CN109441643B - Micro-turbojet engine and ignition device for combustion chamber of gas turbine - Google Patents
Micro-turbojet engine and ignition device for combustion chamber of gas turbine Download PDFInfo
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- CN109441643B CN109441643B CN201811127508.2A CN201811127508A CN109441643B CN 109441643 B CN109441643 B CN 109441643B CN 201811127508 A CN201811127508 A CN 201811127508A CN 109441643 B CN109441643 B CN 109441643B
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- kerosene
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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 invention discloses a micro turbojet engine and a combustion chamber ignition device of a gas turbine, which consists of a kerosene nozzle, a kerosene cavity seat, a fastening nut, an oil inlet pipe and a heating core; the whole is arranged on the engine shell through an air inlet cover. The cylindrical surface of the air inlet cover is provided with 6 air inlets, and air can enter the combustion area of the ignition device through the air inlets to be mixed with kerosene. The kerosene nozzle is provided with a pre-burning hole and a main oil hole, and the kerosene can be sprayed out through the pre-burning hole and the main oil hole respectively, so that layered combustion of the kerosene is realized. The heating core adopts a silicon nitride ceramic glow plug, and the power is high. Air enters the ignition area from the air inlet cover, kerosene enters the kerosene cavity seat from the oil inlet pipe and is sprayed out from the precombustion hole and the main oil hole in two paths through the kerosene nozzle. The near precombustion hole produces less oil quantity, and has the precombustion zone that the air velocity is lower, and the precombustion zone has the flame of stable burning and can help igniting main oil hole spun kerosene in wide operating mode within range to guarantee that the some firearm can both reliable and stable work in wide operating mode range.
Description
Technical Field
The invention belongs to the field of micro-miniature turbojet engines and gas turbines, relates to a method for igniting combustion chambers of the micro-miniature turbojet engines and the gas turbines and an ignition device for implementing the method, and can be applied to the ignition process of the combustion chambers of the micro-miniature turbojet engines and the gas turbines.
Background
The micro-miniature turbojet engine and the gas turbine which take the kerosene as the aviation fuel are limited by the size, the structure and the like, the structures of the combustion chamber and the fuel nozzle are relatively simple, and no special ignition and kerosene atomization device is provided, so that the kerosene atomization quality in the starting process of the engine is difficult to ensure, and the starting ignition and the flame propagation are difficult. The propane gas is ignited by the spark plug, and when the engine reaches a certain state, the kerosene is injected for combustion. The ignition mode has the advantages that the fuel atomization state in the starting stage does not need to be considered, and the disadvantages that ground or aerial auxiliary equipment needs to be added and the use of a microminiature turbojet engine or a gas turbine is troublesome are caused.
The use of aerodynamic resonance technology for ignition is also a way of ignition. A pneumatic resonance heating experimental device is described in patent No. CN 101852680B, and two ignition devices based on pneumatic resonance technology are respectively described in published patent nos. CN101852148A and CN 1653254. The main disadvantages of this ignition method: on the one hand, the pneumatic resonance technology is still in an exploration stage and is not mature. On the other hand, the pneumatic resonance requires compressed gas as a working medium for generating a heat source, so that an additional compressed gas tank is required, which greatly increases the cost and the volume weight of the whole ignition system.
In view of the above, it is necessary to design an ignition device having a special structure to provide a stable and reliable ignition source for the start-up of a micro turbojet engine and a gas turbine, and the device is required not to bring additional increase of the volume and weight of the equipment.
Disclosure of Invention
The object of the present invention is to provide a method for igniting micro turbojet engines and micro gas turbine combustion chambers and an ignition device for carrying out the method, which overcome the disadvantages of the prior art and devices. And the layered combustion structure of the igniter is fully utilized to generate large-scale stable flame, and the layered combustion igniter is good in practicability, reliable in function and simple in structure.
The invention relates to a combustion chamber ignition device of a microminiature turbojet engine and a gas turbine, which comprises a heating core, a kerosene nozzle and a kerosene cavity seat which are coaxially nested from inside to outside.
An oil cavity is arranged between the kerosene cavity seat and the kerosene nozzle; a gap is formed between the outer wall of the heating core and the inner wall of the kerosene nozzle in the circumferential direction; the bottom of the kerosene nozzle is circumferentially provided with a main oil hole and a pre-burning hole, and the main oil hole and the pre-burning hole are both communicated with the oil cavity; and the flow of the main oil hole is larger than that of the precombustion hole.
The bottom of the kerosene chamber base is connected with an air inlet cover through threads; the air intake cover is installed inside the engine case. The bottom of the air inlet cover is circumferentially provided with air inlets which are opposite to the side wall of the bottom of the kerosene nozzle. An oil inlet pipe is arranged on the side wall of the coal oil cavity base and is communicated with the oil cavity.
The ignition method of the ignition device of the combustion chamber of the microminiature turbojet engine and the gas turbine comprises the following steps:
1) the air at the outlet of the air compressor reaches the vicinity of the main oil hole and the pre-combustion hole on the kerosene nozzle through the air inlet hole of the air inlet cover and waits to be mixed with the kerosene sprayed from the main oil hole and the pre-combustion hole.
2) And (5) switching on a power supply of the heating core, supplying power to the heating core, and keeping the heating time of the heating core for 10 seconds.
3) Opening an electromagnetic valve of an oil way of the igniter to control the kerosene to enter the oil cavity after passing through the oil inlet pipe, then spraying the kerosene from the pre-combustion hole, spraying the kerosene on the surface of the heating core for gasification and evaporation, mixing the kerosene with ambient air to form a kerosene/air combustible mixed gas, igniting the kerosene at high temperature to generate high-temperature flame, accelerating the gasification and evaporation of the kerosene sprayed from the main oil hole by the high-temperature flame, and finally igniting the kerosene sprayed from the main oil hole by the flame of the pre-combustion hole to form a flame torch sprayed into the combustion chamber.
4) After the exhaust temperature of the micro-miniature turbojet engine or the gas turbine rises by 50 ℃, the solenoid valve of the oil way of the coil pipe is opened, and the kerosene enters the combustion chamber from the oil coil pipe of the micro-miniature turbojet engine or the gas turbine and is ignited by a torch generated by the ignition device.
5) When the exhaust temperature is higher than 250 ℃, the power supply of the heating core is cut off, the oil supply of the ignition oil circuit is cut off, and all kerosene enters the engine for combustion from the oil circuit of the fuel oil coil.
The invention has the advantages that:
1. the invention relates to a microminiature turbojet engine and a combustion chamber ignition device of a gas turbine, which adopt an oil injection and ignition integrated design and can realize direct ignition of kerosene. The structure is simple and reliable, and no extra pipeline or gas storage device is needed.
2. The invention relates to a combustion chamber ignition device of a microminiature turbojet engine and a gas turbine.A cylinder surface outside an air inlet cover is provided with 6 air inlets, air is divided into two paths through each air inlet, and one path of air is downwards mixed with kerosene sprayed out from a preheating hole to form a low-speed combustion area; one path is mixed with kerosene sprayed from the main oil hole for combustion.
3. The kerosene nozzle of the ignition device for the combustion chamber of the microminiature turbojet engine and the gas turbine adopts the double-oil-way structure design of the main oil and the pre-fuel oil, flame is propagated and combusted in a layered mode, and the stability of combustion and the wide working condition range are ensured.
4. The micro-miniature turbojet engine and the ignition device of the combustion chamber of the gas turbine have the advantages that the heating core adopted in the ignition device is high in power, the flame length of the ignition torch is long, the combustible mixed gas in the combustion chamber can be well penetrated and ignited, the flame diffusion speed in the combustion chamber is accelerated, and the stable combustion in the whole combustion chamber is ensured.
5. The ignition device of the combustion chamber of the micro turbojet engine and the gas turbine adopts the fastening nut to realize the installation and fixation of the ignition device on the micro turbojet engine and the gas turbine, and has simple structure and convenient installation and disassembly.
6. The ignition device of the combustion chamber of the microminiature turbojet engine and the gas turbine is made of stainless steel, has low cost and good expansion and contraction resistance at high temperature, and can be used for continuous high-temperature environment work.
7. The method for igniting the combustion chamber of the ignition device of the combustion chamber of the microminiature turbojet engine and the gas turbine has clear steps, less and simple execution structure, and only needs to control the electromagnetic valve and the power supply switch of the electric heating core.
Drawings
FIG. 1 is a sectional view of the combustion chamber ignition device of a micro turbojet engine and a gas turbine according to the present invention.
FIG. 2 is a diagram of the air and kerosene circuits of the micro turbojet engine and the ignition device of the gas turbine combustion chamber of the present invention.
FIG. 3 is a pre-combustion flame for a combustion chamber of a micro turbojet engine and gas turbine engine to which the present invention is applied.
FIG. 4 shows the actual operation of a combustion chamber of a micro turbojet engine and a gas turbine to which the present invention is applied.
In the figure:
1-kerosene nozzle-2-kerosene chamber seat 3-fastening nut
4-oil inlet pipe 5-heating core 6-oil cavity
7-connector 8-air inlet cover 9-mounted on engine shell
10-inlet hole 101-side wall portion 102-notch portion
103-main oil hole 104-precombustion hole
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
The invention relates to a micro-miniature turbojet engine and a combustion chamber ignition device of a gas turbine, which comprises a kerosene nozzle 1, a kerosene cavity seat 2, a fastening nut 3, an oil inlet pipe 4 and a heating core 5, and is shown in figure 1.
The kerosene nozzle 1, the kerosene cavity base 2, the oil inlet pipe 4 and the heating core 5 form an oil way assembly. Wherein, the heating core 5, the kerosene nozzle 1 and the kerosene cavity seat 2 are coaxially nested from inside to outside. The upper part and the lower part of the kerosene cavity base 2 are provided with contact circular shoulders which are contacted with the top part and the middle outer wall of the kerosene nozzle 1 and are welded and fixed in the circumferential direction to form an integrated welding piece, so that a cavity is formed between the kerosene cavity base 2 and the kerosene nozzle 1 and serves as an oil cavity 6. The heating core 5 and the kerosene nozzle 1 are coaxially arranged, and the bottom end of the heating core is positioned at the bottom of the kerosene nozzle 1; and a gap is arranged between the outer wall of the heating core 5 and the inner wall of the kerosene nozzle 1 in the circumferential direction to be used as a combustion gap. The design of 5 upper portions of heating core has connector 7 of an organic whole structure, and this connector 7 cooperates threaded connection between through lower part external screw thread structure and 2 top internal thread structures of kerosene chamber seat, and closely laminates between connector 7 bottom terminal surface and 1 top terminal surface of kerosene nozzle, realizes heating core 5's fixed from this, realizes simultaneously burning the sealed between the gap top.
Four strip-shaped notches are arranged in the circumferential direction of the bottom of the kerosene nozzle 1, are axially designed along the bottom of the kerosene nozzle 1 and penetrate through the bottom surface of the kerosene nozzle 1, so that the bottom of the kerosene nozzle 1 is circumferentially divided into four side wall parts 101 and four notch parts 102, as shown in fig. 2; the bottom end of each side wall part is used as a main oil hole opening position, and the main oil hole 103 is formed at the position; the top surfaces of the two opposite notch parts are used as pre-burning hole opening positions, and the positions are provided with pre-burning holes 104; the opening positions of the main oil holes 103 and the opening positions of the pre-burning holes are eight positions, and are uniformly distributed and alternately arranged in the circumferential direction of the kerosene nozzle 1. In the invention, a main oil hole 103 is related to each main oil hole opening position, and the number of the main oil holes 103 is four; arranging one precombustion hole 104 at the opening positions of the two precombustion holes at opposite positions, and totally arranging two precombustion holes 104; the flow rate of the main oil hole 103 is made larger than the flow rate of the precombustion hole 104. Meanwhile, an annular groove is formed in the middle of the kerosene nozzle 1, six oil outlet grooves 105 are formed in the bottom surface of the groove along the circumferential direction of the kerosene nozzle, four oil outlet grooves 105 in the six oil outlet grooves are respectively communicated with four main oil holes 103, and the other two oil outlet grooves are communicated with two pre-burning holes 104. The annular groove can store kerosene, has the functions of buffering and stabilizing the oil injection pressure, and reduces the oil injection pulsation
The oil passage assembly is mounted to an engine case 9 through an intake cover 8, as shown in fig. 1. The air inlet cover 8 is of a cylindrical structure, an internal thread structure is designed at the top of the air inlet cover, the air inlet cover is in threaded connection with an external thread structure at the bottom of the kerosene cavity base 2 in a matched mode, and the air inlet cover and the kerosene cavity base are located through a locating shoulder arranged on the outer wall of the middle of the kerosene cavity base in the circumferential direction. The air inlet cover 8 is arranged on the inner side of the engine shell 9, the hexagonal end face with the thickness of 2mm is processed on the middle lower part of the air inlet cover 8, and the end face is tightly attached to the inner surface of the engine or the gas turbine shell to play a role in sealing and fastening. The air inlet cover 8 is fixed on the engine through the fastening nut in a threaded connection mode from the outer side of the engine shell, and therefore the oil way assembly and the engine shell are installed. Four air inlets 10 are circumferentially arranged at the bottom of the air inlet cover 8, and the four air inlets 10 respectively face four side wall parts 101 at the bottom of the kerosene nozzle 1; and the distance from the air inlet hole to the end surface of the kerosene cavity seat 2 is larger than the distance from the pre-combustion hole 104 on the kerosene nozzle 1 to the end surface of the kerosene cavity seat 2.
The oil inlet pipe 4 is welded on the side wall of the kerosene cavity base 2 and is communicated with an oil inlet hole formed in the side surface of the kerosene cavity base 2; the oil inlet pipe 4 is communicated with the oil chamber 6 through the oil inlet hole.
When the ignition device of the combustion chamber of the micro turbojet engine and the gas turbine with the structure is operated, as shown in fig. 2, air flows into the air inlet cover 8 from the air inlet hole 10 on the bottom of the air inlet cover 8 in a direction perpendicular to the axial direction of the kerosene nozzle 1, then is blocked by the side wall part 101 on the bottom of the kerosene nozzle 1 to be divided into two parts, one part flows to the vicinity of the pre-combustion hole 104, and a low-speed area is formed in the vicinity of the pre-combustion hole 104 on the kerosene nozzle 1. The other portion flows to the vicinity of the main oil hole 103.
Kerosene flows into the oil chamber 6 from the oil inlet pipe 4, flows into the main oil hole 103 and the pre-combustion hole 104 through the oil outlet groove 105 on the oil chamber 6, and is ejected from the pre-combustion hole 104 and then ejected from the main oil hole 103 to be mixed with ambient air.
The heating core 5 of the invention can not only gasify and evaporate the kerosene ejected from the pre-combustion hole 104 and provide an ignition heat source to ignite the air/kerosene mixed gas in the pre-combustion area, but also preheat the kerosene flowing through the main oil hole 103, thereby improving the ignition reliability of the main torch. Therefore, a small amount of kerosene ejected from the precombustion holes 104 is mixed with the air in the low velocity zone in advance, heated by the heating core 5, and rapidly evaporated and combusted to form a precombustion flame, as shown in fig. 3. Then the pre-combustion flame preheats the kerosene flowing through the main oil hole 103, the preheated kerosene is sprayed out from the main oil hole 103 and then mixed with air with higher speed, and the mixture is ignited by the pre-combustion flame to form a stable torch, as shown in fig. 4.
Under the working condition of a large equivalence ratio, most of fuel oil is preheated by the heating core 5 and then is sprayed out of the main oil hole 103, only a small part of fuel oil is sprayed out of the pre-combustion hole 104, and the equivalence ratio near the pre-combustion hole 104 is still in a proper range. Kerosene sprayed from the pre-burning holes is directly sprayed on the surface of the heating core, and after the kerosene is mixed with air in a low-speed area, the kerosene is quickly gasified, evaporated and ignited to form pre-burning flame, and the burning flame around the pre-burning holes is surrounded by the inner cylindrical surface of the air inlet cover, so that the stability of the burning flame is ensured. Then, the pre-burning flame helps to ignite the kerosene sprayed from the main oil hole 103, so that the ignition reliability and stability under an oil-rich part are ensured, the flame length of an ignition torch is increased, and the propagation of flame in a combustion chamber is accelerated.
Under the working condition of smaller equivalence ratio, a small amount of air forms a stable low-speed area near the precombustion hole to ensure the formation of precombustion flame, and the residual gas flows away directly through the air inlet hole 10 on the air inlet cover 8 without influencing the formation of precombustion flame in the precombustion area, thereby ensuring the reliability and stability of ignition under the lean oil state. The inventive ignition device is therefore capable of reliable ignition over a wide range of operating conditions.
Parts of the ignition device except the heating core 5 are all made of stainless steel materials, parts needing to be sealed all adopt welded structures, air tightness and connection strength are effectively guaranteed, non-sealed parts are connected through threads, and the simplicity and reliability of the whole structure are guaranteed.
The invention relates to a specific ignition method of an ignition device of a combustion chamber of a microminiature turbojet engine and a gas turbine, which comprises the following steps:
1) the air at the outlet of the air compressor reaches the vicinity of the main oil hole 103 and the pre-combustion hole 104 on the kerosene nozzle 1 through the air inlet hole 10 of the air inlet cover 8 and waits to be mixed with the kerosene sprayed from the main oil hole 103 and the pre-combustion hole 104;
2) switching on a power supply of the heating core 5 to supply power to the heating core 5, and generating hot high temperature on the surface of the tungsten silicon nitride wire of the heating core 5, wherein the heating time lasts for 10 seconds;
3) an electromagnetic valve of an oil way of the igniter is opened, appropriate kerosene is controlled to enter the oil cavity 6 after passing through the oil inlet pipe 4, then the kerosene is firstly sprayed out from the pre-combustion hole 104, is sprayed on the surface of the heating core 5 to be gasified and evaporated, is mixed with ambient air to form kerosene/air combustible mixed gas, is ignited at high temperature to generate high-temperature flame, the gasification and evaporation of the kerosene sprayed out of the main oil hole 103 are accelerated by the high-temperature flame, and finally the kerosene sprayed out of the main oil hole 103 is ignited by the flame of the pre-combustion hole 104 to form a flame torch sprayed into a combustion.
4) After the exhaust temperature of the micro-miniature turbojet engine or the gas turbine rises by 50 ℃, the solenoid valve of the oil way of the coil pipe is opened, and a large amount of kerosene enters the combustion chamber from the oil coil pipe of the micro-miniature turbojet engine or the gas turbine and is ignited by a torch generated by the ignition device.
5) When the exhaust temperature is higher than 250 ℃, the micro turbojet engine or the gas turbine is considered to be ignited successfully, the power supply of the heating core is cut off, the oil supply of the ignition oil way is cut off, and all kerosene enters the engine from the oil way of the fuel oil coil pipe to be combusted.
Claims (3)
1. Microminiature turbojet engine and gas turbine combustion chamber ignition, its characterized in that: comprises a heating core, a kerosene nozzle and a kerosene cavity seat which are coaxially nested from inside to outside;
an oil cavity is arranged between the kerosene cavity seat and the kerosene nozzle; a gap is formed between the outer wall of the heating core and the inner wall of the kerosene nozzle in the circumferential direction; the bottom of the kerosene nozzle is provided with four notch parts and four side wall parts which are alternated in the circumferential direction; the bottom end of each side wall part is used as a main oil hole opening position; the top surfaces of the two opposite notch parts are used as opening positions of the pre-burning holes; the main oil hole and the pre-combustion hole are communicated with the oil cavity; the flow of the main oil hole is larger than that of the precombustion hole;
the bottom of the kerosene chamber base is connected with an air inlet cover through threads; the air inlet cover is arranged on the inner side of the engine shell; the bottom of the air inlet cover is circumferentially provided with air inlet holes which are opposite to the side wall of the bottom of the kerosene nozzle;
an oil inlet pipe is arranged on the side wall of the coal oil cavity base and is communicated with the oil cavity.
2. The micro turbojet engine and gas turbine combustor ignition device of claim 1, wherein: the middle part of the kerosene nozzle is provided with an annular groove, and the bottom surface of the groove is provided with oil outlet grooves along the circumferential direction of the kerosene nozzle and communicated with the main oil hole and the pre-burning hole.
3. The micro turbojet engine and gas turbine combustor ignition device of claim 1, wherein: the ignition method comprises the following steps:
1) the air at the outlet of the air compressor reaches the vicinity of the main oil hole and the pre-combustion hole on the kerosene nozzle through the air inlet hole of the air inlet cover and waits to be mixed with the kerosene sprayed out of the main oil hole and the pre-combustion hole;
2) switching on a power supply of the heating core, supplying power to the heating core, and keeping the heating time of the heating core for 10 seconds;
3) opening an electromagnetic valve of an oil way of the igniter, controlling kerosene to enter an oil cavity after passing through an oil inlet pipe, spraying the kerosene from the pre-combustion hole, gasifying and evaporating the kerosene on the surface of the heating core, mixing the kerosene with ambient air to form a kerosene/air combustible mixed gas, igniting the kerosene at high temperature to generate high-temperature flame, accelerating gasification and evaporation of the kerosene sprayed from the main oil hole by the high-temperature flame, and finally igniting the kerosene sprayed from the main oil hole by the flame of the pre-combustion hole to form a flame torch sprayed into the combustion chamber;
4) after the exhaust temperature of the micro-miniature turbojet engine or the gas turbine rises by 50 ℃, opening a coil oil way electromagnetic valve, and introducing kerosene into a combustion chamber from a fuel oil coil of the micro-miniature turbojet engine or the gas turbine to be ignited by a torch generated by an ignition device;
5) when the exhaust temperature is higher than 250 ℃, the power supply of the heating core is cut off, the oil supply of the ignition oil circuit is cut off, and all kerosene enters the engine for combustion from the oil circuit of the fuel oil coil.
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| 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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| 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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| CN109441643B true CN109441643B (en) | 2020-12-01 |
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| CN111779577B (en) * | 2020-06-30 | 2021-09-14 | 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 |
| CN112761819B (en) * | 2021-01-15 | 2023-01-06 | 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 |
| CN115405949B (en) * | 2022-08-19 | 2023-12-15 | 中国航发湖南动力机械研究所 | Ignition device, ignition method, combustion chamber and gas turbine |
| 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 |
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