CN106640379A - Starting and oil-supply system of micro turbine engine and starting and oil-supply method thereof - Google Patents
Starting and oil-supply system of micro turbine engine and starting and oil-supply method thereof Download PDFInfo
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- CN106640379A CN106640379A CN201610903139.6A CN201610903139A CN106640379A CN 106640379 A CN106640379 A CN 106640379A CN 201610903139 A CN201610903139 A CN 201610903139A CN 106640379 A CN106640379 A CN 106640379A
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- oil
- fuel
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- engine
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Classifications
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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
-
- 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
- F02C7/06—Arrangements of bearings; Lubricating
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
- F02C7/266—Electric
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/48—Control of fuel supply conjointly with another control of the plant
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/85—Starting
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/99—Ignition, e.g. ignition by warming up of fuel or oxidizer in a resonant acoustic cavity
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
The invention relates to the field of engine control, in particular to a starting and oil-supply system of a micro turbine engine and a starting and oil-supply method thereof. The stating and oil-supply method comprises the steps that a battery supplies power to a receiver through an electronic speed controller, the receiver receives signals of a transmitter, controls an igniter and sends signals to the electronic speed controller, and the electronic speed controller controls starting of the motor and the rotating speed of an oil pump; a fuel tank is connected with the oil pump, an oil filter and a flow distributor in sequence, two outlets of the flow distributor are connected with a lubricating oil pipeline and a fuel pipe correspondingly, and the lubricating oil pipeline is connected with a lubricating oil inlet of the turbine engine; the fuel pipe is connected with a fuel valve, a tee joint and a fuel inlet of the turbine engine in sequence; and the tee joint is further connected with a butane gas bottle through a butane gas valve. The starting and oil-supply system is simple, easy to operate, simple in structure and low in cost, can realize the basic control over the thrust of the micro turbine engine and is applicable to the initial test run of the engine and the starting control process of the micro turbojet engine for a model airplane.
Description
Technical field
The present invention relates to the starting of the control field of engine, specially Micro Turbine Jet Engine and oil supply system and its open
Dynamic and fuel supply method.
Background technology
Miniature whirlpool eruption dynamic (Micro Turbine Engine, MTE) is one kind of jet engine, and miniature whirlpool eruption is dynamic
With the features such as structure is relatively easy, small volume, thrust are big, speed-altitude performance is good, it is widely used in aerospace field.
Mechanical-hydraulic controller being adopted the turbojet engine of early stage, its reliability control system is higher, but precision is relatively low, controllable more
Parameter is few.With the continuous progress of aircraft technology, requirements at the higher level are proposed to engine control level, occur in that digital and electronic control
System processed, control accuracy is high, and reaction speed is fast, and engine can be control effectively in various complex work environment,
It is widely used in jumbo jet engine, miniature whirlpool spray also has and much adopt this controller, but the cost of this controller
It is higher.And model plane Micro Turbine Jet Engine, belonging to running stores, life cycle is short, and working condition is relatively single, is substantially and regards
Away from interior flight, relatively simple control system can be adopted.
One of prior art related to the present invention, control system part ECU1 is core, by controlling propane air valve, combustion
Oil pump, start gas tank air valve, start motor and ignition electric nozzle, realize turbojet engine start, accelerate, slowing down, etc. each mistake
The control of journey, while the parameter such as ECU monitoring engine speed, delivery temperature, makes control more accurate.This invention to whirlpool by spraying
Each state of engine adopts different control methods, makes control more accurate, and reaction much sooner, is erupted so as to widen whirlpool
The working range of motivation, improves the adaptive capacity to environment and reliability of turbojet engine.
The advantage of this controller is that control is accurate reliable, and can provide certain safeguard protection to engine.But
Have the disadvantage that control system is complicated, weight is big, and relatively costly, it is difficult to using so complicated control system on model plane.From into
In the market the price of a common ECU control unit does not include this controller between 600-1000 is first, also for this
The sensors such as rotating speed, the pressure and temperature to be used.It is relatively costly for model plane Micro Turbine Jet Engine.
The content of the invention
For above-mentioned technical problem, the present invention provides a kind of starting oil supply system simple to operation, simple structure, cost
It is cheap, it is adapted to the control of engine initial bench test drive and model plane Micro Turbine Jet Engine.
Concrete technical scheme is：
The starting of Micro Turbine Jet Engine and oil supply system, including fuel tank, igniter, also including flow distributor, combustion
Oil pipe line, lubricating pipe, electricity are adjusted, receiver；
Described receiver adjusts power supply, the signal of receiver receiver/transmitter, receiver and igniter by battery by electricity
Connection, controls igniter, and igniter is connected with the ignition electric nozzle of turbojet engine；
Described receiver adjusts signal, electricity to stealthily substitute and include two speed regulators to electricity, is connected with starting motor, oil pump respectively, controls
System starts the rotating speed of motor and oil pump；
Described fuel tank is sequentially connected oil pump, oil filter, flow distributor, and two outlets of flow distributor connect respectively
Lubricating pipe, fuel pipe, described lubricating pipe is connected with the lubricating oil inlet of turbojet engine；Described fuel pipe
Road is sequentially connected the fuel filler of fuel valve, three-way connection, turbojet engine；
Described three-way connection also connects butane gas cylinder by butane air valve.
Wherein, current limiter is also connected with described fuel pipe, installed in fuel valve upstream.
Described flow distributor is the Y-piece of bifurcated at one end, and bifurcated goes out two outlets.
The starting of the Micro Turbine Jet Engine and the startup of oil supply system and fuel supply method, including procedure below：
During starting, butane air valve is first shut off, closes fuel valve, open oil pump, connected 8～12 seconds；
It is then turn on starting motor, drives the operating of turbojet engine rotor, now starts motor and slowly run；
Butane air valve is gradually opened simultaneously, and control igniter is lighted a fire by ignition electric nozzle, until lighting a fire successfully, preheating 20
Second；
After preheating terminates, fuel valve is opened, after fuel oil is ignited, close butane air valve, while control oil pump accelerates,
Start motor to accelerate, close during close slow train rotating speed and start motor, stable slow train is reached by oil pump control turbojet engine and is turned
Speed.Fuel oil is ignited having sound, and jet pipe has of short duration " flame " appearance, obvious；Slow train rotating speed is typically at 30000 turns
Left and right (the generally 20%-35% of maximum (top) speed).
The starting of the Micro Turbine Jet Engine that the present invention is provided and oil supply system and its startup and fuel supply method, simple easily behaviour
Make, simple structure is with low cost, be capable of achieving the basic control to Micro Turbine Jet Engine thrust, be suitable for engine initial
Test run and model plane Micro Turbine Jet Engine starting control process.
The starting of the Micro Turbine Jet Engine that the present invention is provided and oil supply system and its startup and fuel supply method, for model plane
With the starting fuel feeding and control system of Micro Turbine Jet Engine.More existing technology is compared, control system of the present invention is not required to charge
The expensive engine controller ECU of lattice and corresponding sensor, can equally realize remote start(ing), fuel feeding and the control of engine
System, this system architecture is relatively easy, and cost is relatively low.Meanwhile, this system can also realize engine big by simple mechanism
The fuel oil of power rating and the regulation and control of lubricating oil, to engine certain safeguard protection is carried out.
Description of the drawings
Fig. 1 is the structural representation of the present invention；
Fig. 2 is the flow distributor structural representation of the present invention.
Specific embodiment
The specific embodiment of the present invention is described with reference to the drawings.
As shown in figure 1, the starting of Micro Turbine Jet Engine and oil supply system, including fuel tank 20, igniter 5, also include
Flow distributor 15, fuel pipe 14, lubricating pipe 16, electricity adjust 3, receiver 4；
Described receiver 4 adjusts 3 power supplies, the signal of the receiver/transmitter of receiver 4, receiver 4 and point by battery 2 by electricity
Firearm 5 connects, and controls igniter 5, and igniter 5 is connected with the ignition electric nozzle 6 of turbojet engine 1；
Described receiver 4 adjusts 3 signals, electricity to adjust 3 to include two speed regulators to electric, connects with starting motor 8, oil pump 19 respectively
Connect, control starts the rotating speed of motor 8 and oil pump 19；
Described fuel tank 20 is sequentially connected oil pump 19, oil filter 18, flow distributor 15, and two of flow distributor 15 go out
Mouth connects respectively lubricating pipe 16, fuel pipe 14, the lubricating oil inlet of described lubricating pipe 16 and turbojet engine 1
17 connections；Described fuel pipe 14 is sequentially connected the fuel filler 7 of fuel valve 12, three-way connection 9, turbojet engine 1；
Described three-way connection 9 also connects butane gas cylinder 11 by butane air valve 10.
Wherein, current limiter 13 is also connected with described fuel pipe 14, installed in the upstream of fuel valve 12.
Battery 2 adjusts 3 to power to receiver 4 by electricity, the signal that receiver 4 passes through receiver/transmitter, and the eruption of control whirlpool is dynamic
The igniter 5 of machine 1；Simultaneously receiver 4 adjusts 3 signals to electricity, adjusts 3 controls to start the rotating speed of motor 8 and oil pump 19 by electricity.This is
The electricity of system adjusts 3 to be made up of two speed regulators, the little rotating speed of tune oil pump 19, and big tune starts the rotating speed of motor 8.The butane air valve 10
Control butane gas cylinder 11 is supplied by three-way connection 9 to the fuel filler 7 of turbojet engine 1.The oil pump 19 is from fuel tank 20
Oil pumping, by oil filter 18, then through flow distributor 15, by fuel oil two-way is divided into, and lubricating oil is become all the way by lubricating oil pipe
Road 16 provides the bearing of oil lubrication engine to the lubricating oil inlet 17 of turbojet engine 1；Fuel pipe is led up in addition
14th, current limiter 13, then pass through three-way connection 9 after fuel valve 12 to the fuel feeding of fuel filler 7.
The butane air valve 10 controls the break-make of butagas.The butane gas tank 11 stores butagas, for turbojet engine 1
Use during starting.The fuel tank 20 stores the miscella of 95% aviation kerosine and 5% lubricating oil, works for turbojet engine 1
When burning and lubrication use.The fuel valve 12 controls the break-make of aviation kerosine.Start when motor 8 is started and drive engine rotor
Rotation, so that turbojet engine 1 obtains initial kinetic energy.The oil pump 19 be gear motor pump, by control its rotating speed come
The distributive value of control turbojet engine 1, so as to realize that the rotating speed to turbojet engine 1 is controlled.The turbojet engine 1 is whole
The control object of control system.
Actual operating process is as follows：
During starting, butane air valve 10 is first shut off, closes fuel valve 12, open oil pump 19, connected 10 seconds or so, allow eruption
The axle of motivation 1 and bearing have lubricating oil, and now fuel oil is flow through after flow distributor 15, because fuel valve 12 is closed, can only enter profit
Lubrication duct 16, then enter turbojet engine 1, lubrication bearing and axle from lubricating oil inlet 17.It is then turn on starting motor 8, band
The rotor of dynamic turbojet engine 1 operates, and now starts motor 8 and maintains Half Speed, and rotating speed is not too big, while being gradually opened butane air valve
10, control igniter 5 is lighted a fire by ignition electric nozzle 6, until lighting a fire successfully, is preheated 20 seconds or so.Ignition electric nozzle 6 is generally using warm
Duration and degree of heating type sparking plug, matching igniter 5 is also showing tremendous enthusiasm head dummy igniter, such as RCD3007 types igniter.This igniter leads to
Often can be with remote control ignition, also manually controllable igniting.Model plane Micro Turbine Jet Engine generally using backflow toroidal combustion chamber, is steamed
Tube nozzle is sent out, can be by fuel gasification under this nozzle high-temperature condition, and air is well mixed, effect is good, but cryogenic effect
It is bad, so starting process needs preheating.After preheating terminates, fuel valve 12 is opened, after fuel oil is ignited, close butagas
Valve 10, while control oil pump 19 accelerates, starts motor 8 and accelerates, and closes during close slow train rotating speed and starts motor 8, is controlled by oil pump 19
Turbojet engine processed 1 reaches stable slow train rotating speed.
Micro Turbine Jet Engine is due to small volume, and structure is relatively easy, without special oil system and lubricating oil, relies on
Fuel oil lubricates.Fuel-viscosity variation is little, and lubricant effect is bad, and oil viscosity is big, is unfavorable for spray burning.In order to take into account burning and moisten
Sliding, lubricating oil and the miscella of 95% aviation kerosine composition of this design using 5% is taken into account burning and is lubricated, this kind of ratio
The miscella of example is all proved that effect is preferable in relevant document.The work(of the oil feeding line part flow distributor 15 of said system
Can, the fuel oil from oil pump out is exactly divided into the flow proportional of two-way, a lubricating oil road, a fuel oil road, lubricating oil and fuel oil
Substantially 1:10 to 1:9, the lubricant effect and combustion economization of actual test this proportion is preferable.Flow distributor 15 is
Individual purely mechanic part, can be realized, as shown in Figure 2 with the structure similar to Y-piece.The aperture of fuel pipe 14 is lubricating pipe
9 or 10 times of 16 apertures, you can reach the function of distribution fuel oil and lubricating oil.
The effect of current limiter 13 is to limit from fuel filler 7 maximum stream flow for flowing into turbojet engine 1, prevents whirlpool eruption dynamic
The rotating speed of machine 1 is excessive, and temperature is too high.After fuel flow reaches permission maximum, current limiter 13 enters one by prevention fuel flow
Step rises, simultaneously because the metering function of current limiter 13, the allocation proportion of upstream flowrate distributor 15 will change, oil pump 9
Exporting more oil will increase the lubrication and radiating to engine rotor bearing and axle into the oil circuit of lubricating pipe 16, it is ensured that
The safe operation of turbojet engine 1.The current limliting size of current limiter 13 can be according to different Micro Turbine Jet Engines and same
The different working environment of motivation is adjusted, and is realized to fuel flow current limliting and the work for adjusting using parts such as precision flow regluating valves
With.Such as use in high temperature plateau place, turbojet engine performance can decline, it should which maximum fuel feeding is suitably reduced by current limiter
Amount, prevents engine overtemperature.
If starting motor 8 does not adopt electrically actuated, it is also possible to started with high-pressure air source.If ignition system does not adopt automatically controlled
Igniting, it is also possible to which, by outside burning things which may cause a fire disaster, such as lighter is lighted a fire in engine afterbody.Other parts identical also should be of the invention special
Sharp protection domain.
Claims (4)
1. the starting of Micro Turbine Jet Engine and oil supply system, including fuel tank (20), igniter (5), it is characterised in that also wrap
Include flow distributor (15), fuel pipe (14), lubricating pipe (16), electricity and adjust (3), receiver (4)；
Described receiver (4) adjusts (3) power supply, the signal of receiver (4) receiver/transmitter, receiver by battery (2) by electricity
(4) it is connected with igniter (5), control igniter (5), igniter (5) is connected with the ignition electric nozzle (6) of turbojet engine (1)；
Described receiver (4) adjusts (3) signal to electricity, and electricity adjusts (3) including two speed regulators, respectively with starting motor (8), oil pump
(19) connect, control starts the rotating speed of motor (8) and oil pump (19)；
Described fuel tank (20) is sequentially connected oil pump (19), oil filter (18), flow distributor (15), flow distributor (15)
Two outlets connect respectively lubricating pipe (16), fuel pipe (14), described lubricating pipe (16) and turbojet engine
(1) lubricating oil inlet (17) connection；Described fuel pipe (14) is sequentially connected fuel valve (12), three-way connection (9), whirlpool spray
The fuel filler (7) of engine (1)；
Described three-way connection (9) also connects butane gas cylinder (11) by butane air valve (10).
2. the starting of Micro Turbine Jet Engine according to claim 1 and oil supply system, it is characterised in that described fuel oil
Current limiter (13) is also connected with pipeline (14), installed in fuel valve (12) upstream.
3. the starting of Micro Turbine Jet Engine according to claim 1 and oil supply system, it is characterised in that described flow
Distributor (15) for bifurcated at one end Y-piece, bifurcated goes out two outlets.
4. the starting of the Micro Turbine Jet Engine according to any one of Claim 1-3 and the startup of oil supply system and fuel feeding
Method, it is characterised in that including procedure below：
During starting, butane air valve (10) is first shut off, closes fuel valve (12), open oil pump (19), connected 8～12 seconds；
It is then turn on starting motor (8), drives the operating of turbojet engine (1) rotor, now starts motor (8) and slowly run；
Butane air valve (10) is gradually opened simultaneously, and control igniter (5) is lighted a fire by ignition electric nozzle (6), until lighting a fire successfully, in advance
Heat 20 seconds；
After preheating terminates, fuel valve (12) is opened, after fuel oil is ignited, butane air valve (10) is closed, while control oil pump
(19) accelerate, start motor (8) and accelerate, close during close slow train rotating speed and start motor (8), it is dynamic by oil pump (19) control whirlpool eruption
Machine (1) reaches stable slow train rotating speed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610903139.6A CN106640379A (en) | 2016-10-17 | 2016-10-17 | Starting and oil-supply system of micro turbine engine and starting and oil-supply method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610903139.6A CN106640379A (en) | 2016-10-17 | 2016-10-17 | Starting and oil-supply system of micro turbine engine and starting and oil-supply method thereof |
Publications (1)
| Publication Number | Publication Date |
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| CN106640379A true CN106640379A (en) | 2017-05-10 |
Family
ID=58855860
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610903139.6A Pending CN106640379A (en) | 2016-10-17 | 2016-10-17 | Starting and oil-supply system of micro turbine engine and starting and oil-supply method thereof |
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Cited By (10)
| 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 |
| CN107965390A (en) * | 2017-12-18 | 2018-04-27 | 中科合肥微小型燃气轮机研究院有限责任公司 | A kind of gas turbine fuel distribution equipment and its control method |
| CN108825384A (en) * | 2018-08-27 | 2018-11-16 | 西北工业大学 | A kind of air-fuel mixture starter |
| CN110748420A (en) * | 2019-10-09 | 2020-02-04 | 上海交通大学 | Oil supply system of turbojet engine and accurate control method of rotating speed |
| CN111196380A (en) * | 2019-12-18 | 2020-05-26 | 中国民用航空飞行学院 | Method for eliminating slow-vehicle parking fault of airplane |
| CN111502832A (en) * | 2020-04-24 | 2020-08-07 | 中科航星科技有限公司 | Ground starting device of turbojet engine |
| CN112814788A (en) * | 2021-01-14 | 2021-05-18 | 南京航空航天大学 | Starting control system and method of micro turbine engine based on kerosene igniter |
| CN113074949A (en) * | 2021-04-02 | 2021-07-06 | 南京赛恩通航科技有限公司 | System and method for detecting parameters of miniature aviation turbojet engine |
| CN114235421A (en) * | 2021-12-06 | 2022-03-25 | 中国科学院工程热物理研究所 | Device and method for measuring maximum fuel flow limit line of turbojet engine |
| CN114687867A (en) * | 2022-03-14 | 2022-07-01 | 大连理工大学 | Micro turbojet engine control system and starting control method |
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Cited By (15)
| 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 |
| CN107965390A (en) * | 2017-12-18 | 2018-04-27 | 中科合肥微小型燃气轮机研究院有限责任公司 | A kind of gas turbine fuel distribution equipment and its control method |
| CN107965390B (en) * | 2017-12-18 | 2023-09-15 | 中科合肥微小型燃气轮机研究院有限责任公司 | Fuel distribution device of gas turbine and control method thereof |
| CN108825384A (en) * | 2018-08-27 | 2018-11-16 | 西北工业大学 | A kind of air-fuel mixture starter |
| CN110748420B (en) * | 2019-10-09 | 2021-03-19 | 上海交通大学 | Oil supply system of turbojet engine and accurate control method of rotating speed |
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