CN102242939B - Prefilming three-stage pre-mixing and pre-evaporating low-pollution combustor - Google Patents
Prefilming three-stage pre-mixing and pre-evaporating low-pollution combustor Download PDFInfo
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一种预膜式分三级预混预蒸发的低污染燃烧室,包括扩压器、燃烧室外机匣、燃烧室内机匣、火焰筒外壁、火焰筒内壁和燃烧室头部;燃烧用空气全部由燃烧室头部进入火焰筒,采用分级燃烧方案,分为预燃级一级和主燃级两级;主燃级采用预混燃烧方式,预燃级采用旋流稳定的扩散燃烧方式。主燃级结构上分为两级,避免了主燃级一级的情况下,转级时主级油气混合变差导致的污染排放的增加,在不影响稳定燃烧的同时降低了30%工况下的污染物排放。主燃级第二级采取预膜式喷嘴,使燃油分布更加均匀,相比离散喷嘴污染物在大工况下进一步降低。本发明在不影响燃烧稳定性的同时,降低了航空发动机燃烧室的整个着陆起飞循环的污染排放。
A pre-film type low-pollution combustion chamber with three stages of premixing and pre-evaporation, including a diffuser, a casing outside the combustion chamber, a casing inside the combustion chamber, the outer wall of the flame tube, the inner wall of the flame tube, and the head of the combustion chamber; all air used for combustion is Entering the flame cylinder from the head of the combustion chamber, a staged combustion scheme is adopted, which is divided into a pre-combustion stage and a main combustion stage; The structure of the main combustion stage is divided into two stages, which avoids the increase of pollution emissions caused by the poor oil-gas mixing of the main stage when the main stage is changed to one stage, and reduces the working condition by 30% without affecting stable combustion emissions of pollutants. The second stage of the main combustion stage adopts pre-film nozzles to make the fuel distribution more uniform, and further reduce pollutants under large working conditions compared with discrete nozzles. The invention reduces the pollution emission of the whole landing and take-off cycle of the aero-engine combustion chamber without affecting the combustion stability.
Description
技术领域technical field
本发明涉及一种利用预混预蒸发燃烧技术的航空燃气轮机低污染燃烧室。采用分级燃烧的模式,主燃级采用预混燃烧的方式,主要用于降低大工况下的污染排放;预燃级采用扩散燃烧的方式,在保证燃烧室稳定燃烧,主燃级采用分两级的预混预蒸发燃烧的方式,降低航空发动机整个LTO循环的污染排放。The invention relates to a low-pollution combustor of an aviation gas turbine utilizing premixed pre-evaporative combustion technology. The staged combustion mode is adopted, and the main combustion stage adopts the premixed combustion method, which is mainly used to reduce pollution emissions under large working conditions; the pre-combustion stage adopts the diffusion combustion method to ensure stable combustion in the combustion chamber, and the main combustion stage uses two The way of pre-mixed pre-evaporative combustion can reduce the pollution emission of the entire LTO cycle of the aero-engine.
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,仍然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 there are still a lot of problems and challenges for modern aero-engine combustors. The development and application of new materials, new processes, new structures, and new concepts It is the source to ensure its continuous progress.
现代民用航空发动机燃烧室的主要发展趋势是低污染燃烧。民用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 Environmental Protection)标准对污染排放物的规定已经非常严格,特别是对NOx污染排放要求;而最新的CAEP8标准提出了将NOx的排放在CAEP6的排放标准上降低15%,随着航空业的迅猛发展和人们环保意识的不断提高,未来对燃气轮机燃烧室污染排放会提出更高的要求。The main development trend of modern civil aeroengine combustors is low-pollution combustion. Combustion chambers of civil aeroengines must meet increasingly stringent aeroengine pollution emission standards. The currently adopted CAEP6 (Committee on Aviation Environmental Protection) standard has very strict regulations on pollutant emissions, especially the requirements for NOx pollution emissions; and the latest CAEP8 standard proposes to reduce NOx emissions by 15% from the CAEP6 emission standards , with the rapid development of the aviation industry and the continuous improvement of people's awareness of environmental protection, higher requirements will be put forward for the pollution emissions of gas turbine combustors in the future.
美国航空发动机的两个著名公司GE和PW对低污染燃烧室早已着手研究,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RQL(富油燃烧-淬熄-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 Mixing Combustion,贫油直接混合燃烧室)技术为其GEnx发动机研制的TAPS(Twin Annular PremixingSwirler)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%。GE公司申请了多项美国专利:申请号6363726、6389815、6354072、6418726、0178732、6381964和6389815,所有这些专利都是预燃级采用扩散燃烧、主燃级采用预混燃烧的燃烧组织方式,目的是降低排放指数最大的大工况下的NOx排放。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 already started research on low-pollution combustion chambers. GE first developed a double-ring cavity low-pollution combustion DAC (for GE90 and CFM56), and PW company adopted RQL (oil-rich combustion-quenching -Rich burn-Quench-Lean burn, 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. GE has applied for a number of U.S. patents: application numbers 6363726, 6389815, 6354072, 6418726, 0178732, 6381964 and 6389815. All of these patents use diffusion combustion in the pre-combustion stage and premixed combustion in the main combustion stage. It is to reduce the NOx emission under the large working condition with the largest emission index. 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.
中国的北京航空航天大学对低污染燃烧室也申请了200910238793.X、201010101574.X、201010034141.7、201010277014.X等多项专利,采用的方案是预燃级采用扩散燃烧方式,主燃级采用预混燃烧方式,主燃级为环形结构,轴向或径向供油,采用多点喷射或是预膜雾化方式,目的是降低大工况下的NOx排放,从而使整个LTO循环的NOx的排放得到降低,但要进一步降低整个LTO循环的NOx的排放水平难度较大。China's Beijing University of Aeronautics and Astronautics has also applied for a number of patents such as 200910238793.X, 201010101574.X, 201010034141.7, 201010277014.X and other low-pollution combustion chambers. The scheme adopted is that the pre-combustion stage adopts the diffusion combustion method, and the main combustion stage adopts premixing Combustion mode, the main combustion stage is a ring structure, axial or radial oil supply, using multi-point injection or pre-film atomization, the purpose is to reduce NOx emissions under large working conditions, so that the NOx emissions of the entire LTO cycle However, it is difficult to further reduce the NOx emission level of the whole LTO cycle.
以上所述的专利,都是针对在大工况下降低污染排放,而根据国际民航组织(International Civil Aviation Organization,ICAO)规定的一个标准循环下的排放物指数,用LTO Emission来表达这个参数,计算如下式:The above-mentioned patents are all aimed at reducing pollution emissions under large working conditions, and according to the emission index under a standard cycle stipulated by the International Civil Aviation Organization (International Civil Aviation Organization, ICAO), this parameter is expressed by LTO Emission, The calculation is as follows:
由上式可知,LTO Emission跟四个工况下的NOx排放量有关,即既与大工况下的NOx排放有关,还与小工况下的NOx排放有关。It can be seen from the above formula that LTO Emission is related to NOx emissions under four working conditions, that is, not only related to NOx emissions under large working conditions, but also related to NOx emissions under small working conditions.
标准LTO循环中的运行模式、每个运行模式下的推力和运行时间,如下表所示。The operating modes in the standard LTO cycle, the thrust and operating time in each operating mode, are shown in the table below.
表1ICAO规定的LTO循环中的运行模式和时间Table 1 Operation modes and times in the LTO cycle specified by ICAO
常规或者现役的推力在140KN的CFM56-5B/3发动机的NOx排放如下表,数据来源于ICAO Emission data bank。The NOx emissions of CFM56-5B/3 engines with a thrust of 140KN in conventional or active service are shown in the table below, and the data comes from ICAO Emission data bank.
表2CFM56-5B/3的NOx排放水平Table 2 NOx emission levels of CFM56-5B/3
燃烧室采用分级燃烧,预燃级为扩散燃烧方式,主燃级为预混燃烧方式,降低了大工况下的NOx排放,可以达到的NOx排放如下表所示:The combustion chamber adopts staged combustion, the pre-combustion stage adopts the diffusion combustion method, and the main combustion stage adopts the pre-mixed combustion method, which reduces NOx emissions under large working conditions. The NOx emissions that can be achieved are shown in the following table:
表3主燃级采用预混燃烧可以达到的NOx排放水平Table 3 NOx emission levels that can be achieved by premixed combustion in the main combustion stage
在小工况(地面慢车、进场)下,虽然NOx排放指数较低,根据表1可知小工况下的运行时间远远高于其他大工况,根据表3可知,当主燃级采用预混燃烧方式时,可以使大工况下的NOx排放指数得到大幅度降低,此时预燃级的NOx排放总量在整个LTO循环的污染排放排放中占的比重最大,因此要想进一步降低整个LTO循环的NOx排放,就需要考虑降低预燃级的NOx排放。Under small working conditions (ground idle, approach), although the NOx emission index is low, it can be seen from Table 1 that the running time under small working conditions is much higher than other large working conditions. According to Table 3, when the main combustion stage adopts When the co-combustion mode is used, the NOx emission index under large working conditions can be greatly reduced. At this time, the total NOx emission of the pre-combustion stage accounts for the largest proportion in the pollution emission of the entire LTO cycle. Therefore, in order to further reduce the overall For the NOx emission of the LTO cycle, it is necessary to consider reducing the NOx emission of the pre-combustion stage.
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 is controlled, and the uniformity of the equivalence ratio in the main combustion zone mainly depends on the uniformity of fuel atomization and oil-gas mixing.
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 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.
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,在大状态时,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。在小状态时,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 large state, due to the liquid mist diffusion combustion method, the local equivalence ratio of the combustion zone is always around 1, which far exceeds the range of equivalence ratio required for low-pollution combustion. At this time, although CO and UHC The emission is low, but the emission of NOx reaches the maximum. In the small state, the equivalence ratio of the combustion zone is very low, 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 not uniform, so for the conventional combustion chamber, it cannot meet the low pollution requirements in the entire engine working range.
发明内容Contents of the invention
本发明要解决的技术问题是:克服现有技术不足,运用预混预蒸发燃烧技术,提供了一种预膜式分三级预混预蒸发的低污染燃烧室,该燃烧室的主燃级采用预混燃烧方式,能在30%工况以上保持较低的污染排放;预燃级采用扩散燃烧的方式,在小工况下既能保证发动机稳定工作,从而降低了整个LTO循环中的污染排放。The technical problem to be solved by the present invention is: to overcome the deficiencies of the prior art and to provide a pre-film type low-pollution combustion chamber with three stages of pre-mixing and pre-evaporation by using the premixed pre-evaporation combustion technology. The main combustion stage of the combustion chamber The pre-mixed combustion method is adopted, which can maintain low pollution emissions above 30% of the working conditions; the pre-combustion stage adopts the diffusion combustion method, which can ensure the stable operation of the engine under small working conditions, thereby reducing the pollution in the entire LTO cycle emission.
本发明解决其技术问题所采用的技术方案是:预燃级采用扩散燃烧的方式,主燃级采用分两级预混燃烧的方式。所述燃烧室采用单环腔结构,它由燃烧室外机匣和燃烧室内机匣构成其外轮廓;外界空气通过扩压器进入,火焰筒外壁、火焰筒内壁和燃烧室头部组成燃烧区域,燃烧用空气全部由燃烧室头部进入火焰筒,掺混空气由火焰筒外壁上的外掺混孔和火焰筒内壁上的内掺混孔射入;所述燃烧室头部采用分级燃烧方案,分为主燃级和预燃级,主燃级外环通过头部整体端壁与火焰筒外壁和火焰筒内壁连接固定,主燃级内环腔和燃油喷嘴为一体;预燃级通过预燃级头部端壁与主燃级联接,并与主燃级同心;所述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,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;预燃级头部端壁连接于主燃级预混蒸发段内环和预燃级外环管上;其中预燃级旋流器包括预燃级外环管、预燃级文氏管、预燃级旋流器叶片;所述主燃级由预混预蒸发外环、预混预蒸发环内环、主燃级燃油环、预膜式喷嘴内环、预膜式喷嘴外环、主燃级外旋流器、主燃级内旋流器和预膜式喷嘴内旋流器构成,其中主燃级内旋流器与预膜式喷嘴内环、预混预蒸发环内环焊接在一起,构成了主燃级内环腔,主燃级外旋流器与预混预蒸发环外环一起构成主燃级外环,和预膜式喷嘴外环构成了主燃级外环腔,主级内外环腔在预膜式喷嘴之后合并成预混段;所述燃油喷嘴向燃烧室供给所有燃油,燃油喷嘴包括预燃级喷嘴、主燃级内喷嘴和预膜式喷嘴,燃油喷嘴从燃烧室头部的上游直接插入主燃级外环中;其中预燃级喷嘴为单个喷嘴,直接插入到预燃级喷嘴定位环下游内通道里,经过预燃级燃油管路的燃油通过预燃级喷嘴形成预燃级油雾,预燃级油雾打在预燃级旋流器文氏管内壁面上形成油膜,在经过预燃级内通道的来流作用下进行雾化,在预燃级出口进行扩散燃烧;主燃级内喷嘴由主燃级内燃油通道和主燃级内直射喷孔组成,主燃级内燃油环和预混预蒸发环内环一起构成主燃级燃油内通道,为一环形结构;预混预蒸发环内环上沿周向均匀开有多个主燃级内直射喷孔,燃油通过主燃级内燃油管进入主燃级燃油通道,然后经过主燃级内直射喷孔形成多股主燃级内环喷雾,向预混段喷射;主燃级内环油雾在主燃级内旋流的作用下进行蒸发和预混和掺混,在较短的几何尺寸内实现燃油快速蒸发并与空气均匀掺混,然后经过预混段进入主燃级出口进行预混燃烧,保证较低的污染排放;预膜式喷嘴由预膜式喷嘴内环、预膜式喷嘴外环和预膜式旋流器组成;燃油通过预膜式喷嘴,经过预膜式旋流器形成一层均匀主燃级油膜向预混段喷射;主燃级油膜在主燃级内外旋流的作用下进行蒸发和预混和掺混,在较短的几何尺寸内实现燃油快速蒸发并与空气均匀掺混,然后经过预混段进入主燃级出口进行预混燃烧,保证较低的污染排放。The technical solution adopted by the present invention to solve the technical problem is: the pre-combustion stage adopts the method of diffusion combustion, and the main combustion stage adopts the method of premixed combustion in two stages. The combustion chamber adopts a single-ring cavity structure, and its outer contour is composed of an outer casing of the combustion chamber and an inner casing of the combustion chamber; outside air enters through a diffuser, and the outer wall of the flame cylinder, the inner wall of the flame cylinder and the head of the combustion chamber form a combustion area. All the combustion air enters the flame tube from the head of the combustion chamber, and the mixed air is injected from the outer mixing hole on the outer wall of the flame tube and the inner mixing hole on the inner wall of the flame tube; the head of the combustion chamber adopts a staged combustion scheme, It is divided into main combustion stage and pre-combustion stage. The outer ring of the main combustion stage is connected and fixed with the outer wall of the flame tube and the inner wall of the flame tube through the overall end wall of the head. The inner ring cavity of the main combustion stage is integrated with the fuel nozzle; The end wall of the stage head is connected with the main combustion stage, and is concentric with the main combustion stage; The low-velocity recirculation area generated by the swirling air of the pre-combustion stage swirler assembly entering the combustion chamber stabilizes the flame, and the pre-combustion stage swirler assembly is connected to the inner ring of the pre-mixing pre-evaporation section of the main combustion stage through the end wall of the pre-combustion stage head ; The pre-combustion stage nozzle is located in the pre-combustion stage swirler assembly and is coaxial with the pre-combustion stage swirler assembly; the end wall of the pre-combustion stage head is connected to the inner ring of the pre-combustion stage premixing evaporation section and the outer ring of the pre-combustion stage On the ring pipe; wherein the pre-combustion level swirler includes the pre-combustion level outer ring pipe, the pre-combustion level Venturi tube, the pre-combustion level swirler vane; The inner ring of the evaporation ring, the main fuel oil ring, the inner ring of the pre-film nozzle, the outer ring of the pre-film nozzle, the outer swirler of the main combustion stage, the inner swirler of the main combustion stage and the inner swirler of the pre-film nozzle , where the main combustion stage inner swirler is welded with the pre-film nozzle inner ring and the premixing pre-evaporation ring inner ring to form the main combustion stage inner ring chamber, the main combustion stage outer swirler and the premixing pre-evaporation ring The outer ring together constitutes the outer ring of the main combustion stage, and the outer ring of the pre-film nozzle forms the outer ring cavity of the main combustion stage. The inner and outer ring chambers of the main stage are combined into a premixing section after the pre-film nozzle; All fuel is supplied, and the fuel nozzles include pre-combustion stage nozzles, main combustion stage inner nozzles and pre-film nozzles, and the fuel nozzles are directly inserted into the main combustion stage outer ring from the upstream of the combustion chamber head; the pre-combustion stage nozzles are single nozzles, Directly inserted into the inner channel downstream of the positioning ring of the pre-combustion stage nozzle, the fuel passing through the pre-combustion stage fuel pipeline forms a pre-combustion stage oil mist through the pre-combustion stage nozzle, and the pre-combustion stage oil mist hits the pre-combustion stage cyclone Venturi The oil film is formed on the inner wall of the tube, which is atomized under the action of the incoming flow through the inner channel of the pre-combustion stage, and diffused combustion is carried out at the outlet of the pre-combustion stage; The inner fuel ring of the main combustion stage and the inner ring of the premixing pre-evaporation ring together form the inner channel of the main combustion stage fuel, which is a ring structure; the inner ring of the premixing pre-evaporation ring is uniformly opened with multiple main combustion stages along the circumferential direction Inner direct-injection injection holes, the fuel enters the main combustion-stage fuel channel through the main-stage internal fuel pipe, and then passes through the main-stage internal direct-injection injection holes to form multiple main-stage inner-ring sprays, which are sprayed toward the premixing section; the main-stage inner ring The oil mist is evaporated and premixed under the action of the internal swirling flow of the main combustion stage, and the fuel is quickly evaporated and mixed with air in a relatively short geometric size, and then enters the outlet of the main combustion stage through the premixing section for pre-mixing. Co-combustion ensures low pollution The pre-film nozzle is composed of the pre-film nozzle inner ring, the pre-film nozzle outer ring and the pre-film swirler; the fuel passes through the pre-film nozzle and the pre-film swirler to form a layer of uniform main combustion The oil film of the main fuel stage is injected into the premixing section; the oil film of the main fuel stage is evaporated and premixed and mixed under the action of the internal and external swirling flow of the main fuel stage, and the fuel is quickly evaporated and mixed with the air in a relatively short geometric size, and then passed through The premixing section enters the outlet of the main combustion stage for premixed combustion to ensure lower pollution emissions.
本发明的原理如下:通过控制航空发动机燃烧室内燃烧区的当量比和均匀度来达到降低污染排放的目的。燃烧用空气全部从燃烧室头部进入火焰筒,使大部分的燃油和空气掺混均匀后再进入火焰筒燃烧,对控制燃烧区当量比降低污染排放有利。采用分级燃烧方案,在小工况下,只有预燃级供油工作,在中间工况下,主燃级一级和预燃级共同供油工作,在大工况下,主燃级和预燃级共同供油工作。在小工况下,只有预燃级供油工作,预燃级燃油经过预燃级喷嘴在预燃级出口处燃烧,为扩散燃烧方式;由于预燃级出口为较强的回流区,扩散燃烧的预燃级燃油在该强回流区内燃烧,因此保证了燃烧的稳定性;在中间工况下,主燃级和预燃级同时供油工作,主燃级一级燃油经过直射喷嘴进入旋流器的空气流道,在旋流作用下进行预先蒸发和与空气掺混,在主燃级出口处参与燃烧,为预混燃烧方式,避免主燃级不分级时由于照顾大工况导致的主燃级流量数太大而导致中间工况雾化和混合变差,保证中间工况的污染排放。在大工况下,主燃级和预燃级同时供油工作,而主燃级的燃油流量占大部分,污染物排放主要受主燃级控制,而主燃级采用的均匀油气混合气预混燃烧,使燃烧区的当量比在污染排放较低的范围内,从而控制了大工况下的污染排放。因此,该型燃烧室确保了航空发动机在宽的工作范围内拥有低污染排放,从而进一步降低了整个LTO循环下的NOx排放,同时保证了燃烧稳定性。The principle of the invention is as follows: the purpose of reducing pollution discharge is achieved by controlling the equivalence ratio and uniformity of the combustion zone in the combustion chamber of the aero-engine. All the air for combustion enters the flame tube from the head of the combustion chamber, so that most of the fuel and air are mixed evenly before entering the flame tube for combustion, which is beneficial to controlling the equivalent ratio of the combustion zone and reducing pollution emissions. The staged combustion scheme is adopted. Under small working conditions, only the pre-combustion stage works for fuel supply. Combustion level common oil supply work. Under small working conditions, only the pre-combustion stage fuel supply works, and the pre-combustion stage fuel burns at the pre-combustion stage outlet through the pre-combustion stage nozzle, which is a diffusion combustion method; since the pre-combustion stage outlet is a strong recirculation zone, diffusion combustion The pre-combustion grade fuel burns in this strong recirculation zone, thus ensuring the stability of combustion; under the intermediate working condition, the main combustion stage and the pre-combustion stage are supplied with fuel at the same time, and the primary fuel oil of the main combustion stage enters the swivel nozzle through the direct injection nozzle. The air channel of the flow device is pre-evaporated and mixed with air under the action of swirling flow, and participates in combustion at the outlet of the main combustion stage. It is a pre-mixed combustion method to avoid the failure of the main combustion stage due to the consideration of large working conditions when the main combustion stage is not classified. The flow rate of the main combustion stage is too large, resulting in poor atomization and mixing in the intermediate working conditions, so as to ensure the pollution discharge in the intermediate working conditions. Under heavy working conditions, the main combustion stage and the pre-combustion stage work at the same time, and the fuel flow of the main combustion stage accounts for most of the fuel flow. Co-combustion enables the equivalent ratio of the combustion zone to be within the range of low pollution emissions, thereby controlling pollution emissions under large working conditions. Therefore, this type of combustor ensures that the aeroengine has low pollution emissions in a wide operating range, thereby further reducing NOx emissions under the entire LTO cycle, while ensuring combustion stability.
本发明与现有技术相比所具有的优点如下:Compared with the prior art, the present invention has the following advantages:
(1)本发明预燃级采用扩散燃烧和预混燃烧相结合的燃烧方式,通过将燃油分三级的方式达到两种燃烧方式共存的目的,在不影响燃烧室工作稳定性的同时,降低了全工况下的污染排放。(1) The pre-combustion stage of the present invention adopts a combustion method combining diffusion combustion and premixed combustion, and achieves the purpose of coexistence of the two combustion methods by dividing the fuel into three stages. Pollutant emissions under all working conditions.
(2)主燃级分为两级,避免了主燃级一级的情况下,转级时主级油气混合变差导致的污染排放的增加,可以将大工况下和小工况下的污染排放同时降低,从而进一步降低了整个LTO循环的污染排放。(2) The main combustion stage is divided into two stages, which avoids the increase of pollution emissions caused by the poor oil-gas mixing of the main stage when the main combustion stage is one-stage, and can reduce the pollution emissions under large and small working conditions. Pollution emissions are reduced at the same time, thereby further reducing the pollution emissions of the entire LTO cycle.
(3)主燃级第二级采用预膜式喷嘴,使燃油分布更加均匀,进一步降低污染物排放。(3) The second stage of the main combustion stage adopts pre-film nozzles to make the fuel oil distribution more uniform and further reduce pollutant emissions.
(4)本发明采用单环腔燃烧室结构,燃烧用空气全部由头部供入,火焰筒上只有掺混孔和必要的冷却孔,具有模块化特征,简化了燃烧室结构,主燃级和预燃级结构较简单,易于加工。(4) The present invention adopts a single-annular combustion chamber structure, and all the air for combustion is supplied from the head. There are only mixing holes and necessary cooling holes on the flame tube, which has modular features and simplifies the combustion chamber structure. The main combustion stage And pre-combustion level structure is relatively simple, easy to process.
附图说明Description of drawings
图1是发动机结构示意图;Figure 1 is a schematic diagram of the engine structure;
图2是本发明的燃烧室结构剖视图;Fig. 2 is a sectional view of the combustion chamber structure of the present invention;
图3是本发明的燃烧室头部结构剖视图;Fig. 3 is a cross-sectional view of the combustion chamber head structure of the present invention;
图4是本发明的预燃级结构剖视图;Fig. 4 is a cross-sectional view of the pre-combustion stage structure of the present invention;
图5是本发明的头部结构剖视图(不包含喷嘴杆);Figure 5 is a sectional view of the head structure of the present invention (not including the nozzle rod);
图6是本发明的燃油喷嘴结构剖视图;Fig. 6 is a sectional view of the fuel nozzle structure of the present invention;
图7是本发明的主燃级外环剖视图;Fig. 7 is a sectional view of the outer ring of the main combustion stage of the present invention;
图8是本发明的过主燃级内直射喷孔中心截面(A-A截面)的剖视图;Fig. 8 is a sectional view of the center section (A-A section) of the direct injection hole in the main combustion stage of the present invention;
其中1是低压压气机,2是高压压气机,3是燃烧室,4是高压涡轮,5是低压涡轮,6是燃烧室外机匣,7是燃烧室内机匣,8是火焰筒外壁,9是火焰筒内壁,10是扩压器,11是火焰筒外壁掺混孔,12是火焰筒内壁掺混孔,13是燃烧室头部,14是主燃级,15是预燃级,16是燃油喷嘴,17是预燃级油雾,18是主燃级内环油雾,19是主燃级油膜,20是预燃级旋流器组件,21是预燃级喷嘴,22是预燃级头部端壁,23是预燃级外环管,24是预燃级文氏管,25是预燃级旋流器叶片,26是预燃级喷嘴定位环,27是预燃级内通道,28是预燃级燃油管路,29是预燃级文氏管内壁面,30是预燃级出口,31是预混预蒸发环外环,32是预膜式喷嘴旋流器,33是预混预蒸发环内环,34是主燃级外旋流器,35是主燃级内旋流器,36是主燃级外环腔,37是主燃级内环腔,38是预混段,39是预燃级喷嘴,40是主燃级内喷嘴,41是预膜式喷嘴,42是预膜式喷嘴内环,43是预膜式喷嘴外环,44是主燃级外环,45是主燃级燃油内通道,46是主燃级内燃油管,47是主燃级外燃油管,48是主燃级内燃油环,49是主燃级出口,50是主燃级内喷孔,51是头部整体端壁。Among them, 1 is the low-pressure compressor, 2 is the high-pressure compressor, 3 is the combustion chamber, 4 is the high-pressure turbine, 5 is the low-pressure turbine, 6 is the casing outside the combustion chamber, 7 is the casing inside the combustion chamber, 8 is the outer wall of the flame tube, and 9 is The inner wall of the flame tube, 10 is the diffuser, 11 is the mixing hole on the outer wall of the flame tube, 12 is the mixing hole on the inner wall of the flame tube, 13 is the head of the combustion chamber, 14 is the main combustion stage, 15 is the pre-combustion stage, and 16 is the fuel oil Nozzle, 17 is pre-combustion level oil mist, 18 is main combustion level inner ring oil mist, 19 is main combustion level oil film, 20 is pre-combustion level swirler assembly, 21 is pre-combustion level nozzle, 22 is pre-combustion level head 23 is the pre-combustion level outer ring pipe, 24 is the pre-combustion level venturi tube, 25 is the pre-combustion level swirler vane, 26 is the pre-combustion level nozzle positioning ring, 27 is the pre-combustion level inner channel, 28 29 is the inner wall of the pre-combustion venturi tube, 30 is the outlet of the pre-combustion level, 31 is the outer ring of the pre-mixing pre-evaporation ring, 32 is the pre-film nozzle swirler, and 33 is the pre-mixing pre-evaporation ring. The inner ring of the evaporation ring, 34 is the outer swirler of the main combustion stage, 35 is the inner swirler of the main combustion stage, 36 is the outer ring cavity of the main combustion stage, 37 is the inner ring cavity of the main combustion stage, 38 is the premixing section, 39 40 is the inner nozzle of the main combustion stage, 41 is the pre-film nozzle, 42 is the inner ring of the pre-film nozzle, 43 is the outer ring of the pre-film nozzle, 44 is the outer ring of the main combustion stage, and 45 is the main 46 is the internal fuel pipe of the main combustion stage, 47 is the outer fuel pipe of the main combustion stage, 48 is the internal fuel oil ring of the main combustion stage, 49 is the outlet of the main combustion stage, 50 is the inner injection hole of the main combustion stage, 51 is the overall end wall of the head.
具体实施方式Detailed ways
图1是发动机结构示意图,包括低压压气机1,高压压气机2,燃烧室3,高压涡轮4和低压涡轮5。发动机工作时,空气经过低压压气机1压缩后,进入高压压气机2,高压空气再进入燃烧室3中与燃油燃烧,燃烧后形成的高温高压燃气进入到高压涡轮4和低压涡轮5,通过涡轮做功分别驱动高压压气机2和低压压气机1。FIG. 1 is a schematic structural diagram of an engine, including a low-pressure compressor 1 , a high-pressure compressor 2 , a combustion chamber 3 , a high-pressure turbine 4 and a low-pressure turbine 5 . When the engine is working, the air is compressed by the low-pressure compressor 1 and enters the high-pressure compressor 2. The high-pressure air then enters the combustion chamber 3 to burn with fuel. The high-temperature and high-pressure gas formed after combustion enters the high-pressure turbine 4 and low-pressure turbine 5, and passes through the turbine. Work is done to drive the high-pressure compressor 2 and the low-pressure compressor 1 respectively.
如图2所示,燃烧室3采用单环腔结构,燃烧室外机匣6和燃烧室内机匣7构成了燃烧室的外轮廓,并与前后的高压压气机2和高压涡轮4连接。高压压气机2的来流空气从扩压器10经过降速扩压后进入燃烧室,在火焰筒外壁8、火焰筒内壁9和燃烧室头部13所包围的空间内与燃油完成燃烧。在外掺混孔11和内掺混孔12以前的区域为燃烧区,掺混空气从掺混孔进入火焰筒,与燃烧区的高温燃气掺混,使出口温度达到设计要求。燃烧室头部13包括主燃级14、预燃级15以及燃油喷嘴16,主燃级14通过头部整体端壁51与火焰筒外壁8和火焰筒内壁9焊接固定,而预燃级15则由预燃级头部端壁22与主燃级14固定联接,燃油喷嘴16供给全部燃油。所述燃烧室头部13沿周向均匀布置,个数为10~60个,燃烧室头部13的空气量占燃烧室总空气量的20%~80%,其中主燃级14占头部空气量的60%~90%,预燃级15占头部空气量的10%~40%。As shown in Figure 2, the combustion chamber 3 adopts a single-ring cavity structure, and the outer casing 6 and the inner casing 7 of the combustion chamber form the outer contour of the combustion chamber, and are connected with the high-pressure compressor 2 and the high-pressure turbine 4 before and after. The incoming air from the high-pressure compressor 2 enters the combustion chamber from the
图3是一个燃烧室头部结构的剖视图,可清楚的看出主燃级14和预燃级15按照同心的方式布置在一起。图4是预燃级结构剖视图,从图4中可以看到,预燃级15由预燃级旋流器20组成。从图4、图5、图6可以看到,预燃级旋流器20为叶片式旋流器或槽道式旋流器,旋流器的结构可以是轴向旋流器或是径向旋流器。当预燃级旋流器20采用单级旋流器时,直接与预燃级头部端壁22连接,当预燃级旋流器20采用多级旋流器时,各级旋流器先连接成一个整体,组成预燃级旋流器20后再与预燃级头部端壁22连接。预燃级旋流器20与预燃级头部端壁22连接采用焊接或螺纹加锁紧的方式实现。预燃级旋流器20包括预燃级外环管23、预燃级文氏管24、预燃级旋流器叶片25。预燃级旋流器叶片25周向均匀布置并焊接在其上,从而将预燃级外环管23和预燃级文氏管24连接在一起,预燃级旋流器叶片25的叶片安装角度为30°~70°。预燃级喷嘴21为单个压力雾化喷嘴、气动雾化喷嘴或组合式喷嘴,直接插入到预燃级喷嘴定位环26下游内通道27里,经过预燃级燃油管路28的燃油通过预燃级喷嘴21形成预燃级油雾17,预燃级油雾17打在预燃级旋流器文氏管内壁面29上形成油膜,在经过预燃级内通道27的来流作用下进行雾化,在预燃级出口30进行扩散燃烧。Fig. 3 is a sectional view of the head structure of a combustion chamber, it can be clearly seen that the
从图3、图5和图6可以看到,主燃级14由预混预蒸发外环31、预混预蒸发环内环33、主燃级燃油环48、预膜式喷嘴内环42、预膜式喷嘴外环43、主燃级外旋流器34、主燃级内旋流器35和预膜式喷嘴内旋流器32构成,其中主燃级内旋流器35与预膜式喷嘴内环42、预混预蒸发环内环33焊接在一起,构成了主燃级内环腔37,主燃级外旋流器34与预混预蒸发环外环31一起构成主燃级外环44,和预膜式喷嘴外环43构成了主燃级外环腔36,主级内外环腔36在预膜式喷嘴之后合并成预混段38;主燃级15采用的主燃级内旋流器35和主燃级外旋流器34为叶片式旋流器,叶片安装角度为30°~70°。每级叶片式旋流器的结构是轴向旋流器,或是径向旋流器,两级旋向相同或相反。As can be seen from Fig. 3, Fig. 5 and Fig. 6, the
从图6可以看到,燃油喷嘴16向燃烧室供给所有燃油,燃油喷嘴16包括预燃级喷嘴39、主燃级内喷嘴40和预膜式喷嘴41,燃油喷嘴16从燃烧室头部13的上游直接插入主燃级外环44中。As can be seen from Fig. 6, the
从图6,图8中可以看到,主燃级内喷嘴40由主燃级燃油内通道45和主燃级内直射喷孔50组成,主燃级内燃油环48和预混预蒸发环内环33一起构成主燃级燃油内通道45,为一环形结构。预混预蒸发环内环33上沿周向均匀开有多个主燃级内直射喷孔50,燃油通过主燃级内燃油管46进入主燃级燃油内通道45,然后经过主燃级内直射喷孔50形成多股主燃级内环喷雾18,向主燃级内环腔37中喷射。预膜式喷嘴41由预膜式喷嘴内环42、预膜式喷嘴外环43和预膜式旋流器32组成;燃油通过预膜式喷嘴41向预混段38喷射,主燃级内外旋流的作用下进行蒸发和预混和掺混,在较短的几何尺寸内实现燃油快速蒸发并与空气均匀掺混,进入主燃级出口49进行预混燃烧,保证较低的污染排放。As can be seen from Fig. 6 and Fig. 8, the main combustion stage
主燃级内直射喷孔50的个数为6~30个,主燃级内旋流器35叶片的个数与直射喷油孔的个数之比为1:1~5:1,主燃级内直射喷孔50和预混预蒸发环内环33壁面所形成的倾角均为10°~90°。直射喷孔轴向位置在主燃级内叶片通道里或主燃级内叶片通道下游,距主燃级出口的轴向距离为20~50mm。预膜式喷嘴41出口轴向位置距主燃级出口49的轴向距离为20~50mm,主级预混预蒸发外环31、预混预蒸发环内环33上可开切向槽,切向槽和预混预蒸发环内外环31、33壁面所形成的倾角均为10°~90°,轴向位置距主燃级出口49的轴向距离为20~50mm。主燃级燃油占总燃油量的比例为50%~90%。The number of direct-injection injection holes 50 in the main combustion stage is 6 to 30, the ratio of the number of
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