatic adjustment, the aperture of micro-control valve 152 can also be incorporated into the starting
In order, thus open inspire motor 111 while or substantially concurrently set the aperture of micro-control valve 152.At this stage, exist
In a kind of specific preferable examples, start command is issued by remote manipulator 161, ECU 160 receives the start command,
And motor-drive circuit 181 is controlled, connect the power supply for inspiring motor 111, that is, in structure shown in the figure, start by electric power storage
Pond group 190 to inspiring motor 111 to provide electric power makes that motor 111 is inspired to run.Wherein, motor-drive circuit 181 is according to from ECU
160 instructions issued control the operation for inspiring motor 111.
In startup stage, still in compared with the slow-speed of revolution ignition condition is had not yet been reached, therefore fuel oil at this time in the main shaft of gas turbine
Pump 151 is in close state, and igniter 131 is also inactive.In other words, in this startup stage, only enlightening motor 111 drives combustion
The main shaft of gas-turbine rotates, and ramps up.In the process, the air stream sucked by compressor 110, in gas turbine
The oil accumulation or foreign matter of portion's remaining are purged, to provide better service condition for subsequent gas turbine operation.
Further, in startup stage, if being not up to ignition condition within the regular hour, ECU 160 will be controlled
Whole system parking, and cut off the power supply for inspiring motor 111.Thus, it is ensured that the safety of gas turbine engine systems.Specifically,
In the present invention, the first predetermined time, such as 10~30s, preferably 20s are set, starts to open when in inspiration motor 111
After dynamic when first predetermined time expires, the main shaft of gas turbine still not up to the first revolving speed (i.e. fire speed), is then opened
Move above-mentioned alarm parking procedure.
When gas turbine main shaft accelerates to the first revolving speed, ECU160 controls trigger valve 153 and opens, and fuel pump 151 starts
Operation conveys fuel oil to combustion chamber 130.At this point, 131 starting ignition of igniter, lights the combustion being transported in combustion chamber 130
Oil.High temperature caused by fuel burning, high-pressure gas flow into turbine 120, and turbine is pushed to accelerate.At this point, inspire motor 111 after
Reforwarding row, so that the compression impellor and turbine of gas turbine accelerate fortune in the case where inspiring the collective effect of motor 111 and high-temperature fuel gas
Row.Herein, the first revolving speed is, for example, 3500~4000rpm, preferably 3800rpm, or can also be according to different types of
Gas turbine or different operations and environmental condition and be varied.
After ignition, gas turbine accelerates.Wherein, the revolving speed of gas turbine by main shaft (that is, be connected in gas turbine
The revolving speed of compression impellor and turbine wheel) persistently increase, when the revolving speed of gas turbine reaches the second revolving speed, ECU 160 is controlled
Motor-drive circuit stops driving and inspires motor 111, and closes igniter 131.At this point, fuel pump 151 is constantly to combustion chamber
130 supply fuel oils, so that high temperature, high-pressure gas caused by fuel burning drive the continuation Accelerating running of gas turbine.
Herein, the second revolving speed may, for example, be 5500~8000rpm, preferably 7000rpm.
In order to make gas turbine accelerate to rated speed state, need to close trigger valve 153, in this way, in oil return pipe 156 only
Have where micro-control valve 152 this all the way pipeline for fuel flow returns into fuel tank 154.In this way, being supplied in combustion chamber 130
Amount of fuel significantly rises, and the revolving speed of gas turbine is enabled to be increased to rated speed.
Preferably, a warm-up period can also be added before gas turbine is accelerated to rated speed.It is specific next
It says, after gas turbine accelerates to idling rating, trigger valve 153 is stayed open, and gas turbine continues to accelerate to third revolving speed,
Such as 12000~18000rpm, preferably 13000rpm can be accelerated to, then trigger valve 153 continues to stay open second in advance
It fixes time, such as stays open 5~20s, preferably 8s.Then, trigger valve 153 is turned off, gas turbine is accelerated into volume
Determine revolving speed.
When ECU160 detects that gas turbine is more than the operating status of the 4th revolving speed, control inspires motor 111 in combustion gas wheel
Machine is run under driving with generator mode.At this point, for example regulator rectifier circuit 182 is opened by ECU 160, to such as battery group
190 or external electrical network export direct current, which is, for example, 28V.In this way, motor 111 is inspired to charge battery group 190,
In addition, the electric power for inspiring motor 111 to issue can also be used to power to the control of gas turbine engine systems 100 and power line, such as
For the power supply such as mist oil pump 141, fuel pump 151.Wherein, in a kind of preferable situation, the 4th revolving speed is 20000rpm.
For the gas turbine engine systems 100 with smoking device 140, under specified operating status, it can also start hair
Cigarette device 140 provides smog with external environment.Specifically, after ECU 160 receives smoke signal, mist oil pump 141 is opened
It is dynamic, by mist oil from the jet pipe that mist fuel tank 142 is pumped into smoking device 140.In the jet pipe, mist oil with come from turbine
120 high-temperature fuel gas mixing, mixture are ejected the outlet of jet pipe, form smog.The smoke signal for example can be from long-range distant
Device 161 is controlled to issue to ECU 160.
The stopping signal of the sendings such as remote manipulator 161 is received as ECU 160, then ECU 160 cuts off fuel pump
151 power supply, at this point, there is no fuel supplies into combustion chamber 130, also just there is no high-temperature fuel gas generations.At this point, combustion gas wheel
Machine, specifically its compression impellor being connected on main shaft and turbine wheel gradually stop operating under inertia, until finally stopping
Only.
In addition, ECU 160 is also to lubricating oil during running gas turbine engine systems 100 in method as described above
System 170 is controlled, and lubricating oil is supplied to the corresponding component of gas turbine engine systems 100, to ensure gas turbine engine systems 100
It safely and steadily runs.Wherein, as already mentioned above, ECU 160 is received in relation to the lubrication pressure in lubricating oil system 170
Force signal, to control lubricating oil system 170.
It in above method, is described for the sending of remote manipulator 161 by relevant control signal, these controls
Signal processed can also be issued otherwise to ECU 160.For example, control can also be integrated in data monitoring and record system 162
Sender unit processed.Alternatively, various control signals can also be issued from host service function panel by operator.
Further, in the present invention, in such as ECU 160, data monitoring and record system 162, motor driven
Can be added in the control device of circuit 181, regulator rectifier circuit 182 etc. for start failure detection protection, lubricating oil pressure it is low
The program of protection, supply voltage minimum living shield, running speed abnormal protection, anti-surge/resonance protection etc, thereby further ensures that
Steady and safe starting, operation and the shutdown of gas turbine, especially miniature gas turbine.
Claims (6)
1. a kind of gas turbine engine systems, the gas turbine engine systems include:
Gas turbine, the gas turbine include compressor, turbine and the combustion chamber between compressor and turbine, the pressure
The turbine wheel of the compression impellor of mechanism of qi and the turbine is linked together by main shaft, is provided with igniting in the combustion chamber
Device has jet pipe in the downstream connection of the turbine；
Fuel system, the fuel system are connect with the combustion chamber, to supply fuel oil to the combustion chamber；
It is characterized in that, the gas turbine engine systems further include:
Motor is inspired, the output shaft for inspiring motor is connected with the main shaft, and can run with electric motor mode, is opening
The main axis is driven when moving the gas turbine；And
Motor control loop, the inspiration motor are connected to power supply through the motor control loop, wherein the motor control is returned
Road includes motor-drive circuit, and the motor-drive circuit controls institute when the inspiration motor is run with the electric motor mode
State the operation for inspiring motor；
Electronic control unit, the electronic control unit control the motor control loop, and then control the inspiration motor
Operation.
2. gas turbine engine systems as described in claim 1, which is characterized in that the motor-drive circuit is configured to acquisition institute
The counter electromotive force for inspiring the machine winding of motor is stated, as to the control parameter for inspiring motor.
3. gas turbine engine systems as described in claim 1, which is characterized in that the inspiration motor can also be with generator mode
Operation, and, the motor control loop further includes regulator rectifier circuit, wherein under the generator mode, the rectification
The electricity that the inspiration motor issues is changed into the direct current of burning voltage by voltage regulator circuit.
4. gas turbine engine systems as described in claim 1, which is characterized in that the fuel system includes:
Fuel tank,
Fuel feed pump, the fuel feed pump are connected between the fuel tank and the combustion chamber, and combustion is provided on the fuel feed pump
Oil pump, the fuel pump is for fuel oil to be pumped into the combustion chamber from the fuel tank；And
Oil return pipe, the oil return pipe are connected between the fuel tank and the combustion chamber, and are provided on the oil return pipe
Trigger valve,
Wherein, the electronic control unit can control at least one of the fuel pump and the trigger valve.
5. gas turbine engine systems as claimed in claim 4, which is characterized in that be additionally provided with micro-control valve, institute on the oil return pipe
Micro-control valve is stated to be arranged in parallel with the trigger valve.
6. gas turbine engine systems as described in claim 1, which is characterized in that the gas turbine engine systems further comprise:
Smoking device, the smoking device include: at least one mist oil burner nozzle, and the mist oil burner nozzle is arranged in the jet pipe
On；Mist fuel tank accommodates the mist oil for smoke in the mist fuel tank；And mist oil pump, the mist oil pump are connected to the mist
Between oil burner nozzle and the mist fuel tank, so that mist oil is sprayed into the jet pipe via the mist oil burner nozzle；And/or
Lubricating system, the lubricating system provide lubricating oil to the gas turbine；
Wherein, the electronic control unit can control the lubrication pressure in the mist oil pump and/or the acquisition lubricating system
Power simultaneously controls the lubricating system based on the lubricating oil pressure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821506887.1U CN209053695U (en) | 2018-09-14 | 2018-09-14 | Gas turbine engine systems |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821506887.1U CN209053695U (en) | 2018-09-14 | 2018-09-14 | Gas turbine engine systems |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209053695U true CN209053695U (en) | 2019-07-02 |
Family
ID=67048931
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821506887.1U Active CN209053695U (en) | 2018-09-14 | 2018-09-14 | Gas turbine engine systems |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209053695U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109026389A (en) * | 2018-09-14 | 2018-12-18 | 青岛云深动力科技有限公司 | Gas turbine engine systems and its control method |
| CN114508424A (en) * | 2020-11-17 | 2022-05-17 | 本田技研工业株式会社 | Internal combustion engine for aircraft |
-
2018
- 2018-09-14 CN CN201821506887.1U patent/CN209053695U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109026389A (en) * | 2018-09-14 | 2018-12-18 | 青岛云深动力科技有限公司 | Gas turbine engine systems and its control method |
| CN114508424A (en) * | 2020-11-17 | 2022-05-17 | 本田技研工业株式会社 | Internal combustion engine for aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2985901B1 (en) | Hybrid electric pulsed-power propulsion system for aircraft | |
| CN106460662B (en) | For the method for auxiliary turbine shaft generator and the framework of helicopter propulsion system | |
| EP3228544A1 (en) | Hybrid electric aircraft propulsion incorporating a recuperated prime mover | |
| US6244034B1 (en) | Compressor bleed pressure storage for controlled fuel nozzle purging of a turbine power generating system | |
| CN109026389A (en) | Gas turbine engine systems and its control method | |
| CN110388269A (en) | Pressure charging system for aircraft engine | |
| CN102224074A (en) | Powerplant and related control system and method | |
| CN209053695U (en) | Gas turbine engine systems | |
| CN109421927A (en) | VTOL machine | |
| EP3073122A1 (en) | Variable inlet guide vane scheduling, aero gas turbine engine with compressor and method using the same | |
| JP2004132359A (en) | Assistance and urgent drive mechanism for motor accessory | |
| SU1087085A3 (en) | Device for supercharging internal combustion engine | |
| CN116163838A (en) | Gas supply system | |
| EP2613018A2 (en) | Method for meeting a purge flow requirement for a power plant and a power plant having a purge control system | |
| CN110863900B (en) | High altitude internal combustion engine/turbocharger exhaust gas combustion chamber | |
| US20200378302A1 (en) | Advanced 2-spool turboprop engine | |
| RU2374472C1 (en) | Method and device to start gas turbine plant | |
| CN102588143A (en) | Minitype turbofan engine | |
| CN202348475U (en) | Micro-turbofan engine | |
| CN115853666A (en) | Turbine engine with variable pitch fan | |
| CN211174361U (en) | Starting and launching integrated system for micro turbojet engine | |
| CN108397238A (en) | A kind of missile turbojet engine fast starting structure | |
| CN101629517A (en) | Jet propulsion method and jet engine | |
| RU75222U1 (en) | DEVICE FOR STARTING A GAS-TURBINE UNIT | |
| CN109763897B (en) | Aircraft auxiliary power generation mechanism based on metal nano powder combustion |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210622 Address after: 261500 No.1, hengsan Road, east of Kangcheng street and Jiaohe Avenue, Gaomi Economic Development Zone, Weifang City, Shandong Province Patentee after: Shandong Xinyue Machinery Co.,Ltd. Address before: No.233, Jiaozhou West Road, zhongyun sub district office, Jiaozhou City, Qingdao City, Shandong Province 266300 Patentee before: QINGDAO YUNSHEN POWER TECHNOLOGY Co.,Ltd. |
|
| TR01 | Transfer of patent right |