CN101799174B - Main combustible stage tangential oil supply premix and pre-evaporation combustion chamber - Google Patents

Main combustible stage tangential oil supply premix and pre-evaporation combustion chamber Download PDF

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CN101799174B
CN101799174B CN201010034141A CN201010034141A CN101799174B CN 101799174 B CN101799174 B CN 101799174B CN 201010034141 A CN201010034141 A CN 201010034141A CN 201010034141 A CN201010034141 A CN 201010034141A CN 101799174 B CN101799174 B CN 101799174B
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combustion
nozzle
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evaporation
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CN101799174A (en
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林宇震
林阳
许全宏
张弛
刘高恩
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Beihang University
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Abstract

The invention relates to a main combustion stage tangential oil supply premix and pre-evaporation combustion chamber. The combustion chamber is in a single-ring chamber structure and is designed by adopting the conceptual design of staging combustion, and all the used amount of gas for combustion is supplied by the precombustion stage and the main combustion stage. The combustion chamber mainly comprises a flow-dividing type diffuser, a combustion chamber outer case, a combustion chamber inner case, a fuel nozzle, the precombustion stage, the main combustion stage, a flame tube outer wall and a flame tube inner wall. The precombustion stage utilizes a low-speed flow returning zone generated by swirl air entering the combustion chamber by a precombustion stage swirler component; the fuel needed by the main combustion stage is ejected by the tangential main combustion stage nozzle, is atomized under the air flow effect generated by entering of atomized air of the main combustion stage nozzle into a pipe, then flows into a premix and pre-evaporation ring pipe for evaporation, and is further blended with air; and even oil-gas mixed gas formed at the outlet of the premix and pre-evaporation ring pipe enters a flame tube and combusts under the pilot combustion of the precombustion stage flame. The combustion chamber has simple structure, and can effectively reduce the discharge of pollution simultaneously while guaranteeing that an aeroengine is in normal working state.

Description

主燃级切向供油的预混预蒸发燃烧室Premixed pre-evaporative combustor with tangential oil supply to the main combustion stage

技术领域 technical field

本发明涉及一种采用预混预蒸发燃烧组织方式的航空燃气轮机燃烧室,采用该预混预蒸发燃烧组织方式的燃烧室结构简单,在保证燃烧室高效稳定工作的同时,能够降低燃烧的污染排放。  The invention relates to an aviation gas turbine combustor adopting a premixed pre-evaporative combustion organization mode. The combustor adopting the premixed pre-evaporative combustion organization mode has a simple structure, and can reduce combustion pollution emissions while ensuring efficient and stable operation of the combustor . the

背景技术Background technique

现代航空发动机燃烧室的基本性能和结构分布已经达到相当高的水平,但是对于现代航空发动机燃烧室来说,仍在存在大量的难题和挑战,新材料、新工艺、新结构、新概念的发展应用才是保证其持续进步的源泉。  The basic performance and structural distribution of modern aero-engine combustors have reached a fairly high level, but for modern aero-engine combustors, there are still a lot of problems and challenges. The development of new materials, new processes, new structures, and new concepts Application is the source to ensure its continuous progress. the

现代航空发动机燃烧室的主要发展趋势是低污染燃烧。航空发动机燃烧室必须满足日益严格的航空发动机污染排放标准。目前采用的CAEP6(Committee on Aviation EnvironmentalProtection)标准的要求已经非常严格,特别是对NOx污染排放要求,而随着人们对环境保护意识的增强,以后的要求将更为严格。  The main development trend of modern aero-engine combustors is low-pollution combustion. Aeroengine combustors must meet increasingly stringent aeroengine pollution emission standards. The requirements of the currently adopted CAEP6 (Committee on Aviation Environmental Protection) standard are already very strict, especially for NOx pollution emission requirements, and as people's awareness of environmental protection increases, the future requirements will be more stringent. the

美国航空发动机的两个著名公司GE和PW对低污染燃烧室已经着手研究,GE首先研发了双环腔低污染燃烧DAC(用于GE90和CFM56),PW公司采用了类RQL(富油燃烧-快熄-贫油燃烧,Rich burn-Quench-Lean burn,简称RQL)低污染燃烧室TALON II(用于PW4000和6000系列)。在下一代低污染燃烧室方面,GE公司采用LDM(Lean Direct MixingCombustion,贫油直接混合燃烧室)技术为其GEnx发动机研制的TAPS(Twin AnnularPremixing Swirler)低污染燃烧室。该燃烧室在台架全环试验验证中,NOx污染排放比CAEP2排放标准降低了50%。PW公司继续采用RQL方式提出了降低NOx污染排放的低污染燃烧室为TALON X,采用的头部形式是PW公司发展的空气雾化喷嘴,燃烧室为单环腔,在V2500发动机扇型试验段上的试验结果比CAEP2标准降低了50%。Rolls-Royce公司采用LDM技术发展的低污染燃烧室是ANTLE,该燃烧室是一个单环腔分级燃烧室,其NOx污染排放比CAEP2标准降低了50%,用于其新一代发动机湍达1000。  GE and PW, two well-known American aero-engine companies, have started research on low-pollution combustors. GE first developed a double-annular low-pollution combustion DAC (used in GE90 and CFM56), and PW adopted a similar RQL (rich combustion-quick combustion) Quench-lean burn, Rich burn-Quench-Lean burn, referred to as RQL) low-pollution combustor TALON II (for PW4000 and 6000 series). In terms of the next generation of low-pollution combustors, GE uses LDM (Lean Direct Mixing Combustion, Lean Direct Mixing Combustion) technology to develop the TAPS (Twin Annular Premixing Swirler) low-pollution combustor for its GEnx engine. In the bench full ring test verification of the combustion chamber, the NOx pollution emission is reduced by 50% compared with the CAEP2 emission standard. PW Company continues to adopt the RQL method and proposes a low-pollution combustion chamber that reduces NOx pollution emissions as TALON X. The head form used is the air atomizing nozzle developed by PW Company. The combustion chamber is a single annular cavity. In the fan-shaped test section of the V2500 engine The above test results are 50% lower than the CAEP2 standard. The low-pollution combustor developed by Rolls-Royce using LDM technology is ANTLE, which is a single-annular staged combustor. Its NOx pollution emissions are 50% lower than CAEP2 standards, and it is used in its new generation of engines with turbulence up to 1000. the

而不管是何种先进的低污染燃烧室,其关键技术就是降低NOx(氮氧化物)、CO(一氧化碳)、UHC(未燃碳氢化合物)和冒烟的燃烧技术,核心问题是降低燃烧区的温度、同时使燃烧区温度场均匀,即整体和局部的当量比控制,而主燃区当量比的均匀性又主要取决于燃油雾化和油气掺混的均匀性。  No matter what kind of advanced low-pollution combustion chamber, its key technology is to reduce NOx (nitrogen oxides), CO (carbon monoxide), UHC (unburned hydrocarbons) and smoke combustion technology, the core issue is to reduce the combustion area At the same time, the temperature field in the combustion zone is uniform, that is, the overall and local equivalence ratio control, and the uniformity of the equivalence ratio in the main combustion zone mainly depends on the uniformity of fuel atomization and oil-gas mixing. the

本发明是针对航空发动机低污染燃烧的新方法。根据NOx与CO产生的机理及试验结果可知:燃烧室的主燃区当量比在0.6~0.8范围内产生的NOx与CO(UHC和CO的排放规律类似)很少。基于此原理,要兼顾NOx与CO、UHC的排放量都处于低值范围,应考虑两个因素:其一是主燃区的平均当量比,其二是主燃区平均当量比的均匀性,并且在所有航空发动机的工作情况下都应如此。而主燃区当量比的均匀性又主要取决于燃油雾化和油气掺混的均匀性。这主要取决于两方面:一是燃油颗粒直径分布的均匀性,即SMD的分布均匀性;二则是燃油油雾浓度分布的均匀性。从燃烧方式讲,应采用均匀的预混燃烧,达到主燃区当量比均匀性要求以降低污染排放。  The invention is a new method for low-pollution combustion of aero-engines. According to the mechanism and test results of NOx and CO production, it can be known that the equivalent ratio of the main combustion zone of the combustion chamber in the range of 0.6-0.8 produces very little NOx and CO (the emission laws of UHC and CO are similar). Based on this principle, to take into account that the emissions of NOx, CO, and UHC are all in the low range, two factors should be considered: one is the average equivalence ratio of the main combustion zone, and the other is the uniformity of the average equivalence ratio of the main combustion zone. And this should be the case in all aero-engine work situations. The uniformity of the equivalence ratio in the main combustion zone mainly depends on the uniformity of fuel atomization and oil-gas mixing. This mainly depends on two aspects: one is the uniformity of fuel particle diameter distribution, that is, the uniformity of SMD distribution; the other is the uniformity of fuel oil mist concentration distribution. In terms of the combustion method, uniform premixed combustion should be adopted to meet the requirements of uniformity ratio of the main combustion zone to reduce pollution emissions. the

目前的常规燃烧方式无法降低NOx、CO和UHC。原因是目前燃烧室的设计方法所决定的。对于常规燃烧室来说,在高功率状态时,由于采用液雾扩散燃烧方式,燃烧区局部当量比总是在1附近,远超过上述低污染燃烧所需当量比范围要求,此时虽然CO和UHC的排放低,但NOx的排放达到最大。在低功率状态时,燃烧区当量比又很低,远低于上述低污染燃烧所需当量比区间,此时虽然NOx排放低,但CO和UHC排放又很高。另外,由于常规燃烧室普遍采用扩散燃烧方式,局部当量比非常不均匀,因此对于常规燃烧室来说,无法满足在整个发动机工作范围内的低污染要求。  The current conventional combustion methods cannot reduce NOx, CO and UHC. The reason is determined by the current design method of the combustion chamber. For conventional combustors, in the high power state, due to the liquid mist diffusion combustion method, the local equivalence ratio of the combustion zone is always around 1, which is far beyond the range of equivalence ratio required for low-pollution combustion. At this time, although CO and The emission of UHC is low, but the emission of NOx reaches the maximum. In the low power state, the equivalence ratio of the combustion zone is very low, which is far below the equivalence ratio range required for low-pollution combustion. At this time, although NOx emissions are low, CO and UHC emissions are high. In addition, because the conventional combustion chamber generally adopts the diffusion combustion method, the local equivalence ratio is very uneven, so for the conventional combustion chamber, it cannot meet the low pollution requirements in the entire engine working range. the

发明内容 Contents of the invention

本发明的技术解决问题:提供一种采用主燃级切向供油的预混预蒸发燃烧组织方式的航空发动机燃烧室,该燃烧室在满足航空发动机的工作条件下,能有效的降低航空发动机燃烧室燃烧的污染排放,包括NOx、冒烟、CO及UHC,且结构简单。  The technical problem of the present invention is to provide an aero-engine combustor adopting a premixed pre-evaporative combustion organization mode of tangential fuel supply at the main combustion stage, which can effectively reduce the The pollution emissions from combustion in the combustion chamber include NOx, smoke, CO and UHC, and the structure is simple. the

本发明的技术解决方案:主燃级切向供油的预混预蒸发燃烧室为单环腔结构,采用分级燃烧的概念设计,燃烧用气量全部由预燃级和主燃级供入,预燃级采用旋流稳定的扩散火焰燃烧组织方式,主燃级采用切向供油的预混预蒸发燃烧组织方式,冷却气和掺混气从火焰筒供入。主燃级切向供油的预混预蒸发燃烧室主要由分流式扩压器、燃烧室外机匣、燃烧室内机匣、燃油喷嘴、火焰筒头部、火焰筒外壁和火焰筒内壁组成。火焰筒头部由预燃级和主燃级组成:预燃级包括预燃级旋流器组件、预燃级喷嘴、预燃级头部端壁和预燃级头部内导流板,预燃级利用由预燃级旋流器组件进入燃烧室的旋流空气产生的低速回流区稳定火焰,预燃级旋流器组件通过预燃级头部端壁与主燃级预混预蒸发段内环相连接,预燃级喷嘴位于预燃级旋流器组件内,并与预燃级旋流器组件同轴,预燃级头部内导流板与预燃级头部端壁相连;主燃级包括主燃级喷嘴、主燃级预混预蒸发段、主燃级头部整体端壁和主燃级头部整体导流板,主燃级预混预蒸发段由主燃级预混预蒸发环管和主燃级喷嘴雾化空气进入管组成,主燃级喷嘴位于主燃级喷嘴雾化空气进入管入口,并与主燃级喷嘴雾化空气进入管同轴,主燃级喷嘴采用在同一圆周上设置多个单个燃油喷嘴的喷射方式,该 圆周的圆心位于预燃级喷嘴的轴线上,主燃级喷嘴采用的单个喷嘴数量与主燃级喷嘴雾化空气进入管的数量相对应,主燃级所需的燃油由主燃级喷嘴喷出后,首先被主燃级喷嘴雾化空气进入管的气流雾化形成油气混合气,然后流入主燃级预混预蒸发环管,油气混合气在主燃级预混预蒸发环管中蒸发,并与空气进一步掺混,在主燃级预混预蒸发环管的出口处形成均匀的油气混合气射流进入火焰筒内,在预燃级火焰的引燃下进行燃烧,主燃级预混预蒸发段通过主燃级头部整体端壁与火焰筒外壁和火焰筒外壁相连,主燃级头部整体导流板与主燃级头部整体端壁相连;预燃级喷嘴和主燃级喷嘴均连接在燃油喷嘴座上,通过燃油喷嘴座与燃烧室外机匣相连。  The technical solution of the present invention: the premixed pre-evaporation combustor with tangential oil supply from the main combustion stage is a single-ring cavity structure, adopts the conceptual design of staged combustion, and the gas consumption for combustion is all supplied by the pre-combustion stage and the main combustion stage The fuel stage adopts the swirling stable diffusion flame combustion organization mode, the main combustion stage adopts the premixed pre-evaporation combustion organization mode of tangential oil supply, and the cooling gas and mixed gas are supplied from the flame tube. The premixed pre-evaporation combustor with tangential fuel supply in the main combustion stage is mainly composed of a split diffuser, a combustion chamber outside the combustion chamber, a combustion chamber inside the casing, a fuel nozzle, a flame tube head, a flame tube outer wall and a flame tube inner wall. The head of the flame tube is composed of the pre-combustion stage and the main combustion stage: the pre-combustion stage includes the pre-combustion stage swirler assembly, the pre-combustion stage nozzle, the end wall of the pre-combustion stage head and the inner deflector of the pre-combustion stage head, the pre-combustion stage The combustion stage uses the low-velocity recirculation area to stabilize the flame generated by the swirling air that enters the combustion chamber from the pre-combustion stage swirler assembly. The inner ring is connected, the pre-combustion stage nozzle is located in the pre-combustion stage swirler assembly, and is coaxial with the pre-combustion stage swirler assembly, and the inner deflector of the pre-combustion stage head is connected to the end wall of the pre-combustion stage head; The main combustion stage includes the main combustion stage nozzle, the main combustion stage premixing pre-evaporation section, the main combustion stage head integral end wall and the main combustion stage head integral deflector. The mixed pre-evaporation ring pipe and the main combustion stage nozzle atomization air inlet pipe are composed. The nozzle adopts the injection method of setting multiple single fuel nozzles on the same circumference, and the center of the circle is located on the axis of the pre-combustion stage nozzle. Correspondingly, after the fuel required by the main combustion stage is sprayed from the nozzle of the main combustion stage, it is first atomized by the airflow of the atomization air inlet pipe of the main combustion stage nozzle to form an oil-air mixture, and then flows into the premixing pre-evaporation ring pipe of the main combustion stage , the oil-air mixture evaporates in the premixed pre-evaporation loop of the main combustion stage, and is further mixed with air, and forms a uniform jet of oil-air mixture at the outlet of the premixed pre-evaporation loop of the main combustion stage and enters the flame tube. Combustion is carried out under the ignition of the flame of the pre-combustion stage. The pre-mixing and pre-evaporation section of the main combustion stage is connected with the outer wall of the flame tube and the outer wall of the flame tube through the overall end wall of the main combustion stage head. The overall end wall of the stage head is connected; the pre-combustion stage nozzle and the main combustion stage nozzle are connected to the fuel nozzle seat, and are connected to the casing outside the combustion chamber through the fuel nozzle seat. the

本发明的原理是:一般而言,航空发动机燃烧室低污染排放的实现主要就是通过两方面,一是控制整个燃烧室内燃烧区域的总体当量比范围;二则是控制燃烧室内整个燃烧区域的燃烧均匀性,即当量比均匀性,因为局部富油而导致的局部当量比过大也会大大增加发动机的污染排放。根据上述原理并且考虑到航空发动机燃烧室的工作特点,本发明采用:分级燃烧的设计思想,使燃烧用气分别从预燃级和主燃级供入燃烧室,并将燃油进行分级供入,控制燃油在燃烧区内的当量比在航空发动机不同工作状态下都在低污染燃烧区内,从而达到降低燃烧污染排放物的目的。预燃级在慢车等小状态下启动,保持小状态时燃烧区的当量比落在上述低污染燃烧当量比区间内,并且使燃烧的稳定性好,容易启动。当发动机工作在大状态时才启动主燃级,主燃级采用切向供油的预混预蒸发燃烧组织方式,控制燃烧区的当量比在上述低污染燃烧当量比区间。采用上述低污染燃烧室,可确保航空发动机燃烧室在所有的工作状态下,燃烧区的当量比都控制在低污染燃烧的区间内,同时可以通过控制主燃级油雾均匀度、混合度和蒸发度来控制燃烧区的当量比均匀度,从而达到航空发动机低污染燃烧室污染排放低、稳定性好的性能要求。  The principle of the present invention is: Generally speaking, the realization of low pollution emission from the combustion chamber of an aero-engine is mainly through two aspects, one is to control the overall equivalent ratio range of the combustion area in the entire combustion chamber; the other is to control the combustion of the entire combustion area in the combustion chamber Uniformity, that is, the uniformity of the equivalence ratio, because the local equivalence ratio is too large due to local rich oil will also greatly increase the pollution emissions of the engine. According to the above principles and considering the working characteristics of the aero-engine combustion chamber, the present invention adopts the design concept of staged combustion, so that the combustion gas is supplied into the combustion chamber from the pre-combustion stage and the main combustion stage respectively, and the fuel is supplied in stages, The equivalence ratio of the fuel in the combustion zone is controlled to be in the low-pollution combustion zone under different working conditions of the aero-engine, so as to achieve the purpose of reducing combustion pollutant emissions. The pre-combustion stage is started in a small state such as idling, and the equivalence ratio of the combustion zone falls in the above-mentioned low-pollution combustion equivalence ratio range when the small state is maintained, and the stability of combustion is good, and it is easy to start. The main combustion stage is started only when the engine is working in a large state. The main combustion stage adopts the premixed pre-evaporative combustion organization mode of tangential fuel supply, and the equivalence ratio of the combustion zone is controlled within the above-mentioned low-pollution combustion equivalence ratio range. The use of the above-mentioned low-pollution combustor can ensure that the equivalent ratio of the combustion zone of the aero-engine combustor is controlled within the range of low-pollution combustion under all working conditions. At the same time, it can control the uniformity, mixing degree and The degree of evaporation is used to control the uniformity of the equivalence ratio in the combustion zone, so as to meet the performance requirements of the aero-engine low-pollution combustion chamber with low pollution emissions and good stability. the

本发明与现有技术相比的优点如下:  The advantages of the present invention compared with the prior art are as follows:

(1)本发明的燃烧室为单环腔结构,采用分级燃烧的概念设计,燃烧用气量全部由预燃级和主燃级供入,火焰筒没有主燃孔,冷却气和掺混气从火焰筒供入,增加燃烧室功效的同时简化燃烧室结构。  (1) The combustion chamber of the present invention is a single-ring cavity structure, adopts the conceptual design of staged combustion, and the gas consumption for combustion is all supplied by the pre-combustion stage and the main combustion stage. The flame tube is supplied, which increases the efficiency of the combustion chamber and simplifies the structure of the combustion chamber. the

(2)本发明的主燃级采用切向供油的预混预蒸发的燃烧组织方式。切向供油可以在获得良好的燃油一次雾化效果的同时简化主燃级结构,预混预蒸发可以使雾化后的燃油与空气进一步混合均匀,形成均匀的油气混合气射流。当这股均匀的油气混合气射流被点燃后,油气混合气可以在极短的时间内燃烧完全,从而降低燃烧室的污染排放。  (2) The main combustion stage of the present invention adopts a combustion organization mode of premixing and preevaporation with tangential fuel supply. Tangential fuel supply can simplify the structure of the main combustion stage while obtaining a good primary atomization effect of fuel. Premixing and pre-evaporation can further mix the atomized fuel and air evenly to form a uniform jet of fuel-air mixture. When the uniform jet of oil-air mixture is ignited, the oil-air mixture can be completely burned in a very short time, thereby reducing the pollution emission of the combustion chamber. the

(3)本发明的预燃级采用旋流稳定的扩散火焰燃烧组织方式,主燃级采用切向供油的预混预蒸发燃烧组织方式,这种组合燃烧模式可以实现航空发动机燃烧室在宽广的工作范 围内高效稳定的工作,同时可以实现燃烧室低污染排放。  (3) The pre-combustion stage of the present invention adopts a swirling stable diffusion flame combustion organization mode, and the main combustion stage adopts a premixed pre-evaporation combustion organization mode of tangential fuel supply. This combined combustion mode can realize the aeroengine combustion chamber in a wide It can work efficiently and stably within the working range, and at the same time can achieve low pollution emissions from the combustion chamber. the

附图说明 Description of drawings

图1为本发明的工作示意图;  Fig. 1 is the working schematic diagram of the present invention;

图2为本发明的结构剖视图;  Fig. 2 is a structural sectional view of the present invention;

图3为本发明的火焰筒头部结构剖视图;  Fig. 3 is a cross-sectional view of the flame tube head structure of the present invention;

图4为本发明的主燃级预混预蒸发段组件结构示意图;  Fig. 4 is the structural representation of main combustion stage premixed pre-evaporation section assembly of the present invention;

图5为本发明的主燃级预混预蒸发段组件结构剖视图;  Fig. 5 is the structural cross-sectional view of the main combustion stage premixed pre-evaporation section assembly of the present invention;

图6为本发明的预燃级组件结构示意图;  Fig. 6 is the structural representation of the pre-combustion stage assembly of the present invention;

图7为本发明的预燃级组件结构剖视图;  Figure 7 is a cross-sectional view of the pre-combustion stage assembly structure of the present invention;

图8为本发明的预燃级旋流器组件结构示意图;  Fig. 8 is a schematic structural view of the pre-combustion stage cyclone assembly of the present invention;

图9为本发明的预燃级旋流器组件结构剖视图;  Fig. 9 is a structural sectional view of the pre-combustion stage cyclone assembly of the present invention;

图10为本发明的具体实施方案火焰筒结构示意图;  Fig. 10 is a schematic view of the flame cylinder structure of a specific embodiment of the present invention;

图11为本发明采用的燃油喷嘴结构示意图;  Fig. 11 is the schematic diagram of the structure of the fuel nozzle used in the present invention;

图12为本发明采用的主燃级喷嘴喷射方式示意图。  Fig. 12 is a schematic diagram of the injection mode of the main combustion stage nozzle adopted in the present invention. the

图中:1.燃烧室进口气流,2.火焰筒头部气流,3.燃烧室外环腔气流,4.燃烧室内环腔气流,5.燃烧室出口气流,6.预燃级燃烧区域,7.主燃级燃烧区域,8.分流式扩压器,9.燃烧室外机匣,10.燃烧室内机匣,11.燃油喷嘴,12.主燃级头部整体端壁,13.主燃级头部整体导流板,14.火焰筒头部,15.火焰筒外壁,16.火焰筒内壁,17.火焰筒外壁掺混孔,18.火焰筒内壁掺混孔,19.发散冷却孔,20.预燃级,21.主燃级预混预蒸发段,22.预燃级旋流器组件,23.预燃级头部端壁,24.预燃级头部导流板,25.预燃级一级旋流器,26.预燃级一级旋流器压板,27.预燃级二级旋流器,28.主燃级预混预蒸发环管,29.主燃级喷嘴雾化空气进入管,30.预燃级喷嘴,31.主燃级喷嘴,32.燃油喷嘴座,33.主燃级。  In the figure: 1. Airflow at the inlet of the combustion chamber, 2. Airflow at the head of the flame tube, 3. Airflow in the annular cavity outside the combustion chamber, 4. Airflow in the annular cavity inside the combustion chamber, 5. Airflow at the outlet of the combustion chamber, 6. The combustion area of the pre-combustion stage, 7. Combustion area of main combustion stage, 8. Divider diffuser, 9. Outer casing of combustion chamber, 10. Case inside combustion chamber, 11. Fuel nozzle, 12. Integral end wall of main combustion stage head, 13. Main combustion chamber Integral deflector of the stage head, 14. head of the flame tube, 15. outer wall of the flame tube, 16. inner wall of the flame tube, 17. mixing holes on the outer wall of the flame tube, 18. mixing holes on the inner wall of the flame tube, 19. divergent cooling holes , 20. Pre-combustion stage, 21. Main combustion stage premixing pre-evaporation section, 22. Pre-combustion stage swirler assembly, 23. Pre-combustion stage head end wall, 24. Pre-combustion stage head deflector, 25 .Pre-combustion stage primary cyclone, 26. Pre-combustion stage primary cyclone pressure plate, 27. Pre-combustion stage secondary cyclone, 28. Main combustion stage premixing and pre-evaporation ring pipe, 29. Main combustion stage Nozzle atomizing air inlet tube, 30. Pre-firing stage nozzle, 31. Main firing stage nozzle, 32. Fuel nozzle seat, 33. Main firing stage. the

具体实施方式 Detailed ways

如图1和图2所示,本发明设计的切向供油的预混预蒸发燃烧室为单环腔结构,采用分级燃烧的概念设计,燃烧用气量全部由预燃级和主燃级供入,预燃级采用旋流稳定的扩散火焰燃烧组织方式,主燃级采用切向供油的预混预蒸发的燃烧组织方式,冷却气和掺混气从火焰筒供入。本燃烧室包含两个燃烧区域——预燃级燃烧区域6和主燃级燃烧区域7,两个燃烧区域共用相同的内外边界,燃烧区域的外边界是火焰筒外壁15,燃烧区域的内边界是火焰筒内壁16,环形的火焰筒外壁15和火焰筒内壁16位于环形的燃烧室外机匣9和燃烧室内机匣10之间。在火焰筒外壁15上安排有火焰筒外壁掺混孔17,在火焰筒内壁16上安排有火焰筒内壁掺混孔18,掺混用气通过火焰筒外壁掺混孔17和火焰筒内壁掺混孔 18进入燃烧室,用于调节燃烧室出口温度分布。火焰筒外壁15和火焰筒内壁16还安排有冷却,冷却方式可以采用气膜冷却、发散冷却或复合冷却方式,用于冷却火焰筒壁面,保证燃烧室的寿命。在具体实施方案中,火焰筒外壁15和火焰筒内壁16的冷却方式采用发散冷却,在火焰筒外壁15和火焰筒内壁16开有发散冷却孔19,发散冷却孔19的示意如图1和图2所示。  As shown in Figure 1 and Figure 2, the premixed pre-evaporation combustor with tangential oil supply designed by the present invention has a single-ring cavity structure, adopts the conceptual design of staged combustion, and the gas consumption for combustion is all supplied by the pre-combustion stage and the main combustion stage. The pre-combustion stage adopts a swirling stable diffusion flame combustion organization, the main combustion stage adopts a pre-mixed pre-evaporation combustion organization with tangential oil supply, and the cooling gas and mixed gas are supplied from the flame tube. This combustion chamber comprises two combustion areas---the pre-combustion level combustion area 6 and the main combustion level combustion area 7, two combustion areas share the same inner and outer boundaries, the outer boundary of the combustion area is the outer wall 15 of the flame tube, and the inner boundary of the combustion area It is the inner wall 16 of the flame tube, and the outer wall 15 of the annular flame tube and the inner wall 16 of the flame tube are located between the annular casing 9 outside the combustion chamber and the casing 10 inside the combustion chamber. Flame tube outer wall mixing holes 17 are arranged on the flame tube outer wall 15, flame tube inner wall mixing holes 18 are arranged on the flame tube inner wall 16, and the gas for mixing passes through the flame tube outer wall mixing holes 17 and the flame tube inner wall mixing holes. 18 into the combustion chamber to adjust the outlet temperature distribution of the combustion chamber. The flame tube outer wall 15 and the flame tube inner wall 16 are also arranged with cooling, and the cooling method can adopt film cooling, divergent cooling or composite cooling mode, which is used to cool the flame tube wall surface to ensure the life of the combustion chamber. In a specific embodiment, the cooling mode of the outer wall 15 of the flame tube and the inner wall 16 of the flame tube adopts divergent cooling, and the outer wall 15 of the flame tube and the inner wall 16 of the flame tube are provided with divergent cooling holes 19. 2 shown. the

在预燃级燃烧区域6的上游是火焰筒头部14,火焰筒头部14包括预燃级20和主燃级39,火焰筒头部14,如图3所示。  Upstream of the combustion zone 6 of the pre-combustion stage is the flame tube head 14, which includes the pre-combustion stage 20 and the main combustion stage 39, the flame tube head 14, as shown in FIG. 3 . the

主燃级33包括主燃级喷嘴31、主燃级预混预蒸发段21、主燃级头部整体端壁12和主燃级头部整体导流板13。主燃级预混预蒸发段21通过主燃级头部整体端壁12与火焰筒外壁15和火焰筒内壁16相连接,连接方式可以是焊接或螺纹或螺栓。主燃级预混预蒸发段21如图4和图5所示,由主燃级预混预蒸发环管28和主燃级喷嘴雾化空气进入管29组成。主燃级预混预蒸发环管28上的进气孔形状可以是圆孔或半孔或方孔或槽,开孔的角度为-90~90度。具体实施方案如图4和图5所示,以主燃级预混预蒸发环管28上的进气孔为圆孔为例。安装时,将主燃级喷嘴雾化空气进入管29与主燃级预混预蒸发环管28采用整体制造或螺纹或螺栓或焊接的连接方式,组合成主燃级预混预蒸发段21,即可完成主燃级预混预蒸发段21的安装。  The main combustion stage 33 includes the main combustion stage nozzle 31 , the main combustion stage premixing and pre-evaporation section 21 , the main combustion stage head integral end wall 12 and the main combustion stage head integral deflector 13 . The premixing and pre-evaporating section 21 of the main combustion stage is connected to the outer wall 15 of the flame tube and the inner wall 16 of the flame tube through the integral end wall 12 of the head of the main combustion stage, and the connection method can be welding, thread or bolt. The premixing and pre-evaporation section 21 of the main combustion stage is shown in FIG. 4 and FIG. 5 . The shape of the air inlet hole on the main combustion stage premixed pre-evaporator ring pipe 28 can be a round hole, a half hole, a square hole or a groove, and the opening angle is -90 to 90 degrees. The specific implementation is shown in Fig. 4 and Fig. 5, taking the air inlet hole on the premixing pre-evaporation ring pipe 28 of the main combustion stage as a circular hole as an example. During installation, the atomized air inlet pipe 29 of the main combustion stage nozzle and the main combustion stage premixed pre-evaporation ring pipe 28 are combined into a main combustion stage premixed pre-evaporation section 21 by integral manufacturing or threaded or bolted or welded connections. The installation of the premixing and preevaporating section 21 of the main combustion stage can be completed. the

预燃级20包括预燃级旋流器组件22、预燃级喷嘴30、预燃级头部端壁23、预燃级头部导流板24,预燃级20如图6和图7所示,预燃级旋流器组件22如图8和图9所示。预燃级旋流器组件22通过预燃级头部端壁23与主燃级预混预蒸发段内环29相连接。预燃级头部端壁23与主燃级预混预蒸发段内环29的连接方式可采用整体制造或螺纹或螺栓或焊接的方式。预燃级旋流器组件22采用的旋流器的级数1≤n≤5。每级旋流器可采用旋流器的结构可以是轴向旋流器,也可以是径向旋流器,也可以是切向旋流器。当预燃级旋流器组件22的级数n=1时,可采用焊接或螺栓或螺纹的连接方式将旋流器直接与预燃级头部端壁23连接;当预燃级旋流器组件18的级数1<n≤5时,在保证各级旋流器同轴的同时,采用焊接或螺栓或螺纹的连接方式将各级旋流器先连接成一个整体,组成预燃级旋流器组件22后再与预燃级头部端壁23连接。在具体实施方案中,以预燃级旋流器组件22采用二级旋流器方案为例,如图6、图7、图8和图9所示,预燃级旋流器组件22包括预燃级一级旋流器25、预燃级一级旋流器压板26和预燃级二级旋流器27。安装时,首先采用整体制造或螺纹或螺栓或焊接的方式将预燃级头部端壁23与主燃级预混预蒸发环管28连接在一起;然后将预燃级头部导流板24采用螺纹或螺栓或焊接的方式与预燃级头部端壁23相连接;在保证预燃级一级旋流器25与预燃级二级旋流器27同轴的同时,采用焊接或螺纹或 螺栓连接的方式,使预燃级一级旋流器压板26与预燃级二级旋流器27连接在一起,并且将预燃级一级旋流器25夹在预燃级一级旋流器压板26与预燃级二级旋流器27之间,使三个部件连接成为一个整体组成预燃级旋流器组件22;然后采用焊接或螺纹或螺栓连接的方式将预燃级旋流器组件22固定到预燃级头部端壁23上,通过预燃级头部端壁23把预燃级旋流器组件22与主燃级预混预蒸发环管28的内环相连接,将预燃级旋流器组件22与主燃级预混预蒸发段21连接固定在一起,从而完成预燃级20的安装。  The pre-combustion stage 20 includes a pre-combustion stage swirler assembly 22, a pre-combustion stage nozzle 30, a pre-combustion stage head end wall 23, and a pre-combustion stage head deflector 24. The pre-combustion stage 20 is shown in Figures 6 and 7 As shown, the pre-combustion stage swirler assembly 22 is shown in FIGS. 8 and 9 . The pre-combustion stage swirler assembly 22 is connected to the inner ring 29 of the main combustion stage premixing and pre-evaporation section through the pre-combustion stage head end wall 23 . The connection mode between the head end wall 23 of the pre-combustion stage and the inner ring 29 of the pre-mixing and pre-evaporation section of the main combustion stage can be integrally manufactured or threaded, bolted or welded. The number of stages of the swirlers used by the pre-combustion stage swirler assembly 22 is 1≤n≤5. Each cyclone can adopt the structure of the cyclone, which can be an axial cyclone, a radial cyclone, or a tangential cyclone. When the number of stages of the pre-combustion level swirler assembly 22 is n=1, the swirler can be directly connected to the pre-combustion level head end wall 23 by welding, bolts or threads; when the pre-combustion level swirler When the number of stages of the component 18 is 1<n≤5, while ensuring the coaxiality of the cyclones at all levels, the cyclones at all levels are first connected into a whole by welding, bolts or threads to form a pre-combustion stage cyclone The flow device assembly 22 is then connected to the end wall 23 of the pre-combustion stage head. In a specific embodiment, taking the pre-combustion stage cyclone assembly 22 as an example using a secondary cyclone solution, as shown in Figure 6, Figure 7, Figure 8 and Figure 9, the pre-combustion stage cyclone assembly 22 includes a pre-combustion stage cyclone The primary cyclone 25 of the combustion stage, the pressure plate 26 of the primary cyclone of the pre-combustion stage and the secondary cyclone 27 of the pre-combustion stage. During installation, the pre-combustion stage head end wall 23 and the main combustion stage premixed pre-evaporation ring pipe 28 are connected together by integral manufacturing or threaded or bolted or welded; then the pre-combustion stage head deflector 24 It is connected with the end wall 23 of the head of the pre-combustion stage by thread, bolt or welding; while ensuring that the primary cyclone 25 of the pre-combustion stage is coaxial with the secondary cyclone 27 of the pre-combustion stage, welding or threaded Or the way of bolt connection, so that the pressure plate 26 of the pre-combustion stage primary cyclone is connected with the pre-combustion stage secondary cyclone 27, and the pre-combustion stage primary cyclone 25 is clamped between the pre-combustion stage primary cyclone Between the pressure plate 26 of the flow device and the secondary cyclone 27 of the pre-combustion stage, the three parts are connected as a whole to form the pre-combustion stage cyclone assembly 22; then the pre-combustion stage cyclone is welded or threaded or bolted The swirler assembly 22 is fixed to the end wall 23 of the head of the pre-combustion stage, and the swirler assembly 22 of the pre-combustion stage is connected to the inner ring of the pre-mixing and pre-evaporating ring pipe 28 of the main combustion stage through the end wall 23 of the head of the pre-combustion stage , connect and fix the pre-combustion stage swirler assembly 22 and the main combustion stage premixing and pre-evaporation section 21 , thereby completing the installation of the pre-combustion stage 20 . the

在主燃级预混预蒸发段21与预燃级旋流器组件22安装完成后,在对应位置插入主燃级喷嘴31和预燃级喷嘴30,从而完成火焰筒头部14的安装。  After the main combustion stage premixing pre-evaporation section 21 and the precombustion stage swirler assembly 22 are installed, the main combustion stage nozzle 31 and the precombustion stage nozzle 30 are inserted at the corresponding positions, thereby completing the installation of the flame tube head 14 . the

如图1和图2所示,预燃级喷嘴30与主燃级喷嘴31都安装在燃油喷嘴座32上,组合成一个整体的燃油喷嘴11,在完成火焰筒头部14的安装后,从燃烧室外机匣9的开口处伸入燃烧室中,插入对应位置,从而完成燃烧室的安装。预燃级喷嘴30和主燃级喷嘴31采用的单个燃油喷嘴(34)可以是压力雾化喷嘴,可以是气动雾化喷嘴,也可以是组合式喷嘴。具体实施方案中的燃油喷嘴11结构如图11所示。预燃级喷嘴30与预燃级一级旋流器25相对应,并且预燃级喷嘴30的轴线与预燃级一级旋流器25的轴线相重合。主燃级喷嘴31位于主燃级喷嘴雾化空气进入管29入口,并与主燃级喷嘴雾化空气进入管29同轴,主燃级喷嘴31采用在同一圆周上设置多个单个燃油喷嘴34的喷射方式,该圆周的圆心位于预燃级喷嘴30的轴线上,主燃级喷嘴31采用的单个燃油喷嘴34的数量与主燃级喷嘴雾化空气进入管29的数量相对应,主燃级喷嘴31采用的单个燃油喷嘴34的数量0<p≤50,单个燃油喷嘴34的喷射线与圆周的切角A为-90~90度,主燃级喷嘴31的喷射示意如图12所示。  As shown in Figures 1 and 2, the pre-combustion stage nozzle 30 and the main combustion stage nozzle 31 are all installed on the fuel nozzle seat 32 to form a whole fuel nozzle 11. After the installation of the flame tube head 14 is completed, from The opening of the casing 9 outside the combustion chamber stretches into the combustion chamber and is inserted into the corresponding position, thereby completing the installation of the combustion chamber. The single fuel nozzle (34) adopted by the pre-combustion stage nozzle 30 and the main combustion stage nozzle 31 can be a pressure atomization nozzle, a pneumatic atomization nozzle, or a combined nozzle. The structure of the fuel nozzle 11 in the specific embodiment is shown in FIG. 11 . The pre-combustion stage nozzle 30 corresponds to the pre-combustion stage primary swirler 25 , and the axis of the pre-combustion stage nozzle 30 coincides with the axis of the pre-combustion stage primary swirler 25 . The main combustion stage nozzle 31 is located at the inlet of the main combustion stage nozzle atomization air inlet pipe 29, and is coaxial with the main combustion stage nozzle atomization air inlet pipe 29. The main combustion stage nozzle 31 adopts a plurality of single fuel nozzles 34 arranged on the same circumference The injection method, the center of the circle is located on the axis of the pre-combustion stage nozzle 30, the number of single fuel nozzles 34 used by the main combustion stage nozzle 31 corresponds to the number of the main combustion stage nozzle atomized air entering the pipe 29, the main combustion stage The number of single fuel nozzles 34 used in the nozzle 31 is 0 < p ≤ 50, and the cutting angle A between the injection line of a single fuel nozzle 34 and the circumference is -90 to 90 degrees. The injection diagram of the main combustion stage nozzle 31 is shown in FIG. the

燃烧室进口气流1进入燃烧室后,经过分流式扩压器8的减速扩压后分为三股:火焰筒头部气流2、燃烧室外环腔气流3和燃烧室内环腔气流4,以满足燃烧室各部分对空气流量的需求,合理组织燃烧室内流场,便于高效稳定的组织燃烧。  After the inlet airflow 1 of the combustion chamber enters the combustion chamber, it is divided into three streams after being decelerated and diffused by the split diffuser 8: the airflow 2 at the head of the flame tube, the airflow 3 outside the combustion chamber and the airflow 4 inside the combustion chamber to meet the The demand for air flow in each part of the combustion chamber, the reasonable organization of the flow field in the combustion chamber, facilitates the efficient and stable organization of combustion. the

火焰筒头部气流2全部为燃烧用气,占燃烧室进口气流1的40%~80%,除了0%~25%的火焰筒头部气流2被用于预燃级头部端壁23和主燃级头部整体端壁12的冷却外,其余分别由预燃级20和主燃级33供入,用于预燃级20和主燃级33对应燃油的雾化和燃烧,预燃级20所需气量占全部燃烧气量的10%~40%,其余由主燃级39供入。预燃级20所需燃油经预燃级喷嘴30喷出后,被来自预燃级旋流器组件22的空气旋流剪切破碎,形成油雾,然后进入由预燃级旋流器组件22的空气旋流形成的低速回流区——预燃级燃烧区域6形成扩散燃烧。预燃级喷嘴30可以是压力雾化喷嘴,也可以是气动雾化喷嘴,也可以是组合式喷嘴,预燃级喷嘴30的选择依靠燃油在预燃级喷嘴30结合来自预燃级旋流器组件22的空 气旋流的共同作用下的雾化和散布效果决定:雾化和散布效果越好,油雾分布越均匀,越利于在预燃级燃烧区域6内组织高效稳定低污染的燃烧。主燃级33所需的燃油经主燃级喷嘴31喷出后,首先在经过主燃级喷嘴雾化空气进入管29的气流作用下雾化形成油气混合气,然后流入主燃级预混预蒸发环管28,雾化后的油气混气在主燃级预混预蒸发环管28中蒸发和散布,在主燃级预混预蒸发段21的出口处形成均匀的油气混合气射流,该油气混合气射流在预燃级火焰的引燃下被点燃,形成主燃级燃烧区域7。主燃级喷嘴31位于主燃级喷嘴雾化空气进入管29入口,并与主燃级喷嘴雾化空气进入管29同轴,主燃级喷嘴31采用在同一圆周上设置多个燃油喷嘴的喷射方式,该圆周的圆心位于预燃级喷嘴30的轴线上,采用的喷嘴数量与主燃级喷嘴雾化空气进入管29的数量相对应,采用的燃油喷嘴数量0<p≤50单个喷嘴的喷射线与圆周的切角A为-90~90度。主燃级喷嘴31可以是压力雾化喷嘴,也可以是气动雾化喷嘴,也可以是组合式喷嘴,主燃级喷嘴的个数和喷射角度的选择依靠燃油在来自主燃级喷嘴雾化空气进入管29的雾化空气和来自主燃级预混预蒸发环管28的蒸发掺混气流的共同作用下,在主燃级预混预蒸发段21出口形成的油气混合气的均匀程度决定:形成的油气混合气越均匀,越利于在主燃级燃烧区域7内组织快速高效稳定低污染的燃烧。  The flame tube head airflow 2 is all combustion gas, accounting for 40% to 80% of the combustion chamber inlet airflow 1, except that 0% to 25% of the flame tube head airflow 2 is used for the pre-combustion stage head end wall 23 and Except for the cooling of the integral end wall 12 of the head of the main combustion stage, the rest are supplied by the pre-combustion stage 20 and the main combustion stage 33 respectively, and are used for the atomization and combustion of fuel corresponding to the pre-combustion stage 20 and the main combustion stage 33, and the pre-combustion stage 20 The required gas volume accounts for 10% to 40% of the total combustion gas volume, and the rest is supplied by the main combustion stage 39 . After the fuel oil required by the pre-combustion stage 20 is sprayed out by the pre-combustion stage nozzle 30, it is sheared and broken by the air swirl flow from the pre-combustion stage swirler assembly 22 to form oil mist, and then enters the pre-combustion stage swirler assembly 22 The low-velocity recirculation zone formed by the air swirl—the pre-combustion stage combustion zone 6 forms diffusion combustion. The pre-combustion nozzle 30 can be a pressure atomization nozzle, a pneumatic atomization nozzle, or a combined nozzle. The atomization and dispersion effect under the combined action of the air swirl of the component 22 determines: the better the atomization and dispersion effect, the more uniform the oil mist distribution, the more conducive to organizing efficient, stable and low-pollution combustion in the pre-combustion stage combustion area 6. After the fuel oil required by the main combustion stage 33 is sprayed through the main combustion stage nozzle 31, it is first atomized under the action of the airflow passing through the main combustion stage nozzle atomizing air inlet pipe 29 to form an oil-air mixture, and then flows into the main combustion stage premixed premixed gas. Evaporation ring 28, the atomized oil-air mixture evaporates and spreads in the main combustion stage premixing pre-evaporation ring 28, and forms a uniform oil-air mixture jet at the outlet of the main combustion stage premixing pre-evaporation section 21. The jet of oil-air mixture is ignited under the ignition of the pre-combustion stage flame to form the combustion zone 7 of the main combustion stage. The main combustion stage nozzle 31 is located at the entrance of the main combustion stage nozzle atomization air inlet pipe 29, and is coaxial with the main combustion stage nozzle atomization air inlet pipe 29. method, the center of the circle is located on the axis of the pre-combustion stage nozzle 30, the number of nozzles used corresponds to the number of atomized air inlet pipes 29 of the main combustion stage nozzle, and the number of fuel nozzles used is 0<p≤50 The injection of a single nozzle The cutting angle A between the line and the circumference is -90 to 90 degrees. The main combustion stage nozzle 31 can be a pressure atomization nozzle, it can also be a pneumatic atomization nozzle, and it can also be a combined nozzle. Under the joint action of the atomized air entering the pipe 29 and the vaporized mixed gas flow from the premixed pre-evaporation ring pipe 28 of the main combustion stage, the uniformity of the oil-air mixture formed at the outlet of the premixed preevaporation section 21 of the main combustion stage determines: The more uniform the oil-air mixture formed, the more conducive it is to organize rapid, efficient, stable and low-pollution combustion in the combustion zone 7 of the main combustion stage. the

燃烧室外环腔气流3包括火焰筒外壁13的冷却用气和火焰筒外壁掺混孔15的掺混用气。燃烧室内环腔气流4包括火焰筒内壁14的冷却用气和火焰筒内壁掺混孔16的掺混用气。其中火焰筒外壁13或火焰筒内壁14的冷却气占燃烧室进口气流1的0%~20%,火焰筒外壁掺混孔15或火焰筒内壁掺混孔16的掺混用气占燃烧室进口气流1的10%~30%。  The airflow 3 of the annular cavity outside the combustion chamber includes the cooling gas of the outer wall 13 of the flame tube and the gas for mixing in the mixing holes 15 of the outer wall of the flame tube. The annular cavity airflow 4 in the combustion chamber includes the cooling gas of the inner wall 14 of the flame tube and the mixing gas of the mixing hole 16 of the inner wall of the flame tube. Wherein the cooling gas of the outer wall 13 of the flame tube or the inner wall 14 of the flame tube accounts for 0% to 20% of the inlet airflow 1 of the combustion chamber, and the mixing gas of the mixing hole 15 of the outer wall of the flame tube or the mixing hole 16 of the inner wall of the flame tube accounts for 0% to 20% of the inlet airflow of the combustion chamber. 10% to 30% of 1. the

具体实施方案的燃烧室整体结构和燃油喷嘴结构如图10、图11和图12所示。图10为火焰筒结构示意,图11为此时采用的燃油喷嘴11的结构示意,图12为主燃级喷嘴31喷射示意。如图10所示,火焰筒头部14通过主燃级头部整体端壁12与火焰筒外壁15与火焰筒内壁16相连接。火焰筒头部14由预燃级20和主燃级33组成:主燃级33包括主燃级喷嘴31、主燃级预混预蒸发段21、主燃级头部整体端壁12和主燃级头部整体导流板13,主燃级预混预蒸发段21如图4和图5所示;预燃级20包括预燃级旋流器组件22、预燃级喷嘴35、预燃级头部端壁23、预燃级头部导流板24,预燃级旋流器组件22如图8和9所示。预燃级旋流器组件22与主燃级预混预蒸发段21同轴,此时采用的燃油喷嘴11如图11所示,预燃级喷嘴30与预燃级一级旋流器25相对,主燃级喷嘴31与主燃级喷嘴雾化空气进入孔29对应。当航空发动机工作在低功率状态时,燃烧室只有预燃级20供油,主燃级33只有空气经过而不供油,控制此时的油气比在贫油范围,在预燃级燃烧区6内形成扩散燃烧,从而保证了发动机燃烧室可靠的稳定性和起动特性,并降低CO和UHC污染排放。当 航空发动机工作在高功率状态时,预燃级20和主燃级33同时供油,预燃级20在预燃级燃烧区6内形成扩散燃烧,主燃级33在预燃级燃烧区6的外围形成主燃级燃烧区域7。主燃级33采用切向供油的预混预蒸发方式,一方面可以将主燃级33的所需的燃油在主燃级预混预蒸发段21内快速均匀的混合形成油气混合气,该混合气进入火焰筒后可以快速的较好的燃烧干净,从而减少NOx的生成,另一方面可以将预燃级未烧完的CO和UHC燃烧干净。由此可见预混预蒸发燃烧室在航空发动机宽广的工作范围内在保证高效稳定燃烧的同时能有效的降低燃烧室的污染排放,在掺混孔气流的辅助下也可以获得较好的出口温度分布性能。  The overall structure of the combustion chamber and the fuel nozzle structure of the specific embodiment are shown in Figure 10, Figure 11 and Figure 12. FIG. 10 is a schematic diagram of the structure of the flame tube, FIG. 11 is a schematic diagram of the structure of the fuel nozzle 11 used at this time, and FIG. 12 is a schematic diagram of the injection of the main fuel stage nozzle 31 . As shown in FIG. 10 , the flame tube head 14 is connected to the flame tube outer wall 15 and the flame tube inner wall 16 through the integral end wall 12 of the main stage head. The flame tube head 14 is composed of a pre-combustion stage 20 and a main combustion stage 33: the main combustion stage 33 includes a main combustion stage nozzle 31, a main combustion stage premixing pre-evaporation section 21, a main combustion stage head integral end wall 12 and a main combustion stage The overall deflector 13 of the stage head, the premixing and pre-evaporation section 21 of the main combustion stage are shown in Figure 4 and Figure 5; The head end wall 23, the pre-combustion stage head deflector 24, and the pre-combustion stage swirler assembly 22 are shown in FIGS. 8 and 9 . The pre-combustion stage swirler assembly 22 is coaxial with the main combustion stage premixing pre-evaporation section 21, and the fuel nozzle 11 used at this time is shown in Figure 11, and the pre-combustion stage nozzle 30 is opposite to the pre-combustion stage primary swirler 25 , the main fuel stage nozzle 31 corresponds to the main fuel stage nozzle atomization air inlet hole 29 . When the aero-engine works in a low power state, only the pre-combustion stage 20 supplies fuel to the combustion chamber, and the main combustion stage 33 only passes through air without supplying fuel. Diffusion combustion is formed inside, thereby ensuring reliable stability and starting characteristics of the engine combustion chamber, and reducing CO and UHC pollution emissions. When the aero-engine is working in a high-power state, the pre-combustion stage 20 and the main combustion stage 33 supply oil simultaneously, the pre-combustion stage 20 forms diffusion combustion in the pre-combustion stage combustion zone 6, and the main combustion stage 33 is in the pre-combustion stage combustion zone 6 The periphery of the main combustion stage forms the combustion zone 7 of the main combustion stage. The main combustion stage 33 adopts the premixing and pre-evaporation method of tangential fuel supply. On the one hand, the fuel required by the main combustion stage 33 can be quickly and evenly mixed in the main combustion stage premixing and pre-evaporation section 21 to form an oil-air mixture. After the mixed gas enters the flame tube, it can be burned quickly and well, thereby reducing the formation of NOx. On the other hand, it can burn the unburned CO and UHC in the pre-combustion stage. It can be seen that the pre-mixed pre-evaporative combustor can effectively reduce the pollution emissions of the combustor while ensuring efficient and stable combustion within the wide operating range of the aero-engine, and can also obtain a better outlet temperature distribution with the assistance of the mixing hole airflow performance. the

本发明未详细阐述部分属于本领域公知常识。  Parts not described in detail in the present invention belong to common knowledge in the field. the

以上所述仅是本发明的优选实施方式,应当指出,对于本技术领域的普通技术人员来说,在不脱离本发明原理的前提下,还可以做出若干改进和润饰,这些改进和润饰也应视为本发明的保护范围。  The above is only a preferred embodiment of the present invention, it should be pointed out that, for those of ordinary skill in the art, without departing from the principle of the present invention, some improvements and modifications can also be made, and these improvements and modifications can also be made. It should be regarded as the protection scope of the present invention. the

Claims (8)

1. the premix and pre-evaporation combustion chamber of main combustible stage tangential oil supply; It is characterized in that: said combustion chamber is the monocycle cavity configuration; Adopt the fractional combustion mode, the burning gas consumption is all infeeded by pre-combustion grade and main combustion level, and pre-combustion grade adopts swirl stabilized diffusion flame burning organizational form; Main combustion level adopts the premix and pre-evaporation burning organizational form of tangential oil supply, and cold gas and mixed gas infeed from burner inner liner; The premix and pre-evaporation combustion chamber of said main combustible stage tangential oil supply mainly is made up of casing (10), fuel nozzle (11), burner inner liner head (14), burner inner liner outer wall (15) and burner inner liner inwall (16) in shunting diffuser (8), outer combustion case (9), the combustion chamber; Burner inner liner head (14) is made up of pre-combustion grade (20) and main combustion level (33): pre-combustion grade (20) comprises deflector (24) in pre-combustion grade swirler assembly (22), pre-combustion grade nozzle (30), pre-combustion grade head end wall (23) and the pre-combustion grade head; Pre-combustion grade (20) is utilized the low speed recirculating zone retention flame that is got into the rotational flow air generation of combustion chamber by pre-combustion grade swirler assembly (22); Pre-combustion grade swirler assembly (22) is connected with main combustion level premix and pre-evaporation endless tube (28) through pre-combustion grade head end wall (23); Pre-combustion grade nozzle (30) is positioned at pre-combustion grade swirler assembly (22); And coaxial with pre-combustion grade swirler assembly (22), deflector (24) links to each other with pre-combustion grade head end wall (23) in the pre-combustion grade head; Main combustion level (33) comprises main combustion level nozzle (31), main combustion level premix and pre-evaporation section (21), the main whole end wall (12) of combustion level head and the whole deflector (13) of main combustion level head; Main combustion level premix and pre-evaporation section (21) gets into pipe (29) by main combustion level premix and pre-evaporation endless tube (28) and main combustion level nozzle atomization air and forms; Main combustion level nozzle (31) is positioned at main combustion level nozzle atomization air and gets into pipe (29) inlet; And it is coaxial with main combustion level nozzle atomization air entering pipe (29); Main combustion level nozzle (31) is employed in the spray regime that a plurality of single fuel nozzles (34) are set on the same circumference; The center of circle of this circumference is positioned on the axis of pre-combustion grade nozzle (30), and the quantity of the single fuel nozzle (34) of main combustion grade nozzle (31) employing is corresponding with the quantity that (29) are managed in the entering of main combustion level nozzle atomization air, after the required fuel oil of main combustion level (33) fires level nozzle (31) ejection by the master; The aerodynamic atomization that is at first got into pipe (29) by main combustion level nozzle atomization air forms fuel-air mixture; Flow into a main combustion level premix and pre-evaporation endless tube (28) then, fuel-air mixture evaporates in main combustion level premix and pre-evaporation endless tube (28), and with the further blending of air; Form uniform fuel-air mixture jet gets in the burner inner liner in the exit of main combustion level premix and pre-evaporation endless tube (28); Under the igniting of pre-combustion grade flame, burn, main combustion level premix and pre-evaporation section (21) links to each other with burner inner liner inwall (16) with burner inner liner outer wall (15) through the main combustion level whole end wall of head (12), and the main combustion level whole deflector of head (13) links to each other with the main combustion level whole end wall of head (12); Pre-combustion grade nozzle (30) and main combustion level nozzle (31) all are connected on the fuel nozzle seat (32), form fuel nozzle (11), and fuel nozzle (11) links to each other with outer combustion case (9) through fuel nozzle seat (32).
2. premix and pre-evaporation combustion chamber according to claim 1; It is characterized in that: be provided with burner inner liner outer wall blending hole (17) at described burner inner liner outer wall (15) rear portion; Be provided with burner inner liner inwall blending hole (18) at described burner inner liner inwall (16) rear portion; Blending usefulness gas gets into burner inner liner from burner inner liner outer wall blending hole (17) and burner inner liner inwall blending hole (18) respectively, with control combustor exit Temperature Distribution.
3. premix and pre-evaporation combustion chamber according to claim 1 and 2; It is characterized in that: described shunting diffuser (8) is divided into three strands with combustion chamber inlet air flow (1): ring cavity air-flow (4) in ring cavity air-flow (3) and the combustion chamber outside burner inner liner head air-flow (2), the combustion chamber, and to satisfy the demand of combustion chamber each several part to air mass flow.
4. premix and pre-evaporation combustion chamber according to claim 1 and 2 is characterized in that: the single fuel nozzle (34) that said pre-combustion grade nozzle (30) and main combustion level nozzle (31) adopt is pressure atomized fog jet, pneumatic nozzle or combined nozzle.
5. premix and pre-evaporation combustion chamber according to claim 1 is characterized in that: progression 1≤n≤5 of the cyclone that said pre-combustion grade swirler assembly (22) adopts; It is axial swirler that every grade of cyclone adopts the structure of cyclone, or radial swirler, or the tangential swirl device; When the progression n=1 of pre-combustion grade swirler assembly (22), cyclone directly is connected with pre-combustion grade head end wall (23); When the progression 1<n of pre-combustion grade swirler assembly (22)≤5, cyclones at different levels connect into an integral body earlier, are connected with pre-combustion grade head end wall (23) after forming pre-combustion grade swirler assembly (22) again.
6. premix and pre-evaporation combustion chamber according to claim 1; It is characterized in that: said main combustion level nozzle (31) is employed in the spray regime that a plurality of single fuel nozzles (34) are set on the same circumference; The center of circle of this circumference is positioned on the axis of pre-combustion grade nozzle (30); The quantity of the single fuel nozzle (34) that adopts is corresponding with the quantity that main combustion level nozzle atomization air gets into pipe (29); Quantity 0<p≤50 of single fuel nozzle (34), the spray line of single fuel nozzle (34) and the corner cut A of circumference are-90~90 degree.
7. premix and pre-evaporation combustion chamber according to claim 1; It is characterized in that: the burning usefulness gas of said combustion chamber is all infeeded by burner inner liner head (14); Burner inner liner head air-flow accounts for 40%~80% of combustion chamber inlet air flow: the cooling institute air demand of pre-combustion grade head end wall (23) and the main combustion level whole end wall of head (12) accounts for 0%~25% of burner inner liner head air-flow; Pre-combustion grade (20) institute air demand accounts for 10%~40% of whole burning tolerance, and all the other main combustion level premix and pre-evaporation sections (21) by main combustion level (33) infeed.
8. premix and pre-evaporation combustion chamber according to claim 1; It is characterized in that: the burner inner liner outer wall (15) of said combustion chamber and the type of cooling of burner inner liner inwall (16) adopt the air film cooling, disperse the cooling or the compound type of cooling, wall surface temperature is controlled the life-span that prolongs burner inner liner.
CN201010034141A 2010-01-15 2010-01-15 Main combustible stage tangential oil supply premix and pre-evaporation combustion chamber Expired - Fee Related CN101799174B (en)

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CN102032597B (en) * 2010-11-29 2012-07-04 北京航空航天大学 Premixing pre-vaporization combustion chamber for main combustible stage of discrete pipe
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CN102242940B (en) * 2011-07-29 2014-02-12 北京航空航天大学 A low-pollution combustor with three-stage premixed and preevaporated structure
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CN112113242B (en) * 2020-11-09 2024-11-26 南昌航空大学 A trapped vortex combustion chamber with a combined configuration of inner and outer concave cavities
CN112963273B (en) * 2021-03-03 2022-07-01 中国人民解放军空军工程大学 Self-air-entraining kerosene pre-combustion cracking activation device and method for concave cavity flame stabilizer
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CN114001375B (en) * 2021-11-12 2022-09-06 西安热工研究院有限公司 A rotary detonation combustion chamber with a pre-combustion chamber
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