CN206092185U - Micro turbine engine starts and oil feeding system - Google Patents
Micro turbine engine starts and oil feeding system Download PDFInfo
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- CN206092185U CN206092185U CN201621125894.8U CN201621125894U CN206092185U CN 206092185 U CN206092185 U CN 206092185U CN 201621125894 U CN201621125894 U CN 201621125894U CN 206092185 U CN206092185 U CN 206092185U
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- fuel
- oil
- receiver
- electricity
- micro turbine
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Abstract
The utility model relates to a control field of engine specifically is micro turbine engine starts and oil feeding system, and the power supply is transferred by the battery through the electricity to the receiver, and the signal of transmitter is received to the receiver, and receiver control point firearm, receiver transfer the rotational speed of signal, electricity regulation and control system starter motor and oil pump for the electricity, the fuel tank connects gradually that oil pump, oil are strained, flow distributor, and lubricating pipe, fuel pipeline are connected respectively in two exports of flow distributor, and lubricating pipe and turbojet engine's lubricating oil inlet are connected, fuel pipeline connects gradually fuel valve, three way connection, turbojet engine's fuel inlet, three way connection still connects the butane gas cylinder through the butane pneumatic valve. This control system easily operates, simple structure, and low cost can realize the basic control to micro turbine engine thrust, is fit for being used for that the engine is initial takes a trial run and micro turbine engine's for the model aeroplane and model ship starting control process.
Description
Technical field
This utility model is related to the control field of electromotor, the specially starting of Micro Turbine Jet Engine and oil supply system.
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 electromotor control level, occur in that digital and electronic control
System processed, control accuracy is high, and response speed is fast, and electromotor can be control effectively in various complex work environment,
It is widely used in jumbo jet electromotor, 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 consumable goodss, 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 this utility model, control system part ECU1 is core, by controlling propane flammable gas
Valve, fuel pump, start gas tank air valve, start motor and ignition electric nozzle, realize turbojet engine start, accelerate, slowing down, etc. it is each
The control of individual process, while the parameter such as ECU monitoring engine speed, delivery temperature, makes control more accurate.This utility model is led to
Each state to turbojet engine is crossed using different control methods, makes control more accurate, reacted much sooner, so as to open up
The working range of wide turbojet engine, 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 electromotor.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.
Utility model content
For above-mentioned technical problem, this utility model provides a kind of starting oil supply system simple to operation, simple structure,
It is with low cost, it is adapted to the control of electromotor 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, lighter, 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 lighter by battery by electricity
Connection, controls lighter, and lighter 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 cock, turbojet engine；
Described three way cock 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 lighter 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.
The starting of the Micro Turbine Jet Engine that this utility model is provided and oil supply system, simple to operation, simple structure, into
This is cheap, is capable of achieving the basic control to Micro Turbine Jet Engine thrust, is suitable for the initial test run of electromotor and model plane are used
The starting control process of Micro Turbine Jet Engine.
The starting of the Micro Turbine Jet Engine that this utility model is provided and oil supply system, it is dynamic with the eruption of miniature whirlpool for model plane
The starting fuel feeding of machine and control system.More existing technology is compared, this utility model control system does not need expensive
Motivation controller ECU and corresponding sensor, can equally realize remote start(ing), fuel feeding and the control of electromotor, this system
Structure is relatively easy, and cost is relatively low.Meanwhile, this system can also realize electromotor in high-power state by simple mechanism
The regulation and control of fuel oil and lubricating oil, to electromotor certain safeguard protection is carried out.
Description of the drawings
Fig. 1 is structural representation of the present utility model；
Fig. 2 is flow distributor structural representation of the present utility model.
Specific embodiment
Specific embodiment of the present utility model 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, lighter 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 lighter 5, and lighter 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 cock 9, turbojet engine 1；
Described three way cock 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 lighter 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 cock 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 electromotor 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 cock 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% aerial kerosene and 5% lubricating oil, works for turbojet engine 1
When burning and lubrication use.The fuel valve 12 controls the break-make of aerial kerosene.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 lighter 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 lighter 5 is also showing tremendous enthusiasm head dummy lighter, such as RCD3007 types lighter.This lighter 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, meeting is by fuel gasification under this nozzle high-temperature condition, and air mix homogeneously, and 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% aerial kerosene 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 allotter 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 electromotor 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 electromotor afterbody.
Claims (3)
1. the starting of Micro Turbine Jet Engine and oil supply system, including fuel tank (20), lighter (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 lighter (5), control lighter (5), lighter (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 cock (9), whirlpool spray
The fuel filler (7) of electromotor (1)；
Described three way cock (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
Allotter (15) for bifurcated at one end Y-piece, bifurcated goes out two outlets.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621125894.8U CN206092185U (en) | 2016-10-17 | 2016-10-17 | Micro turbine engine starts and oil feeding system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621125894.8U CN206092185U (en) | 2016-10-17 | 2016-10-17 | Micro turbine engine starts and oil feeding system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206092185U true CN206092185U (en) | 2017-04-12 |
Family
ID=58483329
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621125894.8U Expired - Fee Related CN206092185U (en) | 2016-10-17 | 2016-10-17 | Micro turbine engine starts and oil feeding system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206092185U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106640379A (en) * | 2016-10-17 | 2017-05-10 | 中国民用航空飞行学院 | Starting and oil-supply system of micro turbine engine and starting and oil-supply method thereof |
| CN107842425A (en) * | 2017-09-15 | 2018-03-27 | 江西洪都航空工业集团有限责任公司 | A kind of engine starts oil supply system |
| CN108150823A (en) * | 2017-11-21 | 2018-06-12 | 北京动力机械研究所 | Aircraft starts the long-term storage method of fuel oil with fanjet |
| CN109736953A (en) * | 2018-12-13 | 2019-05-10 | 西安航天动力研究所 | The multiple starting liquid oxygen kerosene engine of gas-powered precompressed turbine and starting method |
| CN110714837A (en) * | 2019-11-06 | 2020-01-21 | 四川航天中天动力装备有限责任公司 | Turbojet engine lubricating oil system |
| CN111502832A (en) * | 2020-04-24 | 2020-08-07 | 中科航星科技有限公司 | Ground starting device of turbojet engine |
-
2016
- 2016-10-17 CN CN201621125894.8U patent/CN206092185U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106640379A (en) * | 2016-10-17 | 2017-05-10 | 中国民用航空飞行学院 | Starting and oil-supply system of micro turbine engine and starting and oil-supply method thereof |
| CN107842425A (en) * | 2017-09-15 | 2018-03-27 | 江西洪都航空工业集团有限责任公司 | A kind of engine starts oil supply system |
| CN108150823A (en) * | 2017-11-21 | 2018-06-12 | 北京动力机械研究所 | Aircraft starts the long-term storage method of fuel oil with fanjet |
| CN108150823B (en) * | 2017-11-21 | 2019-11-15 | 北京动力机械研究所 | Aircraft starts the long-term storage method of fuel oil with fanjet |
| CN109736953A (en) * | 2018-12-13 | 2019-05-10 | 西安航天动力研究所 | The multiple starting liquid oxygen kerosene engine of gas-powered precompressed turbine and starting method |
| CN110714837A (en) * | 2019-11-06 | 2020-01-21 | 四川航天中天动力装备有限责任公司 | Turbojet engine lubricating oil system |
| CN111502832A (en) * | 2020-04-24 | 2020-08-07 | 中科航星科技有限公司 | Ground starting device of turbojet engine |
| CN111502832B (en) * | 2020-04-24 | 2021-08-10 | 中科航星科技有限公司 | Ground starting device of turbojet engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170412 Termination date: 20191017 |