CN109441643A - Micro turbojet engine and gas-turbine combustion chamber igniter - Google Patents
Micro turbojet engine and gas-turbine combustion chamber igniter Download PDFInfo
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- CN109441643A CN109441643A CN201811127508.2A CN201811127508A CN109441643A CN 109441643 A CN109441643 A CN 109441643A CN 201811127508 A CN201811127508 A CN 201811127508A CN 109441643 A CN109441643 A CN 109441643A
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- kerosene
- hole
- oil
- burning
- nozzle
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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
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
Abstract
The present invention discloses a kind of micro turbojet engine and gas-turbine combustion chamber igniter, is made of kerosene nozzle, kerosene chamber seat, fastening nut, oil inlet pipe, heating core；It is installed on engine housing entirely through airscoop shroud.There are 6 air inlets on airscoop shroud cylindrical surface, and air can enter igniter combustion zone by air inlet and kerosene blends.Kerosene nozzle is equipped with pre-burning hole and main oil-hole, and kerosene can be sprayed by pre-burning hole and main oil-hole respectively, realizes the stratified combustion of kerosene.Heating core uses silicon nitride ceramics glow plug, and power is big.Air enters seed region by airscoop shroud, and kerosene enters kerosene chamber seat from oil inlet pipe, divides two-way to spray from pre-burning hole and main oil-hole through kerosene nozzle.Nearby oil pump capacity is less and has the lower preignition zone of air velocity in pre-burning hole, preignition zone presence stablizes burned flame and can help to light the kerosene of main oil-hole ejection in a wide range of operating conditions, to guarantee the work that igniter can be reliable and stable in wider condition range.
Description
Technical field
The invention belongs to micro turbojet engine and gas turbine field, it is related to lighting micro turbojet engine and combustion
The method of gas turbine combustion chamber and the igniter for implementing this method can be applied to micro turbojet engine and gas turbine combustion
The ignition process of combustion chamber.
Background technique
It is the micro turbojet engine of aviation fuel and gas turbine due to being limited by size, structure etc. using kerosene,
The structure of combustion chamber and fuel nozzle is relatively simple, without specially sparking and kerosene atomising device, therefore it is difficult to ensure that
Kerosene atomization quality in engine starting process, causes starting ignition and flame propagation more difficult.This is also many small
The reason of type turbojet engine and gas turbine do not light kerosene directly but use propane gas igniting, first will by spark plug
It sprays into indoor propane gas of burning to light, after engine reaches certain state, then sprays into kerosene and burn.This igniting
The advantages of mode is the state without the concern for startup stage fuel-oil atmozation, the disadvantage is that needing to increase ground or aerial auxiliary
Equipment makes troubles to micro turbojet engine or gas turbine use.
It is also a kind of sparking mode that igniting is carried out using the technology of Pneumatic resonance.Patent No. CN 101852680B is just retouched
A kind of experimental provision of Pneumatic resonance heating has been stated, and disclosed patent CN101852148A and CN1653254 then distinguish
Describe two kinds of igniters based on Pneumatic resonance technology.The major defect of this sparking mode: one side Pneumatic resonance skill
Art is not overripened also in the exploratory stage.Another aspect Pneumatic resonance need compressed gas as generate heat source working medium, because
This needs to be additionally provided compression gas tank, this greatly increases the cost of entire ignition system and volume weight.
In conclusion needing to design the igniter with special construction is micro turbojet engine and gas turbine
Starting provides reliable and stable igniting fire source, and requires the device that cannot bring the increase of additional equipment volume and weight.
Summary of the invention
It is a kind of suitable for lighting Micro Turbine Jet Engine and miniature gas turbine combustion chamber the task of the present invention is providing
Method and the igniter for implementing this method, they overcome the shortcomings of current technology and equipment.And it is characterized in making full use of a little
The stratified combustion structure of firearm generates the stabilization flame of large scale, and practicability is good, and function is reliable, while structure is simple.
Micro turbojet engine and gas-turbine combustion chamber igniter of the present invention, including coaxial nesting from the inside to the outside
Heating core, kerosene nozzle and kerosene chamber seat.
There is oil pocket between the kerosene chamber seat and kerosene nozzle；Between having between heating outer core and kerosene nozzle inner walls circumferential direction
Gap；Kerosene nozzle bottom is circumferentially provided with main oil-hole and pre-burning hole, and main oil-hole is connected to pre-burning Kong Junyu oil pocket；And make main oil-hole
Flow is greater than pre-burning hole flow.
Kerosene chamber seat bottom thread is connected with airscoop shroud；Airscoop shroud is mounted on the inside of engine housing.Airscoop shroud bottom week
To being equipped with air inlet, air inlet face kerosene nozzle bottom side wall.Oil inlet pipe is installed on kerosene chamber seat side wall, with oil pocket phase
It is logical.
Micro turbojet engine and gas-turbine combustion chamber ignition device method of the present invention are as follows:
1) blower outlet air reaches on kerosene nozzle near main oil-hole and pre-burning hole through the air inlet of airscoop shroud, waits
It is mixed with kerosene is sprayed in main oil-hole and pre-burning hole.
2) heating core power supply is connected, is powered to heating core, heating core heating time is for 10 seconds.
3) igniter oil circuit solenoid valve is opened, kerosene is controlled and enters oil pocket after oil inlet pipe, subsequent kerosene is first by pre-burning
Hole sprays, and is sprayed at the gasification of heating wicking surface, evaporation, and blend to form Kerosene/Air combustion mixture with surrounding air, and by
High temperature is lighted, and thermal-flame is generated, and is evaporated by the kerosene-gasifying that thermal-flame accelerates main oil-hole to spray, final main oil-hole sprays coal
Oil is formed the flame torch for spraying into combustion chamber by pre-burning hole flame ignition.
4) after micro turbojet engine or combustion turbine exhaustion temperature rise 50 DEG C, coil pipe oil circuit solenoid valve is opened,
Kerosene from micro turbojet engine or gas turbine fuel oil coil pipe enter combustion chamber be ignited device generate torch ignite.
5) when delivery temperature is greater than 250 DEG C, disconnect heating core power supply, while cut-out point kerosene road fuel feeding, kerosene all by
Fuel oil coil pipe oil circuit enters engine combustion.
The invention has the advantages that:
1, micro turbojet engine and gas-turbine combustion chamber igniter of the present invention is integrally set using oil spout and igniting
Meter, can be realized kerosene and directly lights.It is simple and reliable for structure, do not need additional pipeline and caisson.
2, micro turbojet engine and gas-turbine combustion chamber igniter of the present invention, airscoop shroud external cylindrical surface are machined with
6 air inlets, air are divided into two-way by each air inlet, and the kerosene sprayed all the way with preheating gate downwards blends, and form low speed
Combustion zone；Kerosene blending is sprayed with main oil-hole all the way to burn.
3, micro turbojet engine and gas-turbine combustion chamber igniter of the present invention, kerosene nozzle using it is main oil and
The double oil circuits structure of pre- fuel oil designs, flame separate propagating burning, ensure that burning stability and wide condition range.
4, micro turbojet engine and gas-turbine combustion chamber igniter of the present invention, the heating core power of middle use
Greatly, the lighting-off torch length of flame is long, can penetrate and light very well combustion mixture in combustion chamber, accelerates the indoor flame that burns
Diffusion velocity guarantees to stablize burning in entire combustion chamber.
5, micro turbojet engine and gas-turbine combustion chamber igniter of the present invention is realized using fastening nut and is lighted a fire
Device is installed on micro turbojet engine and gas turbine, is fixed, and structure is simple, installation, convenient disassembly.
6, micro turbojet engine and gas-turbine combustion chamber igniter of the present invention, is made of stainless steel, at low cost,
And there is good anti-breathing ability at high temperature, continuous hot environment work can be used for.
7, the method step for lighting combustion chamber of micro turbojet engine and gas-turbine combustion chamber igniter of the present invention
It is rapid clear, it is few and simple to execute structure, it is only necessary to control solenoid valve and heating core power switch.
Detailed description of the invention
Fig. 1 is micro turbojet engine of the present invention and gas-turbine combustion chamber ignition device structure cross-sectional view.
Fig. 2 is micro turbojet engine of the present invention and gas-turbine combustion chamber igniter air and kerosene route map.
Fig. 3 is the pre-burning flame using micro turbojet engine of the present invention and gas-turbine combustion chamber.
Fig. 4 is the actual working state using micro turbojet engine of the present invention and gas-turbine combustion chamber.
In figure:
1- kerosene nozzle -2- kerosene chamber seat 3- fastening nut
4- oil inlet pipe 5- heating core 6- oil pocket
7- connector 8- airscoop shroud 9- is installed on engine housing
10- air inlet 101- sidewall sections 102- barbed portion
103- main oil-hole 104- pre-burning hole
Specific embodiment
It is next with reference to the accompanying drawing that invention is further described in detail.
Micro turbojet engine and gas-turbine combustion chamber igniter of the present invention, including kerosene nozzle 1, kerosene chamber seat
2, fastening nut 3, oil inlet pipe 4 and heating core 5, as shown in Figure 1.
The kerosene nozzle 1, kerosene chamber seat 2, oil inlet pipe 4 and heating core 5 constitute oil circuit component.Wherein, heating core 5, coal
It is coaxial from the inside to the outside nested between 2 three of oil burner nozzle 1 and kerosene chamber seat.2 top of kerosene chamber seat and lower part design have contact platform
Shoulder, 1 top of contact shoulder and kerosene nozzle with contacted between the outer wall of middle part, and be circumferentially welded and fixed and to form integrated soldering member, make
Cavity is formed between kerosene chamber seat 2 and kerosene nozzle 1, as oil pocket 6.It is coaxially disposed between heating core 5 and kerosene nozzle 1, bottom end position
In 1 bottom of kerosene nozzle；And there is gap between 1 inner wall circumferential direction of 5 outer wall of heating core and kerosene nozzle, as burning gap.Heating
5 upper design of core has the connector 7 of integral structure, which passes through spiral shell in 2 top of lower external thread structure and kerosene chamber seat
Matching thread connects between line structure, and fits closely between 1 top end face of 7 bottom end end face of connector and kerosene nozzle, is achieved in
The fixation of heating core 5, while realizing the sealing between the top of burning gap.
Above-mentioned 1 bottom of kerosene nozzle is circumferentially all provided with there are four v notch v, and four v notch vs are along 1 bottom of kerosene nozzle
Axial design, and 1 bottom surface of kerosene nozzle is penetrated through, 1 bottom end of kerosene nozzle is circumferentially thus divided into four sidewall sections 101, with four
A barbed portion 102, as shown in Figure 2；Each sidewall sections bottom end opens up position as main oil-hole, opens up main oil-hole at the position
103；The top surface of two opposite barbed portions opens up position as pre-burning hole, and pre-burning hole 104 is opened up at the position；Then main oil-hole
103 open up position and pre-burning hole opens up position at totally eight, and uniformly distributed in 1 circumferential direction of kerosene nozzle, are arranged alternately.In each master in the present invention
Oilhole is related to a main oil-hole 103 at opening up, totally four main oil-holes 103；It is opened up at position in the pre-burning hole of two relative positions
A pre-burning hole 104 is opened up, totally two pre-burning holes 104；The flow of main oil-hole 103 is set to be greater than 104 flow of pre-burning hole.Kerosene simultaneously
It is provided with annular groove in the middle part of nozzle 1, the bottom surface of groove is equipped with six and goes out oil grooves 105 along kerosene nozzle is circumferential, in six
Four go out oil groove 105 be connected to respectively with four main oil-holes 103, another two goes out oil groove and is connected to two pre-burning holes 104.Above-mentioned ring
Connected in star can store kerosene, play the role of buffering, pressure stabilizing to injection pressure, reduce oil spout pulsation
Above-mentioned oil circuit component is installed on engine housing 9 by airscoop shroud 8, as shown in Figure 1.The airscoop shroud 8 is cylinder
Shape structure, top design have internal thread structure, and matching thread is connect between 2 bottom external thread structure of kerosene chamber seat, and between the two
The locating shoulder positioning circumferentially designed by 2 middle part outer wall of kerosene chamber seat.Airscoop shroud 8 is mounted on 9 inside of engine housing, into
8 middle and lower part of gas hood is machined with 2mm thickness hexagon end face, and engine or gas turbine inner surface of outer cover are close in end face, play sealing,
Fastening effect.Airscoop shroud 8 is threadedly coupled on the outside of engine housing by fastening nut and is fixed on the engine, and then is realized
Installation between oil circuit component and engine housing.8 bottom of airscoop shroud is circumferentially all provided with there are four air inlet 10, and four air inlets 10 divide
Other face kerosene nozzle 1 bottom four sidewall sections 101；And the distance of air inlet to 2 end face of kerosene chamber seat is greater than kerosene spray
The distance of 2 end face of kerosene chamber seat is arrived in pre-burning hole 104 on mouth 1.
The oil inlet pipe 4 is welded on the side wall of kerosene chamber seat 2, and the fuel feed hole opened up with 2 side of kerosene chamber seat communicates；It is logical
It crosses the fuel feed hole oil inlet pipe 4 and oil pocket 6 are connected.
When the micro turbojet engine of above structure and the igniter of gas-turbine combustion chamber work, such as Fig. 2 institute
Show, air by the air inlet 10 on 8 bottom of airscoop shroud with perpendicular to 1 axially direction of kerosene nozzle flow into airscoop shroud 8 in, then
Stopped to split into two parts by 1 bottom sidewall part 101 of kerosene nozzle, a part flows near pre-burning hole 104, and sprays in kerosene
Pre-burning hole 104 on mouth 1 is formed about low regime.Another part flows near main oil-hole 103.
Kerosene is flowed in oil pocket 6 by oil inlet pipe 4, and through going out oil groove 105 on oil pocket 6, flows into main oil-hole 103 and pre-burning
Hole 104, kerosene can first be sprayed by pre-burning hole 104, then be sprayed again by main oil-hole 103, be blended with surrounding air.
Heating core 5 can not only make the kerosene-gasifying of the ejection of pre-burning hole 104, evaporation in the present invention, and provide igniting hot source point
Preignition zone air/kerosene gaseous mixture is fired, also the kerosene for flowing through main oil-hole 103 is preheated, improves Cauldron igniting reliability.
Therefore, it is mixed in advance with the air of low regime from a small amount of kerosene that pre-burning hole 104 sprays, is heated rapid evaporation after core 5 heats
And burn, pre-burning flame is formed, as shown in Figure 3.Subsequent pre-burning flame preheats the kerosene for flowing through main oil-hole 103, after preheated
Kerosene sprayed by main oil-hole 103 after mix with the higher air of speed, and by pre-burning flame ignition, form stable torch,
As shown in Figure 4.
Under larger equivalent proportion operating condition, most of fuel oil is sprayed from main oil-hole 103 after the preheating of heating core 5, only
Small part fuel oil takes the lead in spraying from pre-burning hole 104, ensure that equivalent proportion is still in suitable range near pre-burning hole 104.In advance
Combustion hole sprays kerosene and is sprayed directly on heating wicking surface, after being blended with the air in low regime, makes kerosene Quick-gasifying, steams
It sends out and is ignited, form pre-burning flame, and combustion flame is surrounded by airscoop shroud inner cylinder face around pre-burning hole, guarantee combustion flame
Stablize.It then goes help to light the kerosene that main oil-hole 103 sprays by pre-burning flame, ensure that the reliability of rich oil part down-firing
And stability, the length of flame of lighting-off torch is increased, the propagation of burning interior flame is accelerated.
Under smaller equivalent proportion operating condition, a small amount of air is formed about stable low regime in pre-burning hole, guarantees pre-burning fire
The formation of flame, remaining more gas then directly flow away through the air inlet 10 on airscoop shroud 8, will not influence the pre-burning fire of preignition zone
The formation of flame, to guarantee the reliability and stability of oil-poor state down-firing.Therefore igniter of the present invention can be wider
It reliably lights a fire in ground condition range.
Part of the igniter of the present invention other than heating core 5 is all made of stainless steel material, each zero for needing to seal
Part is all made of welding structure, and air-tightness and bonding strength has been effectively ensured, and non-tight component ensure that entirety using being threadedly coupled
Structure it is simple and reliable.
The specific ignition method of micro turbojet engine and gas-turbine combustion chamber igniter of the present invention is as follows:
1) blower outlet air reaches main oil-hole 103 and pre-burning hole on kerosene nozzle 1 through the air inlet 10 of airscoop shroud 8
Near 104, waits and being mixed with ejection kerosene in main oil-hole 103 and pre-burning hole 104；
2) 5 power supply of heating core to be connected, is powered to heating core 5, the silicon nitride tungsten filament of heating core 5 generates hot high temperature,
Heating time is for 10 seconds；
3) igniter oil circuit solenoid valve is opened, appropriate kerosene is controlled and enters oil pocket 6 after oil inlet pipe 4, subsequent kerosene is first
It is sprayed by pre-burning hole 104, is sprayed at the gasification of 5 surface of heating core, evaporation, and blend with surrounding air that form Kerosene/Air flammable
Gaseous mixture, and lighted by high temperature, thermal-flame is generated, is evaporated by the kerosene-gasifying that thermal-flame accelerates main oil-hole 103 to spray, most
Whole main oil-hole 103 sprays kerosene and is formed the flame torch for spraying into combustion chamber by 104 flame ignition of pre-burning hole.
4) after micro turbojet engine or combustion turbine exhaustion temperature rise 50 DEG C, coil pipe oil circuit solenoid valve is opened,
A large amount of kerosene, which from micro turbojet engine or gas turbine fuel oil coil pipe enter combustion chamber and are ignited the torch that device generates, to be drawn
Combustion.
5) when delivery temperature is greater than 250 DEG C, it is believed that micro turbojet engine or gas turbine are lighted a fire successfully, and heating is disconnected
Core power supply, while cut-out point kerosene road fuel feeding, kerosene all enter engine combustion by fuel oil coil pipe oil circuit.
Claims (4)
1. micro turbojet engine and gas-turbine combustion chamber igniter, it is characterised in that: including coaxial from the inside to the outside embedding
The heating core of set, kerosene nozzle and kerosene chamber seat；
There is oil pocket between the kerosene chamber seat and kerosene nozzle；Heating has gap between outer core and kerosene nozzle inner walls circumferential direction；
Kerosene nozzle bottom is circumferentially provided with main oil-hole and pre-burning hole, and main oil-hole is connected to pre-burning Kong Junyu oil pocket；And make the stream of main oil-hole
Amount is greater than pre-burning hole flow；
Kerosene chamber seat bottom thread is connected with airscoop shroud；Airscoop shroud is mounted on the inside of engine housing；Airscoop shroud bottom is circumferentially equal
Equipped with air inlet, air inlet face kerosene nozzle bottom side wall；
Oil inlet pipe is installed on kerosene chamber seat side wall, is communicated with oil pocket.
2. micro turbojet engine as described in claim 1 and gas-turbine combustion chamber igniter, it is characterised in that: kerosene
There are alternate four barbed portions and four sidewall sections in nozzle bottom circumferential direction；Each sidewall sections bottom end is as main oil-hole
Open up position；The top surface of two opposite barbed portions opens up position as pre-burning hole.
3. micro turbojet engine as described in claim 1 and gas-turbine combustion chamber igniter, it is characterised in that: kerosene
Annular groove is provided in the middle part of nozzle, the bottom surface of groove is circumferentially equipped with out oil groove along kerosene nozzle, with main oil-hole and pre-burning
Hole connection.
4. micro turbojet engine as described in claim 1 and gas-turbine combustion chamber igniter, it is characterised in that: igniting
Method are as follows:
1) blower outlet air reaches on kerosene nozzle near main oil-hole and pre-burning hole through the air inlet of airscoop shroud, waits and main
Kerosene mixing is sprayed in oilhole and pre-burning hole；
2) heating core power supply is connected, is powered to heating core, heating core heating time is for 10 seconds；
3) igniter oil circuit solenoid valve is opened, kerosene is controlled and enters oil pocket after oil inlet pipe, subsequent kerosene is sprayed by pre-burning hole first
Out, it is sprayed at the gasification of heating wicking surface, evaporation, and blends to form Kerosene/Air combustion mixture with surrounding air, and by high temperature
It lights, generates thermal-flame, evaporated by the kerosene-gasifying that thermal-flame accelerates main oil-hole to spray, final main oil-hole sprays kerosene quilt
Pre-burning hole flame ignition forms the flame torch for spraying into combustion chamber；
4) after micro turbojet engine or combustion turbine exhaustion temperature rise 50 DEG C, coil pipe oil circuit solenoid valve, kerosene are opened
From micro turbojet engine or gas turbine fuel oil coil pipe enter combustion chamber be ignited device generate torch ignite；
5) when delivery temperature is greater than 250 DEG C, heating core power supply is disconnected, while cut-out point kerosene road fuel feeding, kerosene is all by fuel oil
Coil pipe oil circuit enters engine combustion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811127508.2A CN109441643B (en) | 2018-09-27 | 2018-09-27 | Micro-turbojet engine and ignition device for combustion chamber of gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811127508.2A CN109441643B (en) | 2018-09-27 | 2018-09-27 | Micro-turbojet engine and ignition device for combustion chamber of gas turbine |
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| Publication Number | Publication Date |
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| CN109441643A true CN109441643A (en) | 2019-03-08 |
| CN109441643B CN109441643B (en) | 2020-12-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201811127508.2A Active CN109441643B (en) | 2018-09-27 | 2018-09-27 | Micro-turbojet engine and ignition device for combustion chamber of gas turbine |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111779577A (en) * | 2020-06-30 | 2020-10-16 | 四川航天中天动力装备有限责任公司 | Afterburner ignition system |
| CN112539109A (en) * | 2020-11-25 | 2021-03-23 | 北京动力机械研究所 | High-altitude low-temperature reliable ignition structure of unmanned aerial vehicle |
| CN112761819A (en) * | 2021-01-15 | 2021-05-07 | 北京动力机械研究所 | Microminiature intelligent adjustable ignition system and adjusting method |
| CN113123882A (en) * | 2021-04-28 | 2021-07-16 | 浙江意动科技股份有限公司 | Miniature vortex spraying igniter |
| CN115289497A (en) * | 2022-09-22 | 2022-11-04 | 中国空气动力研究与发展中心空天技术研究所 | Pneumatic resonance ignition device for combustion heater |
| CN115405949A (en) * | 2022-08-19 | 2022-11-29 | 中国航发湖南动力机械研究所 | Ignition device and method, combustion chamber and gas turbine |
| CN111207413B (en) * | 2020-02-29 | 2024-04-26 | 哈尔滨工业大学 | Multistage rotational flow miniature gas turbine combustor |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111207413B (en) * | 2020-02-29 | 2024-04-26 | 哈尔滨工业大学 | Multistage rotational flow miniature gas turbine combustor |
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| CN112539109A (en) * | 2020-11-25 | 2021-03-23 | 北京动力机械研究所 | High-altitude low-temperature reliable ignition structure of unmanned aerial vehicle |
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| CN113123882A (en) * | 2021-04-28 | 2021-07-16 | 浙江意动科技股份有限公司 | Miniature vortex spraying igniter |
| CN115405949A (en) * | 2022-08-19 | 2022-11-29 | 中国航发湖南动力机械研究所 | Ignition device and method, combustion chamber and gas turbine |
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Also Published As
| Publication number | Publication date |
|---|---|
| CN109441643B (en) | 2020-12-01 |
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