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A master-lean premixing stage direct fuel injection combustion chamber of the pre-evaporator pollution

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CN103123122B
CN103123122B CN 201210589590 CN201210589590A CN103123122B CN 103123122 B CN103123122 B CN 103123122B CN 201210589590 CN201210589590 CN 201210589590 CN 201210589590 A CN201210589590 A CN 201210589590A CN 103123122 B CN103123122 B CN 103123122B
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CN 201210589590
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CN103123122A (en )
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颜应文
徐榕
邓远灏
朱嘉伟
李诗
党龙飞
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南京航空航天大学
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Abstract

本发明涉及一种主级燃油直接喷射的贫油预混预蒸发低污染燃烧室,属于航空发动机领域,本发明核心思想是进行空气分级和燃油分级,它由值班级/副模和主级/主模组成,值班级包括一级轴向旋流器(8)、二级轴向旋流器(9)、套筒(10)和值班级收扩段(20),形成扩散燃烧,提供稳定点火源;主级包括主级旋流器(11)、主级供油管(15)、集油腔(16)、燃油直射式喷口(17)、主级收扩段(12)以及主级预混环腔(22),进行部分预混预蒸发贫油燃烧,降低高温热点,从而减少热力型NOX排放。 The present invention relates to a lean premixed pre-evaporator a master-level low-pollution combustion of the direct injection of fuel, the engine belongs to the field of aviation, the core idea of ​​the present invention is an air classification and grading of fuel, it is the value of the class / sub-mode from the main stage and / master mold composition comprising a class value of an axial swirler (8), two axial swirler (9), the sleeve (10) and the value of the class divergent section (20), forming a diffusion combustion, provide a stable ignition source; main stage includes a main stage cyclone (11), the primary supply pipe (15), an oil collection chamber (16), direct-fuel nozzle (17), the primary divergent section (12) and a main stage premix annulus (22), partially evaporated lean premixed pre-combustion, lowers the high temperature hot spots, thus reducing the thermal type NOX emissions. 本发明的燃烧室具有中心分级思想的贫油预混预蒸发燃烧模式,可以在不牺牲燃烧室其他性能的同时,能有效的降低航空发动机燃烧室污染排放,包括NOx、冒烟、CO及UHC。 Lean premixed combustion mode, the combustion chamber pre-evaporator according to the present invention having a graded central idea can without sacrificing other properties of the combustion chamber, the combustion chamber can effectively reduce polluting emissions aviation engine, comprising the NOx, smoke, CO and UHC .

Description

一种主级燃油直接喷射的贫油预混预蒸发低污染燃烧室 A master-lean premixing stage direct fuel injection combustion chamber of the pre-evaporator pollution

技术领域 FIELD

[0001] 本发明涉及一种主级燃油直接喷射的贫油预混预蒸发低污染燃烧室,属于航空发动机技术领域。 [0001] The present invention relates to a master-level lean premixed direct fuel injection combustion chamber of the pre-evaporator pollution, belongs to the technical field of aviation engines.

背景技术 Background technique

[0002]目前,民用航空发动机向大气排放的污染物日益增多,对大气污染也日趋严重。 [0002] At present, an increasing number of civil aircraft engine emissions to air pollutants, air pollution has become increasingly serious. 为了控制飞机发动机排放对环境造成的影响,民机燃烧室污染排放要求满足国际民航组织ICAO CAEP标准,目前执行的是CAEP6,特别是对NOx排放要求越来越严格。 In order to control the impact of aircraft engine emissions on the environment, civil aircraft combustion emissions required to meet the ICAO CAEP ICAO standards, the current implementation of CAEP6, especially for NOx emission requirements more stringent. 为了满足CAEP标准,各大航空发动机公司和研宄机构均开展低污染燃烧技术的研宄,GE公司开发了双环预混旋流(Twin Annular Premixing Swirler, TAPS)燃烧技术,排放量比1996 年ICAO标准约低65% ;普惠公司采用RQL燃烧技术开发了第3代TALON III燃烧室。 In order to meet the CAEP standards, the major aircraft engine companies and research institutions are to carry out research traitor traitor and low emission combustion technologies, GE has developed a double loop premixed swirl (Twin Annular Premixing Swirler, TAPS) combustion technology, emissions in 1996 ICAO standard about 65% lower; Pratt & Whitney developed using RQL combustion technology 3rd generation TALON III combustion chamber.

[0003] 传统军机主燃烧室采用的是扩散燃烧,在100%工况下,主燃烧区油气比为化学恰当油气比设计,燃烧效率高,但主燃区燃气温度非常高,因此会产生大量的热力型NOx;而在慢车工况时,燃烧效率低,燃烧不完全,因此污染物CO和UHC生成比较多。 [0003] Traditional main combustion chamber is used in military aircraft diffusion combustion condition at 100%, the primary combustion zone fuel ratio of air-fuel ratio properly designed chemical, high combustion efficiency, the primary combustion zone, the gas temperature is very high, it will produce a large amount the NOx thermal type; and in the idle condition, the combustion efficiency is low, incomplete combustion, thus generating pollutants CO and UHC more. 因此,常规扩散燃烧方式难以达到目前或将来低污染排放要求。 Therefore, the conventional diffusion combustion difficult to achieve at present or in the future low emission requirements. 目前,在研的民用航空发动机燃烧室主要采用贫油预混预蒸发低污染燃烧方式,最核心思想是对空气和燃油进行分级,空气分别从主级/主模和值班级/副模进入燃烧室头部,值班级一般采用小流量压力雾化喷嘴进行扩散燃烧方式,而主级一般进行部分预混燃烧,从而实现燃烧室贫油预混预蒸发燃烧,由于主级燃烧温度均匀,从而降低污染物排放。 Currently, research in civil aviation engine combustion chamber is mainly lean premixed low emission combustion mode pre-evaporator, the core idea is to classify the air and fuel, respectively, into the combustion air from the primary / main die and the value of the class / sub-module chamber head, the value of the general class of small pressure atomizing nozzle flow diffusion combustion mode, and the main stage is generally carried out partially premixed combustion, lean premixed combustion to achieve pre-evaporation combustion, since the main stage combustion temperature uniformity, thereby reducing Emissions.

发明内容 SUMMARY

[0004] 本发明针对上述问题的不足,提出一种主级燃油直接喷射的贫油预混预蒸发低污染燃烧室,该燃烧室在满足航空发动机的性能条件下,能有效的降低航空发动机燃烧室污染排放,包括NOx、冒烟、CO及UHC。 [0004] The above problems of the lack of the present invention, a primary fuel lean premixed direct injection pre-evaporator low pollution combustion chamber performance under conditions of aircraft engines, can effectively reduce the aeroengine combustion emissions chamber, comprising the NOx, smoke, CO and UHC.

[0005] 本发明为解决上述技术问题提出的技术方案是:一种主级燃油直接喷射的贫油预混预蒸发低污染燃烧室,包括燃烧室头部、火焰筒、燃烧室内环通道(25)、燃烧室外环通道 [0005] The present invention is to solve the above problems is proposed solution: a master-lean premixed pre-stage direct fuel injection combustion evaporated pollution, comprising a head combustion chamber, a flame tube, an inner ring of the combustion chamber channel (25 ), combustion chamber outer passage

(24)、喷油杆(21)及机匣,喷油杆(21)安装在机匣(6)上,燃烧室头部通过喷油杆(21)与机匣相连,而燃烧室头部、燃烧室内环通道(25)和燃烧室外环通道(24)按流量分配规律设计,所述喷油杆(21)设置有值班级离心喷嘴(7)和主级供油管(15)的双油路管道,所述燃烧室头部为圆形双环腔结构,分为值班级/副模(I)和主级/主模(2)两部分,且所述主级(2)环绕在值班级(I)的外环;所述值班级包括一级轴向旋流器(8)、二级轴向旋流器(9)、套筒(10)和值班级收扩段(20),一级轴向旋流器⑶与二级轴向旋流器(9)旋向可以相同也可以相反,所述一级轴向旋流器(8)环绕在离心喷嘴(7)外面,而二级轴向旋流器(9)环绕在一级轴向旋流器(8)的外面,所述一级轴向旋流器⑶与二级轴向旋流器(9)之间连接值班级收扩段(20),且值班级收扩段(20)位于一级轴向旋流器(8)的出口处,而套筒 (24), the injector rod (21) and the casing, the injector rod (21) is mounted on the casing (6), the combustor casing through the injector head is connected to the lever (21), a combustion chamber head and , the inner passage of the combustion chamber (25) and the combustion chamber of the outer ring channel (24) according to the law of flow distribution design, the injection rod (21) is provided with a swirl injector class value (7) and the primary supply pipe (15) double oil pipeline, the circular combustor head bicyclic cavity structure, the value is divided into classes / sub-mode (I) and the primary / main die (2) in two parts, and the main stage (2) around the class value (I) of the outer ring; the value of one class comprises an axial swirler (8), two axial swirler (9), the sleeve (10) and the value of the class divergent section (20) , an axial swirler and secondary ⑶ axial swirler (9) may be the same rotation to be reversed, one of the axial swirler (8) surrounding the outside of the centrifugal nozzle (7), and two axial swirler (9) surrounds the outside of an axial swirler (8) connected between the duty ⑶ an axial swirler and secondary axial swirler (9) (20), and the value of the segment-level class divergent divergent section (20) at the outlet an axial swirler (8), and the sleeve

(10)设置在二级轴向旋流器(9)的外面;主级包括主级旋流器(11)、主级供油管(15)、集油腔(16)、燃油直射式喷口(17)、主级收扩段(12)以及主级预混环腔(22),所述主级旋流器(11)环绕在套筒(10)的外面,且喷油杆(21)、主级供油管(15)、集油腔(16)、燃油直射式喷口(17)、主级旋流器(11)、主级预混环腔(22)依次连接,且燃油直射式喷口17布置在主级旋流器11的叶片通道中,同时所述主级收扩段(12)设置在主级预混环腔(22)的出 (10) is disposed outside the two axial swirler (9); a main stage comprising a primary swirler (11), the primary supply pipe (15), an oil collection chamber (16), a direct-fuel nozzle (17), the primary divergent section (12) and a main stage premix annulus (22), said primary swirler (11) surrounding the outside of the sleeve (10), and the injection rod (21) , primary supply pipe (15), an oil collection chamber (16), direct-fuel nozzle (17), the primary cyclone (11), the primary premix annulus (22) are sequentially connected, and a direct-fuel spout 17 is arranged in the primary swirler vane channel 11, while a front stage of said divergent section (12) provided in the main stage premix annulus (22)

□ O □ O

[0006] 进一步地:所述主级和值班级之间设置有头部内环冷却组件(3),空气经头部内环冷却组件(3)上的头部内环冷却小孔(18)进入,对头部内环档溅盘(19)进行冲击冷却;而所述主级和火焰筒之间设置有头部外环冷却组件(4),空气经头部外环冷却组件(4)上的头部外环冷却小孔(13)进入,对头部外环档溅盘(14)进行冲击冷却。 [0006] Further: provided between the primary head and the inner cooling module class values ​​(3), the inner head cooling holes (18) on the cooling air through the inner head assembly (3) enters, the inner profile of the head splash plate (19) for impingement cooling; while cooling the head assembly outer ring (4) disposed between the primary and the flame tube, outer cooling air through the head assembly (4) head cooling holes on the outer ring (13) entering, on the outer profile of the head splash plate (14) for impingement cooling.

[0007] 优选的:所述一级轴向旋流器(8)的叶片、值班级收扩段与二级轴向旋流器(9)的叶片通过整体机械加工、整体铸造或焊接等方式加工形成,套筒(10)与值班级档溅盘(19)和头部内环冷却组件(3)焊接相联,头部内环冷却组件(3)与主级(2)通过焊接相联或通过螺栓相联,主级(2)与头部外环冷却组件(4)相互焊接或螺栓连接,主级集油腔与主级 [0007] The preferred: a blade of the axial cyclone (8), the value of the class with two divergent section axial swirler (9) by an integral blade machining, casting or the like integrally welding processed to form a sleeve (10) and the value of the class file splash plate (19) and an inner ring cooling head assembly (3) associated welding head inner cooling module (3) and the main stage (2) linked by welding or linked by bolts, the main stage (2) and the outer ring cooling head assembly (4) are welded or bolted, the primary collection chamber and the primary oil

(2)可以通过焊接或螺栓相互连接。 (2) may be connected to each other by welding or bolting.

[0008] 优选的:所述燃油直射式喷口(17)在圆环上的分布数量为6〜36个。 [0008] Preferred are: the direct-fuel nozzle (17) distributed over the number ring is 6~36 months.

[0009] 优选的:所述值班级一级轴向旋流器(8)的旋流角度为20°〜45°,一级轴向旋流器(8)的叶片数目为8〜16片,且一级轴向旋流器(8)叶片的旋向沿气流方向可为顺时针或逆时针,原则上与喷雾旋向相反;所述值班级二级轴向旋流器(9)叶片安装角为25。 [0009] Preferred are: the value of a Class axial swirler (8) swirl angle of 20 ° ~45 °, the number of an axial swirler blades (8) is 8~16 sheet, and an axial swirler (8) blade rotation to the direction of flow may be clockwise or counterclockwise, the rotation opposite to the spray principle; the value of the class two axial swirler (9) mounted blade angle of 25. 〜45°,叶片数目为8〜20;二级轴向旋流器(9)叶片旋流安装角度与一级轴向旋流器(8)叶片旋流安装角度相反或相同。 ~45 °, the number of blades of 8~20; two axial swirler (9) and the swirl blade angles an axial swirler (8) opposite to or the same swirl blade mounting angle.

[0010] 优选的:所述套筒(10)的扩张角度为8°〜20°。 [0010] Preferably: the said sleeve (10) of the expansion angle of 8 ° ~20 °.

[0011] 优选的:所述主级旋流器(11)为径向旋流器或轴向旋流器;所述径向旋流器叶片安装角为40°〜60°,叶片数目为12〜40 ;所述轴向旋流器叶片安装角为30°〜70°,叶片数目为6〜48。 [0011] Preferably: the said primary swirler (11) is a radial swirler or an axial swirler; said radial swirler vanes mounted angle of 40 ° ~60 °, the number of vanes 12 ~ 40; and the axial swirler blade mounting angle of 30 ° ~70 °, the number of vanes is 6~48.

[0012] 优选的:所述燃烧室头部的空气量占燃烧室总空气量的50%〜85%,其中主燃级占头部空气量的60%〜90%,预燃级占头部空气量的10%〜40%。 [0012] Preferred: 50% ~ 85% of the head portion of the total combustion air amount of the combustion air amount, wherein the primary combustion stage 60% ~ 90% of the amount of air head, pre-combustion stage accounted head 10% ~ 40% of the amount of air.

[0013] 优选的:所述火焰筒(5)的冷却采用全覆盖气膜冷却、冲击发散冷却或是其它复合冷却方式,所述火焰筒后部根据实际需要布置有多个掺混孔。 [0013] Preferred of: cooling the flame tube (5) of the all-covering film cooling, effusion cooling, or other composite shock cooling, the rear portion of the flame tube according to the actual needs of a plurality of dilution holes are arranged.

[0014] 本发明的工作过程: [0014] The operation of the present invention:

[0015] 来自高压压气机的空气从扩压器(23)进入燃烧室后,之后分三路分别进入燃烧室内环通道(25)、燃烧室头部和燃烧室外环通道(24),内、外环通道的空气分别从火焰筒 [0015] After the high pressure air from the compressor into the combustion chamber from the diffuser (23), respectively, into the combustion chamber in three columns after the inner ring channel (25), a combustion chamber and the combustion chamber head outer channel (24), the inner , respectively, from the air passage outer liner

(5)上的掺混孔和气膜冷却孔进入火焰筒。 Dilution holes and film cooling holes on the (5) into the flame tube. 燃烧室中燃烧用气大部分从头部供入,其它用气均从火焰筒供入。 Most of the combustion gas in the combustion chamber is fed from the head, the other are fed with gas from the flame tube. 而燃烧室头部包括值班级⑴和主级⑵。 And the combustor comprises a head portion and a main stage value classes ⑴ ⑵. 在值班级⑴中,燃油(占总燃油的5%〜50%)经离心喷嘴(7)喷出并进行初始雾化,受到来自环绕在其周围的一级轴向旋流器(8)气流的撞击破碎,形成二次雾化,接着值班级收扩段(20)出口受一级轴向旋流器(8)和二级轴向旋流器(9)出口气流的剪切破碎进行三次雾化,掺混后的油气混合物进入燃烧室主燃区进行部分扩散燃烧,形成稳定点火源;对于主级,燃油(占总燃油的50%〜95%)从供油管(15)进入主级集油腔(16),再分别经主级燃油直射喷口(17)喷出,可以调节主级燃油直射式喷口喷射角度和轴向位置,来调节主级燃油雾化情况,由于主级燃油直射式喷口(17)布置在主级叶片通道中,且由于燃油喷射方向与主级空气流动方向相互垂直或相对,燃油在主级气动力作用下,实现破碎、雾化,之后进入主级预混环腔(22),燃油与空气在预混环腔(22)内继续混合并部分蒸发后进 ⑴ class value, the fuel (7) by centrifugal ejection nozzle and initial atomization (5% ~ 50% of total fuel), being looped therearound from an axial swirler (8) air flow the impact crusher, to form a secondary atomization, then the value of the class divergent section (20) cut by the outlet (9) of an outlet of the axial swirler airflow (8) and two axial swirler crushed three times atomizing, blending the fuel-air mixture into the combustion chamber portion of the primary combustion zone for diffusion combustion, a stable ignition sources are formed; the main stage, the fuel (50% ~ 95% of total fuel) into the main pipe from the supply (15) grade oil collection chamber (16), respectively, and then (17) through the primary fuel direct discharge spout may be adjusted to direct the primary fuel injection nozzle of formula angular and axial positions, to adjust the primary fuel atomization case, since the main fuel stage direct-spout (17) is arranged in the primary blade passage, and since the fuel injection direction of the primary air flow direction or perpendicular relative to each other, in the main stage fuel gas dynamic action, crushing implement, atomizing, after entering the main stage pre- mixing annulus (22), and fuel and air mixing continued evaporated backward portion (22) in the premix annulus 入燃烧区,形成贫油预混燃烧。 Into the combustion zone to form a lean premixed combustion.

[0016] 本发明的一种主级燃油直接喷射的贫油预混预蒸发低污染燃烧室,相比现有技术,具有以下有益效果: [0016] The present invention is one kind of a lean premixed main-stage direct fuel injection combustion chamber of the pre-evaporator pollution, compared to the prior art, it has the following advantages:

[0017] 1.由于值班级由一级或两级(包括同向或反向)轴向旋流器和压力雾化喷嘴组成,形成扩散火焰,因此能够提供稳定点火源,兼顾点火/熄火性能以及慢车工况燃烧效率问题。 [0017] 1. Since the value of one or two classes (including the same or opposite) axial swirler composition and a pressure atomizing nozzle, forming a diffusion flame, and therefore can provide a stable ignition source, taking into account the ignition / extinction performance local conditions and combustion efficiency.

[0018] 2.由于主级由一个径向旋流器或轴向旋流器、空腔与多个燃油直接喷射孔组成,因而进行部分预混预蒸发均匀燃烧,降低高温热点,从而降低大工况下NOx、冒烟、CO及UHC排放,同时且该类型的主级燃油雾化方式结构简单。 [0018] 2. Since the main stage of a radial swirler or an axial swirler, a plurality of cavities with direct fuel injection hole constituent, thus pre-evaporator is partially premixed homogeneous combustion, to reduce the high temperature hot spots, thus reducing the large conditions the NOx, smoke, CO and UHC emissions, and the simple type of primary fuel atomization structure.

[0019] 3.由于主燃级空气进气占整个扩压器进气的40%〜70%左右,而燃油占总燃油的50%〜95%,并且在空腔中进行了部分预混预蒸发,因此基本实现预混预蒸发燃烧,降低污染物排放,同时值班级提供稳定可靠的点火源。 [0019] 3. Since the primary combustion stage air inlet about 40% ~ 70% of the total intake air diffuser, and 50% ~ 95% of the total fuel oil, and was pre-partially premixed in the cavities evaporation, thus pre-evaporator basically premixed combustion, reduce emissions, while the value of the class to provide a stable and reliable source of ignition.

[0020] 4.由于设置有值班级收扩段(20)、主级收扩段(12),从而有效防止贫油预混预蒸发燃烧中的回火、喷嘴积碳问题。 [0020] 4. As the value of classes provided divergent section (20), the primary divergent section (12), thereby effectively preventing the lean premixed combustion in the pre-evaporator tempering nozzle coking problem.

[0021] 5.由于空气经头部内环冷却组件(3)上的头部内环冷却小孔(18)进入,对头部内环档溅盘(19)进行冲击冷却,同时空气经头部外环冷却组件(4)上的头部外环冷却小孔 [0021] 5. As the cooling air through the inner head assembly inner head cooling holes (18) (3) enters, the inner profile of the head splash plate (19) for impingement cooling, and air through the head outer ring outer ring portion cooling assembly cooling holes on the head (4)

(13)进入,对头部外环档溅盘(14)进行冲击冷却,从而延长燃烧室头部的使用寿命。 (13) entering, on the outer profile of the head splash plate (14) for impingement cooling, thereby extending the life of the head of the combustion chamber.

[0022] 6.由于火焰筒(5)的冷却采用全覆盖气膜冷却、冲击发散冷却或是其它复合冷却方式,从而控制火焰筒壁面温度,因而延长火焰筒使用寿命;在火焰筒后部根据实际需要来布置掺混孔,从而控制燃烧室出口温度分布。 [0022] 6. the cooling of the flame tube (5) of the all-covering film cooling, effusion cooling, or other composite shock cooling, to control the flame tube wall temperature, thus prolonging the service life of the flame tube; The flame tube at the rear dilution holes disposed actual needs, so as to control the combustor exit temperature distribution.

附图说明 BRIEF DESCRIPTION

[0023] 图1是本发明实施例的结构示意图; [0023] FIG. 1 is a block diagram of an embodiment of the present invention;

[0024] 图2是图1的燃烧室头部结构放大图; [0024] FIG. 2 is a configuration diagram of a combustor head enlarged view;

[0025] 其中:1.值班级/副模,2.主级/主模,3.头部内环冷却组件,4.头部外环冷却组件,5.火焰筒,6.机匣,7.值班级离心喷嘴,8.—级轴向旋流器,9.二级轴向旋流器,10.套筒,11.主级旋流器,12.主级收扩段,13.头部外环冷却小孔,14.头部外环档溅盘,15.主级供油管,16.集油腔,17.燃油直射式喷口,18.头部内环冷却小孔,19.头部内环档溅盘,20.值班级收扩段,21.喷油杆,22.主级预混环腔,23.扩压器,24.燃烧室外环通道,25.燃烧室内环通道。 [0025] wherein:...... Class value 1 / sub-die, 2 the primary / master mold, the inner head cooling assembly 3, outer cooling head assembly 4, a flame tube 5, the casing 6, 7 The value of the class centrifugal nozzle 8.- stage axial cyclone, 9. two axial swirler 10. The sleeve 11 primary cyclone, 12. primary divergent section 13 head cooling the outer portion aperture 14. splash head disc outer profile, 15 primary supply pipe, 16 gathers the oil chamber 17 direct-fuel nozzle, 18 an inner ring head cooling holes, 19. splash head inner gear disc 20. A value class divergent segment 21. injection rod 22. annulus primary premix, 23. diffuser 24. combustor outer passage 25. combustor inner aisle.

具体实施方式 detailed description

[0026] 附图非限制性地公开了本发明一个优选实施例的结构示意图,以下将结合附图详细地说明本发明的技术方案。 [0026] Non-limiting drawings discloses a schematic structural diagram of a preferred embodiment of the present invention, will be described in conjunction with the technical solutions of the present invention in detail with the accompanying drawings.

实施例 Example

[0027] 本实施例的一种主级燃油直接喷射的贫油预混预蒸发低污染燃烧室如图1、2所示,包括燃烧室头部、火焰筒5、燃烧室内环通道25、燃烧室外环通道24、喷油杆21及机匣,喷油杆21安装在机匣6上,一方面为燃烧室头部供油,另一方面承担一部分机械力,燃烧室头部通过喷油杆21与机匣6相连,而燃烧室头部、燃烧室内环通道25和燃烧室外环通道24按流量分配规律设计,内、外环通道的空气分别从火焰筒5上的掺混孔和气膜冷却孔进入火焰筒,所述喷油杆21设置有值班级离心喷嘴7和主级供油管15的双油路管道,所述燃烧室头部为圆形双环腔结构,分为值班级/副模I和主级/主模2两部分,且所述主级2环绕在值班级I的外环;所述值班级包括一级轴向旋流器8、二级轴向旋流器9、套筒10和值班级收扩段20,一级轴向旋流器8与二级轴向旋流器9旋向可以相同也可以相 [0027] This lean premixed fuel a master-stage embodiment of the direct injection combustion chamber of the pre-evaporator pollution 1 and 2, a head including a combustion chamber, a flame tube 5, the inner passage 25 of the combustion chamber, the combustion outdoor ring channel 24, the rod 21 and the injector casing, the injector rod 21 is mounted on the casing 6, on the one hand to supply the combustion chamber head, a portion of a mechanical force to bear on the other hand, the combustion chamber through the injection head 6 is connected to the rod 21 and the casing, and a combustion chamber head, a combustion chamber 25 and the combustion chamber inner passage 24 by the outer ring channel allocation pattern design, the inner, outer air flow passages, respectively, from the dilution holes of the cylinder liner 5 film-cooling hole into the flame tube, the injection rod 21 is provided with a nozzle 7 centrifugation class value and the main stage for a double pipe oil pipeline 15, the circular combustor head bicyclic cavity structure, into a class value / I die and primary sub / main die 2 in two parts, the main stage and the value of the class 2 surrounding the outer ring I; the value of class 8 comprising an axial swirler, two axial swirler 9, the sleeve 10 and the class value divergent section 20, an axial swirler 8 and the two rotation axial swirler 9 may be the same with respect to 反,所述一级轴向旋流器8环绕在值班级离心喷嘴7外面,而二级轴向旋流器9环绕在一级轴向旋流器8的外面,所述一级轴向旋流器8与二级轴向旋流器9之间连接值班级收扩段20,且值班级收扩段20位于一级轴向旋流器8的出口处,值班级收扩段20相当于文氏管,其收缩段角度和扩张段角度的设计都很重要,可有效防止回火、喷嘴积碳,而套筒10设置在二级轴向旋流器9的外面;主级包括主级旋流器11、主级供油管15、集油腔16、燃油直射式喷口17、主级收扩段12以及主级预混环腔22,所述主级旋流器11环绕在套筒10的外面,且喷油杆21、主级供油管15、集油腔16、燃油直射式喷口17、主级旋流器11、主级预混环腔22依次连接,且燃油直射式喷口17布置在主级旋流器11的叶片通道中,同时所述主级收扩段12设置在主级预混环腔22的出口。 In contrast, the axial swirler 8 surrounds an outside of class values ​​centrifugal nozzle 7, 9 and two axial swirler surrounds the outside of an axial swirler 8, an axial spin the 8 with two axial flow swirler 9 is connected between the divergent section 20 the value of the class, and the class value of a divergent section 20 located at the outlet of the axial swirler 8, the value of the class corresponding to divergent section 20 venturi constriction angle and its angular expansion section design is very important, can effectively prevent tempering nozzles carbon, and the sleeve 10 is provided outside the two axial swirler 9; main stage includes a main stage cyclone 11, the primary supply pipe 15, the oil collection chamber 16, a direct-fuel nozzle 17, the primary divergent section 12 and a main stage premix annulus 22, a primary swirler 11 surrounding the sleeve 10 outside, and the injection rod 21, the primary supply pipe 15, the oil collection chamber 16, a direct-fuel nozzle 17, primary cyclone 11, the primary premix chamber annulus 22 in turn is connected, and a direct-fuel nozzle stage 17 disposed in the main swirler vane passages 11, while the primary divergent section 12 is provided at the outlet of the primary premix chamber 22 ring.

[0028] 所述主级2和值班级I之间设置有头部内环冷却组件3,空气经头部内环冷却组件3上的头部内环冷却小孔18进入,对头部内环档溅盘19进行冲击冷却;而所述主级和火焰筒之间设置有头部外环冷却组件4,空气经头部外环冷却组件4上的头部外环冷却小孔13进入,对头部外环档溅盘14进行冲击冷却。 [0028] The main stage 2 and is provided with a head between the inner cooling assembly Class I value 3, the cooling air through the inner hole of the head on the head portion 3 of the inner ring 18 into the cooling assembly, the head of the inner ring profile splash plate 19 for impingement cooling; while disposed between the primary and outer flame cylinder head cooling assembly 4, the air cooling holes through the head on the head portion of the outer ring 4 into the outer ring cooling assembly 13, for outer ring gear head 14 to impingement cool splash plate.

[0029] 所述一级轴向旋流器8的叶片、值班级收扩段与二级轴向旋流器9的叶片通过整体机械加工、整体铸造或焊接等方式加工形成,套筒10与值班级档溅盘19和头部内环冷却组件3焊接相联,头部内环冷却组件3与主级2通过焊接相联或通过螺栓相联,主级2与头部外环冷却组件4相互焊接或螺栓连接,主级集油腔与主级2可以通过焊接或螺栓相互连接。 Blade [0029] The one axial swirler vanes, the value of the class two divergent section axial swirler 8 and 9 by integral machining, casting or the like integrally formed welding process, the sleeve 10 class files value splash plate 19 and the inner ring cooling head assembly 3 associated welding head 3 and the inner ring main stage cooling assembly 2 is associated or linked by bolts, by welding, the main stage the outer ring 2 and the head cooling assembly 4 are welded or bolted, the primary collection chamber and the primary oil 2 may be connected to each other by welding or bolting.

[0030] 所述燃油直射式喷口17在圆环上的分布数量、喷射角度以及轴向距离可以根据所需的工作状态以及主级叶片数目来确定,所述燃油直射式喷口17在圆环上的分布数量为6〜36个,燃油直射式喷口17的喷射角度在一45°〜45°之间,以使得主级预混腔22的油气混合更加均匀;并且根据工况不同,燃油直射式喷口17打开的数目可以进行控制。 [0030] The direct-injection fuel quantity distribution nozzle 17 in the ring, and an axial distance from the injection angle may be determined according to a desired operating state of the main stage and the number of blades, the direct fuel injection port 17 on the ring of formula distribution of a number of 6~36, direct-injection fuel injector nozzle 17 is an angle between a 45 ° ~45 °, so that the primary premix chamber 22 is more uniform fuel air mixture; and, depending on conditions, a direct-fuel the number of orifices 17 is opened can be controlled.

[0031] 所述值班级一级轴向旋流器8的旋流角度为20°〜45°,一级轴向旋流器8的叶片数目为8〜16片,具体根据实际情况确定,一级轴向旋流器8叶片的旋向沿气流方向可为顺时针或逆时针,原则上与喷雾旋向相反;所述值班级二级轴向旋流器9叶片安装角为25。 The [0031] value of a class axial swirler swirl angle 8 of 20 ° ~45 °, the number of blades of an axial swirler 8 is 8~16 sheet, particularly according to the actual situation, a stage axial swirler blades 8 may be clockwise or counterclockwise rotation, the principle of rotation of the spray stream in the opposite direction; the value of the class two axial swirler vanes 9 mounted angle of 25. 〜45°,叶片数目为8〜20;二级轴向旋流器9叶片旋流安装角度与一级轴向旋流器8叶片旋流安装角度相反或相同。 ~45 °, the number of blades of 8~20; two same or opposite axial swirler 9 and a mounting angle swirl vane axial swirler 8 swirl blade angles.

[0032] 所述套筒10的扩张角度为8°〜20°。 Spread angle [0032] The sleeve 10 is 8 ° ~20 °.

[0033] 所述主级旋流器11为径向旋流器或轴向旋流器;所述径向旋流器叶片安装角为40°〜60°,叶片数目为12〜40 ;所述轴向旋流器叶片安装角为30°〜70°,叶片数目为 [0033] The primary swirler 11 is a radial swirler or an axial swirler; said radial swirler vanes mounted angle of 40 ° ~60 °, the number of blades of 12~40; the axial swirler blade mounting angle of 30 ° ~70 °, the number of leaves

6 〜48 ο 6 ~48 ο

[0034] 所述燃烧室头部的空气量占燃烧室总空气量的50%〜85%,其中主燃级占头部空气量的60%〜90%,预燃级占头部空气量的10%〜40%。 [0034] 50% ~ 85% of the total combustion air amount of the air amount of the combustion head, wherein the primary combustion stage 60% ~ 90% of the amount of air head, pre-combustion stage air quantity representing the head 10% ~ 40%.

[0035] 所述火焰筒5的冷却采用全覆盖气膜冷却、冲击发散冷却或是其它复合冷却方式,因而能够控制火焰筒壁面温度,从而延长火焰筒使用寿命;所述火焰筒后部根据实际需要布置有多个掺混孔,从而控制燃烧室出口温度分布。 [0035] The cooling of the flame tube 5 of the all-covering film cooling, effusion cooling, or other composite shock cooling, it is possible to control the flame tube wall temperature, thereby prolonging the service life of the flame tube; rear portion of the flame tube according to the actual necessary to arrange a plurality of dilution holes, so as to control the combustor exit temperature distribution.

[0036] 本发明的工作过程: [0036] The operation of the present invention:

[0037] 来自高压压气机的空气从扩压器23进入燃烧室后,之后分三路分别进入燃烧室内环通道25、燃烧室头部和燃烧室外环通道24,内、外环通道的空气分别从火焰筒5上的掺混孔和气膜冷却孔进入火焰筒。 After [0037] from the high pressure compressor air from diffuser 23 into the combustion chamber into the combustion chamber after the three columns each inner passage 24, the air passage of the outer ring outer combustion chamber and the combustion chamber channel 25 of the head respectively, into the flame tube from the dilution holes and film cooling holes in the flame tube 5. 燃烧室中燃烧用气大部分从头部供入,其它用气均从火焰筒供入,而燃烧室头部包括值班级I和主级2ο在值班级I中,燃油(占总燃油的5%〜50 % )经离心喷嘴7喷出并进行初始雾化,受到来自环绕在其周围的一级轴向旋流器8气流的撞击破碎,形成二次雾化,接着值班级收扩段20出口受一级轴向旋流器8和二级轴向旋流器9出口气流的剪切破碎进行三次雾化,掺混后的油气混合物进入燃烧室主燃区进行部分扩散燃烧,形成稳定点火源;对于主级,燃油(占总燃油的50%〜95%)从供油管15进入主级集油腔16,再分别经主级燃油直射喷口17喷出,可以调节主级燃油直射式喷口喷射角度和轴向位置,来调节主级燃油雾化情况,由于主级燃油直射式喷口17布置在主级旋流器11的叶片通道中,且由于燃油喷射方向与主级空气流动方向相互垂直或相对,燃油在主级气动力作用下, Most of the combustion gas supplied into the combustion chamber from the head, the other are fed with gas from the flame tube, and the combustion chamber head includes a value class I and class values ​​2ο main stage I, the fuel (total fuel 5 % ~ 50%) is ejected by centrifugation and initial atomization nozzle 7, from the impact is looped therearound an axial swirler airflow crushing 8, to form a secondary atomization, then the value of the class divergent section 20 shear outlet 9 by an axial swirler outlet stream 8 and two axial swirler atomized crushed three times, the blended fuel-air mixture into the combustion chamber portion of the primary combustion zone for diffusion combustion, to form a stable ignition source; for the main stage, the fuel (50% ~ 95% of total fuel) into the primary collection chamber 16 from the oil supply pipe 15, respectively, and then through the discharge spout 17 to direct the main fuel stage, a main stage fuel may be adjusted to direct the formula nozzle spray angle and axial positions, to adjust the primary fuel atomization case, since the main stage fuel nozzle 17 is arranged in a direct-primary swirler vane passages 11, and since the fuel injection direction of the primary air flow direction to each other or relatively vertical, the primary fuel gas under the action of force, 现破碎、雾化,之后进入主级预混环腔22,燃油与空气在预混环腔22内继续混合并部分蒸发后进入燃烧区,形成贫油预混燃烧。 Now broken, atomizing, after entering the primary premix annulus 22, fuel and air continue to mix in the premix chamber 22 and the rear portion of the ring evaporates into the combustion zone, lean premixed combustion is formed.

[0038] 上面结合附图所描述的本发明优选具体实施例仅用于说明本发明的实施方式,而不是作为对前述发明目的和所附权利要求内容和范围的限制,凡是依据本发明的技术实质对以上实施例所做的任何简单修改、等同变化与修饰,均仍属本发明技术和权利保护范畴。 As described above in conjunction with the accompanying drawings [0038] Preferred embodiments of the present invention are for illustration only particular embodiments of the present invention, and not as a limitation on the content and scope of the foregoing object of the invention and the appended claims, all according to the techniques of this invention any simple substance of the modification made to the above embodiment, such modifications and equivalent, are still claimed in the present invention and the scope of protection technology.

Claims (8)

1.一种主级燃油直接喷射的贫油预混预蒸发低污染燃烧室,包括燃烧室头部、火焰筒、燃烧室内环通道(25)、燃烧室外环通道(24)、喷油杆(21)及机匣,喷油杆(21)安装在机匣(6)上,燃烧室头部通过喷油杆(21)与机匣相连,而燃烧室头部、燃烧室内环通道(25)和燃烧室外环通道(24)按空气流量分配规律设计,所述喷油杆(21)设置有值班级离心喷嘴(7)和主级供油管(15)的双油路管道,其特征在于:所述燃烧室头部为圆形双环腔结构,分为值班级/副模⑴和主级/主模⑵两部分,且所述主级⑵环绕在值班级⑴的外环;所述值班级包括一级轴向旋流器(8)、二级轴向旋流器(9)、套筒(10)和值班级收扩段(20),一级轴向旋流器⑶与二级轴向旋流器(9)旋向可以相同也可以相反,所述一级轴向旋流器(8)环绕在离心喷嘴(7)外面,而二级轴向旋流器(9)环绕在一级轴向旋流器(8)的外面,所述 A lean premixed direct injection of primary fuel combustion pre-evaporator pollution, comprising a head combustion chamber, a flame tube, an inner ring of the combustion chamber channel (25), the outer ring of the combustion chamber channel (24), the injector rod (21) and the casing, the injector rod (21) is mounted on the casing (6), the combustor casing through the injector head is connected to the lever (21), and a combustion chamber head, a combustion chamber inner ring channel (25 ) of the combustion chamber and the outer ring channel (24) by an air flow distribution law design, the injection rod (21) is provided with a swirl injector class value (7) and the primary supply pipe (15) double oil pipeline, which characterized in that: said head combustion chamber is circular bicyclic structure, into a class values ​​/ sub-mode and primary ⑴ / ⑵ two main mold portion, and said primary looped value class ⑴ ⑵ outer ring; the a value of said classes comprises an axial swirler (8), two axial swirler (9), the sleeve (10) and the value of the class divergent section (20), and an axial swirler ⑶ two axial swirler (9) may be the same rotation to be reversed, one of the axial swirler (8) surrounding the outside of the centrifugal nozzle (7), and two axial swirler (9) surrounds an axial swirler (8) outside the 一级轴向旋流器(8)与二级轴向旋流器(9)之间连接值班级收扩段(20),且值班级收扩段(20)位于一级轴向旋流器(8)的出口处,而套筒(10)设置在二级轴向旋流器(9)的外面;主级包括主级旋流器(11)、主级供油管(15)、集油腔(16)、燃油直射式喷口(17)、主级收扩段(12)以及主级预混环腔(22),所述主级旋流器(11)环绕在套筒(10)的外面,且喷油杆(21)、主级供油管(15)、集油腔(16)、燃油直射式喷口(17)、主级旋流器(11)、主级预混环腔(22)依次连接,且燃油直射式喷口17布置在主级旋流器11的叶片通道中,同时所述主级收扩段(12)设置在主级预混环腔(22)的出口;所述主级和值班级之间设置有头部内环冷却组件(3),空气经头部内环冷却组件(3)上的头部内环冷却小孔(18)进入,对头部内环档溅盘(19)进行冲击冷却;而所述主级和火焰筒之间设置有头部外环冷却组件(4),空气经头部外 Connection value class divergent section (20) between an axial swirler (8) with two axial swirler (9), and the value of the class divergent section (20) located at an axial swirler (8) at the outlet, and the sleeve (10) disposed outside the two axial swirler (9); a main stage comprising a primary swirler (11), the primary supply pipe (15), set an oil chamber (16), direct-fuel nozzle (17), the primary divergent section (12) and a main stage premix annulus (22), said primary swirler (11) surrounding the sleeve (10) outside, and the injection rod (21), the primary supply pipe (15), an oil collection chamber (16), direct-fuel nozzle (17), the primary cyclone (11), the primary premix annulus (22) sequentially connected, and a direct-fuel nozzle 17 is disposed in the main stage vane swirler passage 11, while the primary divergent section (12) is provided at the outlet of the primary premix annulus (22); between said primary inner header set and the value of class cooling module (3), the inner cooling air through the head assembly inner head cooling holes (18) (3) enters, of the head studs splash plate (19) for impingement cooling; while cooling the head assembly outer ring (4) disposed between the primary and the flame tube, the outer air through the head 环冷却组件(4)上的头部外环冷却小孔(13)进入,对头部外环档溅盘(14)进行冲击冷却。 Outer ring cooling assembly head cooling holes (13) (4) enters the head outer profile splash plate (14) for impingement cooling.
2.根据权利要求1所述主级燃油直接喷射的贫油预混预蒸发低污染燃烧室,其特征在于:所述一级轴向旋流器(8)的叶片、值班级收扩段与二级轴向旋流器(9)的叶片通过整体机械加工、整体铸造或焊接等方式加工形成,套筒(10)与值班级档溅盘(19)和头部内环冷却组件(3)焊接相连,头部内环冷却组件(3)与主级(2)通过焊接相连或通过螺栓相连,主级(2)与头部外环冷却组件(4)相互焊接或螺栓连接,主级集油腔与主级(2)可以通过焊接或螺栓相互连接。 The primary fuel to the claim 1 lean premixed direct injection combustion chamber of the pre-evaporator pollution, characterized in that: said one axial swirler (8) of the blade, and the value of the class divergent section two axial swirler vanes (9) integral by machining, casting or the like integrally formed welding process, the sleeve (10) and the value of the class file splash plate (19) and an inner ring cooling head assembly (3) welding is connected, an inner ring cooling head assembly (3) and the main stage (2) is connected by welding or by a bolt connected to the main stage (2) and the outer ring cooling head assembly (4) are welded or bolted, the primary current the oil chamber of the main stage (2) can be connected to one another by welding or bolting.
3.根据权利要求2所述主级燃油直接喷射的贫油预混预蒸发低污染燃烧室,其特征在于:所述燃油直射式喷口(17)在圆环上的分布数量为6〜36个。 2 according to the direct injection of the primary fuel lean premixed low-pollution combustion chamber pre-evaporator as claimed in claim, wherein: the direct-fuel nozzle (17) distributed over the number ring is 6~36 months .
4.根据权利要求3所述主级燃油直接喷射的贫油预混预蒸发低污染燃烧室,其特征在于:所述值班级一级轴向旋流器(8)的旋流角度为20°〜45°,一级轴向旋流器(8)的叶片数目为8〜16片,且一级轴向旋流器⑶叶片的旋向沿气流方向为顺时针或逆时针,与喷雾旋向相反;所述值班级二级轴向旋流器(9)叶片安装角为25°〜45°,叶片数目为8〜20 ;二级轴向旋流器(9)叶片旋流安装角度与一级轴向旋流器(8)叶片旋流安装角度相反或相同。 According to the claim 3 primary fuel lean premixed direct injection combustion chamber of the pre-evaporator pollution, characterized in that: the value of the angle class a cyclone axial swirler (8) is 20 ° number of blades ~45 °, an axial cyclone (8) is 8~16 sheet, and an axial swirler vane ⑶ a rotation to the direction of flow is clockwise or counterclockwise, with the spray of rotation Conversely; the value of the class two axial swirler (9) the blade setting angle of 25 ° ~45 °, the number of blades of 8~20; two axial swirler (9) and a swirl blade angles stage axial swirler (8) opposite to or the same swirl blade mounting angle.
5.根据权利要求4所述主级燃油直接喷射的贫油预混预蒸发低污染燃烧室,其特征在于:所述套筒(10)的扩张角度为8°〜20°。 Lean premix according to claim 4 primary direct fuel injection combustion chamber of the pre-evaporator pollution, characterized in that: said sleeve (10) of the expansion angle of 8 ° ~20 °.
6.根据权利要求5所述主级燃油直接喷射的贫油预混预蒸发低污染燃烧室,其特征在于:所述主级旋流器(11)为径向旋流器或轴向旋流器;所述径向旋流器叶片安装角为40°〜60°,叶片数目为12〜40 ;所述轴向旋流器叶片安装角为30°〜70°,叶片数目为6 〜48 ο 5 according to claim said primary fuel lean premixed direct injection combustion chamber of the pre-evaporator pollution, characterized in that: said primary swirler (11) as a radial or axial cyclone swirler ; said radial swirler blade mounting angle of 40 ° ~60 °, the number of blades of 12~40; the axial swirler blade mounting angle of 30 ° ~70 °, the number of blades 6 ~48 ο
7.根据权利要求6所述主级燃油直接喷射的贫油预混预蒸发低污染燃烧室,其特征在于:所述燃烧室头部的空气量占燃烧室总空气量的50%〜85%,其中主级占头部空气量的60%〜90%,值班级占头部空气量的10%〜40%。 The primary fuel to the claim 6 lean premixed direct injection combustion chamber of the pre-evaporator pollution, characterized in that: 50% ~ 85% of the total combustion air amount of the combustion air amount of the head wherein the primary air 60% ~ 90% of the amount of the head, the value of the class 10% ~ 40% of the amount of air head.
8.根据权利要求7所述主级燃油直接喷射的贫油预混预蒸发低污染燃烧室,其特征在于:所述火焰筒(5)的冷却采用全覆盖气膜冷却、冲击发散冷却或是其它复合冷却方式,所述火焰筒后部根据实际需要布置有多个掺混孔。 Lean premixed claimed in claim 7 primary fuel direct injection combustion chamber of the pre-evaporator pollution, characterized in that: the cooling of the flame tube (5) of the all-covering film cooling, or transpiration cooling impact other composite cooling, the rear portion of the flame tube are arranged according to the actual needs of a plurality of dilution holes.
CN 201210589590 2012-12-31 2012-12-31 A master-lean premixing stage direct fuel injection combustion chamber of the pre-evaporator pollution CN103123122B (en)

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JPH06137559A (en) * 1992-10-26 1994-05-17 Mitsubishi Heavy Ind Ltd Combustor for gas turbine
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