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Publication numberCN103123122 B
Publication typeGrant
Application numberCN 201210589590
Publication date12 Aug 2015
Filing date31 Dec 2012
Priority date31 Dec 2012
Also published asCN103123122A
Publication number201210589590.7, CN 103123122 B, CN 103123122B, CN 201210589590, CN-B-103123122, CN103123122 B, CN103123122B, CN201210589590, CN201210589590.7
Inventors颜应文, 徐榕, 邓远灏, 朱嘉伟, 李诗, 党龙飞
Applicant南京航空航天大学
Export CitationBiBTeX, EndNote, RefMan
External Links: SIPO, Espacenet
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-level direct fuel injection lean premixed combustion chamber pre-evaporation pollution translated from Chinese
CN 103123122 B
Abstract  translated from Chinese
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 main-stage direct fuel injection lean premixed combustion chamber pre-evaporation pollution, belong to the field of aviation engines, the core idea of the invention is to carry out an air classifier and fuel grade, which consists of the value of class / Sub mode and the main stage / master mold composition, value class including an axial cyclone (8), two axial cyclone (9), the sleeve (10) and the value of the class-divergent section (20), to form a diffusion combustion, providing a stable ignition source; main level includes a primary cyclone (11), the main stage for the pipeline (15), set the oil chamber (16), direct-fuel spout (17), the primary income expanded section (12) and the main stage premix annular cavity (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 pre-evaporation chamber of the present invention has a central hierarchical thinking, can without sacrificing performance, while the other chamber, which can effectively reduce the aero-engine combustion emissions, including NOx, smoke, CO and UHC .
Claims(8)  translated from Chinese
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。 A main stage direct fuel injection in a pre-evaporator pollution lean premixed combustion, including the combustion head, liner, combustor inner channel (25), a combustion chamber outer channel (24), injection rod (21) and the casing, the injector rod (21) mounted on the casing (6), the combustion chamber by the injector head bar (21) is connected to the casing, and a combustion chamber head, a combustion chamber inner channel (25 ) and combustion chamber outer channel (24) according to the law of the air flow distribution design, the fuel injector (21) is provided with a value class centrifugal nozzle (7) and the main stage for the pipeline (15) double oil pipeline, which wherein: the combustion head circular cavity bicyclic structure, divided into value class / Sub mode ⑴ and primary / primary mode ⑵ two parts, and the primary value of the class ⑴ ⑵ around the outer ring; the It said the value of the class include an axial cyclone (8), two axial cyclone (9), the sleeve (10) and the value of the class-divergent section (20), and an axial cyclone ⑶ two axial swirler (9) may be the same rotating direction opposite said one axial swirler (8) surrounding the centrifugal nozzle (7) outside, and the two axial swirler (9) Outside around the level of the axial cyclone (8), axially between the primary cyclone (8) and second axial cyclone (9) the value of the class-divergent section (20), and the value of the class-divergent section (20) is located axially primary cyclone (8) at the outlet, and the sleeve (10) is arranged outside the second axial cyclone (9); the main level includes a master class cyclone (11), the main stage for the pipeline (15), set the oil chamber (16), direct-fuel spout (17), expansion of primary income segment (12) and the main stage premix ring chamber (22), said primary cyclone (11) around the outside of the sleeve (10), and the fuel injector (21), the main stage for the pipeline (15), set the oil chamber (16), direct-fuel spout (17 ), the primary cyclone (11), the main stage premix annular cavity (22) in turn connected, and the direct-fuel injection port 17 is disposed in the primary swirler vane channel 11, while the expansion of primary income segment (12) is provided at the outlet of the main stage premix ring chamber (22); with a head inner cooling assembly (3) disposed between the primary and the value of the class, inner cooling air through the head assembly (3) the head of the inner cooling holes (18) to enter, to head the inner profile splash plate (19) the impact of cooling; disposed between the primary and the flame tube with a head outer cooling assembly (4), outer cooling air through the head assembly head outer cooling holes (13) (4) to enter, the head outer profile splash plate (14) the impact of 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。 2. According to the claim 1 primary fuel direct injection lean premixed combustion pollution pre-evaporation, wherein: the primary blade axial cyclone (8), the value segment and expand income class two axial cyclone (9) of the blade through the whole machining, welding, etc. integrally cast or processed to form a sleeve (10) and the value of the class file splash plate (19) and head inner cooling assembly (3) Welding connected head inner cooling assembly (3) and the main stage (2) are connected by welding or by a bolt connected to the main stage (2) and the head of the outer ring cooling assembly (4) are welded or bolted, the main stage set oil chamber and main stage (2) can be connected to each other by welding or bolts.
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。 3. According to the second main stage direct fuel injection in a pre-evaporator lean premixed combustion pollution claims, wherein: the fuel direct-spout (17) the number of distribution points on the ring is 6~36 .
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。 4. The fuel of claim 3 primary lean premixed direct injection combustion chamber pre-evaporation pollution, characterized in that: said axial swirler value class level (8) of the swirl angle of 20 number of blades ~45 , primary axial cyclone (8) is 8~16 sheet, and ⑶ primary swirler vane axial rotation along the air flow direction is clockwise or counterclockwise, rotation of the spray On the contrary; the value of the Class II axial cyclone (9) blade mounting angle of 25 ~45 , number of blades is 8~20; two axial cyclone (9) and a mounting angle swirl vane stage axial cyclone (8) opposite or same Vane 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 premixed according to claim 4, wherein the primary direct fuel injection and pre-evaporation of low-pollution combustion chamber, 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 the primary claim direct injection of fuel lean premixed pre-evaporation chamber pollution, characterized in that: said primary swirler (11) is a radial or axial cyclone swirler ; said radial swirler blade mounting angle of 40 ~60 , the number of blades is 12~40; said axial swirler blade mounting angle of 30 ~70 , the number of blades is 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%。 6 according to claim said primary fuel lean premixed direct injection combustion chamber pre-evaporation pollution, characterized in that: said combustion head 50% ~ 85% of the total combustion air in an amount of the air amount , which accounted for 60% of the primary air volume ~ 90% of the head, the value of class 10% ~ 40% of the head air volume.
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 according to claim 7 main stage direct fuel injection and pre-evaporation of low-pollution combustion chamber, wherein: the cooling flame tube (5) with full coverage film cooling, cooling or the impact of diverging Other composite cooling, the flame tube rear according to actual needs are arranged a plurality of mixing holes.
Description  translated from Chinese
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-level direct fuel injection lean premixed combustion chamber pre-evaporation pollution

技术领域 TECHNICAL 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 main-stage direct fuel injection lean premixed combustion chamber pre-evaporation pollution, belong to aero-engine technology.

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] Currently, civil aviation engines to increasing atmospheric emissions of 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 satisfy ICAO CAEP ICAO standards, the current implementation is 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。 To meet the CAEP standards, the major aero-engine companies and research institutions have conducted traitor pollution combustion technology research traitor, GE has developed a bicyclic premixed swirl (Twin Annular Premixing Swirler, TAPS) combustor technology, emissions in 1996 ICAO low standard of about 65%; Pratt & Whitney uses RQL combustion technology developed 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] The traditional military aircraft main diffusion combustion chamber is used in 100% condition, the primary combustion zone GOR GOR chemical proper design, high combustion efficiency, but the main combustion zone gas temperature is very high, it will produce a large number of thermal-type NOx; while in idle conditions, the combustion efficiency is low, incomplete combustion pollutants CO and UHC therefore generate 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。 Thus, the conventional diffusion combustion is 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, in the research of civil aviation engine combustion chamber mainly lean premixed combustion pollution pre-evaporation, the core idea is to classify air and fuel, air, respectively, from the main stage / main mode and value Class / paratypes into the combustion chamber head, the value of the class generally use low flow pressure atomizing nozzles diffusion combustion mode, and the main stage is generally carried out partially premixed combustion, in order to achieve a pre-evaporation chamber lean premixed combustion, since the main stage combustion temperature uniformity, thereby reducing pollutant emissions.

发明内容 SUMMARY OF THE INVENTION

[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] insufficient to address the problem of the present invention proposes a primary fuel direct injection lean premixed pre-evaporation polluting combustion chamber at aircraft engines to meet performance conditions, can effectively reduce the aero-engine combustion room pollution emissions, including 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 to solve the above technical problem proposed solution is: A main stage direct fuel injection lean premixed pre-evaporation pollution combustor includes a combustion chamber head, liner, combustor inner channel (25 ), combustor outer channel

(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 injection rod (21) and casing, injection rod (21) is mounted on the casing (6), the combustion chamber through the injector head rod (21) connected to the receiver, and the combustion chamber head combustion chamber inner channel (25) and the combustion chamber outer channel (24) according to the law of flow distribution design, the fuel injector (21) is provided with a value class centrifugal nozzle (7) and the main stage for the pipeline (15) double oil pipeline, said chamber head circular cavity bicyclic structure, divided into value Class / Vice-mode (I) and the main stage / master mold (2) in two parts, and the main stage (2) around the the value of class (I) of the outer ring; said value comprises an axial cyclone class (8), two axial cyclone (9), the sleeve (10) and the value of the class-divergent section (20) , an axial swirler ⑶ with two axial swirler (9) may be the same rotating direction opposite said one axial swirler (8) surrounding the centrifugal nozzle (7) outside, and Secondary axial swirler (9) surrounds the axially outer primary cyclone (8), the connection between the primary duty ⑶ axial swirler and a secondary swirler axis (9) level income expanded section (20), and the value of the class-divergent section (20) is located in an axial cyclone (8) at the outlet, 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) located outside the second axial cyclone (9); the main level includes a primary cyclone (11), the main stage for the pipeline (15), set the oil chamber (16), direct-fuel vents (17), the primary income expanded section (12) and the main stage premix ring chamber (22), said primary cyclone (11) around the outside of the sleeve (10), and the fuel injector (21) , the main stage for the pipeline (15), set the oil chamber (16), direct-fuel spout (17), the primary cyclone (11), the main stage premix annular cavity (22) in turn connected, and the direct-fuel spout 17 is arranged in the primary swirler vane channel 11, while the expansion of the primary income segment (12) is provided at the main stage premix ring chamber (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: Setting the value between the primary and the head of the class have inner cooling assembly (3), the head of the inner cooling hole inner cooling air through the head assembly (3) (18) enter the inner profile of the head splash plate (19) the impact of cooling; while cooling the outer ring of the head assembly (4) is provided between the main stage and the flame tube, the outer ring of cooling air through the head assembly (4) head cooling holes on the outer ring (13) to enter, the head outer profile splash plate (14) the impact of 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] Preferred: Leaves the primary axial cyclone (8), the value of expanding income class segment with the secondary axial cyclone (9) of the blade through the whole machining, welding, casting or the whole way processed to form a sleeve (10) and the value of the class file splash plate (19) and head inner cooling assembly (3) associated welding head inner cooling assembly (3) and main stage (2) linked by welding or linked by a bolt, main stage (2) cooling the outer ring of the head assembly (4) are welded or bolted, the main stage set oil chamber and the main stage

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

[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] Advantageously: the fuel direct-spout (17) number distribution on the 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] Preferably: the value of the class primary axial swirler (8) of the swirl angle of 20 ~45 , the number of primary axial swirler vanes (8) is 8~16 sheet, and stage axial cyclone (8) to the rotation of the blade along the flow direction may be clockwise or counterclockwise, opposite to the rotation of the spray principle; the value of Class II axial swirler (9) mounting the 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 , number of blades is 8~20; two axial cyclone (9) Vane Axial mounting angle with the primary cyclone (8) opposite or same Vane mounting angle.

[0010] 优选的:所述套筒(10)的扩张角度为8〜20。 [0010] Preferably: the 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: said primary swirler (11) for the radial swirler or axial swirler; said radial swirler blade mounting angle of 40 ~60 , the number of blades is 12 ~ 40; the axial swirler blade mounting angle of 30 ~70 , number of leaves 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] Preferably: the air accounts for 50% ~ 85% of the total combustion air amount of the combustion head, wherein the main combustion stage 60% ~ 90% of the amount of air the head, the head of the pre-combustion stage accounted 10% ~ 40% air content.

[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] Advantageously: the cooled flame tube (5) with full coverage film cooling, the impact of diverging or other complex cooling methods to cool the rear of the actual needs of the flame tube disposed a plurality of mixing holes.

[0014] 本发明的工作过程: [0014] The present invention works:

[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 air from the high pressure compressor from the diffuser (23) into the combustion chamber, respectively, in three columns into the combustion chamber after the inner channel (25), combustion head and combustion chamber outer channel (24), inside , respectively, from the air passage outer liner

(5)上的掺混孔和气膜冷却孔进入火焰筒。 Blended hole and film cooling holes (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 combustion air in the combustion chamber is fed from the head, the other gas are fed from the flame tube. 而燃烧室头部包括值班级⑴和主级⑵。 The combustor head including value class and the main stage 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入燃烧区,形成贫油预混燃烧。 ⑴ in the value of the class, fuel (5% ~ 50% of total fuel) by centrifugation nozzle (7) and initial discharge atomized by around from around the primary axial cyclone (8) airflow the impact crusher, the formation of secondary atomization, then the value of the class-divergent section (20) by an axial cyclone outlet (8) and two axial cyclone (9) outlet flow shear broken three times atomized fuel-air mixture into the combustion chamber after mixing the main combustion zone is partially diffusion combustion, the formation of a stable source of ignition; for the main stage, fuel (50% ~ 95% of total fuel) from the supply pipe (15) into the main stage set oil chamber (16), and then by the main stage direct fuel spout (17) were discharged, you can adjust the main stage direct-fuel injection orifice angular and axial position to adjust the primary fuel atomization case, since the primary fuel direct-spout (17) is disposed in the main stage blade path, and since the fuel injection direction of the primary air flow perpendicular to each other or relative, the fuel in the main stage aerodynamic effects, achieve crushing, atomizing, after entering the main stage pre- After mixing ring chamber (22), premixed fuel and air in the ring cavity (22) and mixing continued within and partially evaporate 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 a primary fuel direct injection lean premixed combustion chamber pre-evaporation pollution, compared to the prior art, has the following beneficial effects:

[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 and a pressure atomizing nozzles, forming a diffusion flame, it is possible to provide a stable ignition sources, taking into account the ignition / extinction performance as well as local conditions 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 consists of a radial or axial cyclone swirler cavity with a plurality of fuel injection holes directly composition, and thus pre-partially evaporated uniform premixed combustion, lowers the high temperature hot spots, thus reducing the large conditions NOx, smoke, CO and UHC emissions, and simply the 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 main combustion stage air intake accounts for about 40% ~ 70% of the diffuser intake, while 50% ~ 95% of the total fuel oil, and were part of the pre-premixed in the cavity evaporation, so the basic realization of the pre-evaporation 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 provided value class income expanded section (20), the primary income expanded section (12), thereby effectively preventing pre-evaporation lean premixed combustion tempering nozzle coke 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. Because the inner cooling air through the head assembly head inner cooling holes (3) (18) to enter, to head the inner profile splash plate (19) the impact of cooling air through the head at the same time Department of outer cooling assembly head outer cooling holes (4) on

(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 the outer profile of the head splash plate (14) the impact of cooling, thus prolonging the life of the combustion chamber of the head.

[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. Because cooling the flame tube (5) with full coverage film cooling, cooling or other composite impact divergence cooling, thereby controlling the flame tube wall temperature, thus prolonging the life of the flame tube; according to the flame tube rear the actual need to blend holes arranged 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 combustion chamber head an enlarged view of the structure of FIG. 1;

[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] where:...... 1 value Class / deputy dies, 2 primary / primary mode, 3 head inner cooling assembly, the head of the outer ring cooling assembly 4, 5 fire extinguishers, 6 receiver, 7 The value of the class centrifugal nozzle, 8.- stage axial cyclone, 9 two axial cyclone, 10 sleeve, 11 primary cyclone, 12 primary income expansion segment 13 head Department of outer cooling holes, 14 head outer profile splash plate, 15 primary supply pipe, 16 sets oil chamber, 17 direct-fuel vents, 18 head inner cooling holes, 19. the head of the inner profile splash plate 20. Divergent value class segment, 21 injection rod, 22 main stage premix ring cavity 23. diffuser, 24. The combustor outer channel, 25 inner chamber 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 view of a preferred embodiment of the present invention, described in detail hereinafter in conjunction with the accompanying drawings aspect of the present invention.

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。 A lean premixed main stage fuel direct injection embodiment [0027] The pre-evaporator low pollution combustion chamber 1 and 2, the head including a combustion chamber, a flame tube 5, the inner passage 25 of the combustion chamber, the combustion outdoor ring channel 24, fuel injector 21 and the casing, injection rod 21 is mounted on the casing 6, on the one hand to the head oil chamber, on the other hand to bear part of the mechanical strength, the combustion chamber through the injector head lever 21 is connected with the casing 6, and combustion head, combustion chamber inner passage 25 and the combustion chamber outer flow channel 24 Distribution of press design, interior, air outer passage holes respectively, from the blend of flame on the gas cylinder 5 film cooling hole into the flame tube, the fuel injector 21 is provided with a value class centrifugal nozzle 7 and the main stage for double oil pipeline tubing 15, the combustion chamber head circular cavity bicyclic structure, divided into value classes / Paratype I and the main stage / main die 2 in two parts, and the main stage 2 around the outer ring of the value of class I; the value of the class includes an axial cyclone 8, two axial cyclone 9, the sleeve 10 and the value of the class Divergent section 20, an axial swirler 8 and the two axial cyclone 9 may be the same direction of rotation may be reversed, wherein an axial swirler 8 surrounds Value Class centrifugal nozzle 7 outside, while the secondary axial cyclone 9 surround the outside of the axial cyclone 8 level, the primary and secondary axial cyclone 8 between the axial cyclone 9 Divergent connection value class section 20, and the value of class income level diffuser section 20 located at the outlet of the axial cyclone 8, the value of the class-divergent section 20 is equivalent to the venturi tube constriction and dilation angle angle segment design are important, can effectively prevent tempering nozzle carbon deposition, while the sleeve 10 is disposed outside the second axial cyclone 9; main level includes a primary cyclone 11, the main stage for the pipeline 15, set oil chamber 16, the fuel direct-injection port 17, the primary income expanded section 12 and 22, the main stage cyclone primary premix ring around the outside of the chamber 11 of the sleeve 10, and the fuel injector 21, the main stage oil pipe 15, set the oil chamber 16, the fuel direct-injection port 17, the main stage cyclone 11, the main stage premix ring chamber 22 in turn is connected, and a direct-fuel injection port 17 is disposed in the primary swirler vane channel 11, At the same time the primary income expanded section 12 provided at the outlet ring main stage premix chamber 22.

[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] 2 and the value of the primary class disposed between the inner ring I head cooling assembly 3, the inner cooling air through the head assembly head cooling holes 3 on the inner ring 18 to enter the inner ring of the head profile splash plate 19 is impingement cooling; and between the main stage and the flame tube have set the head outer cooling unit 4, the outer ring of cooling air through the head assembly head cooling holes 4 of the outer ring 13 to enter, to the head of the outer ring gear splash plate 14 impingement cooling.

[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 primary axial swirl vane, the value of expanding income class segment and the secondary axial cyclone 8 9 by integral machining, welding, etc. integrally cast or processed form, the sleeve 10 and the value class file splash plate 19 and the head inner cooling assembly 3 associated welding head 3 and the inner ring cooling assembly by welding the main stage 2 associated or linked by bolts, main stage 2 and the head outer cooling assembly 4 are welded or bolted, the main stage set oil chamber and the main stage 2 may be connected to each other by welding or bolts.

[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-fuel injection port 17 on the ring number distribution, spray angle and an axial distance can be determined based on the desired operating state and the number of primary blades, said fuel direct-injection port 17 on the ring 6~36 a number of distribution, direct-fuel injection orifice angle 17 between a 45 ~45 , so that the main stage premix fuel mixing chamber 22 is more uniform; and depending on the operating conditions, fuel direct-injection The number of open spout 17 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。 [0031] The value of the class level axial cyclone swirl angle 8 of 20 ~45 , the number of blade stage axial cyclone 8 is 8~16 sheet, as determined in accordance with the actual situation, a spin-stage axial cyclone 8 blades along the flow direction to be clockwise or counterclockwise rotation principle and spray the opposite; the value of the Class II axial cyclone 9 blade mounting 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 , number of blades is 8~20; two axial cyclone 9 Vane axial mounting angle with the primary cyclone 8 Vane mounting angle of the opposite or the same.

[0032] 所述套筒10的扩张角度为8〜20。 Expansion 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] 11 of the primary cyclone swirler radial or axial swirler; said radial swirler blade mounting angle of 40 ~60 , the number of blades is 12~40; the Axial swirler blade mounting angle of 30 ~70 , 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 combustion chamber of the head portion of the total combustion air accounts for the amount of air, wherein the main combustion stage 60% ~ 90% of the amount of air the head, the head of the pre-combustion stage representing the amount of air 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 cooled flame tube 5 with full coverage film cooling, cooling or other composite impact divergence cooling, it is possible to control the flame tube wall temperature, thus extending the life of the flame tube; the flame tube rear actual It requires a plurality of mixing holes are arranged so as to control the combustor exit temperature distribution.

[0036] 本发明的工作过程: [0036] The present invention works:

[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 the [0037] from the air from the high pressure compressor diffuser 23 into the combustion chamber, respectively, after three columns inner passage 25 into the combustion chamber, combustion head and combustion chamber outer channel 24, inner, outer air passage respectively, into the flame tube from mixing and film cooling holes 5 holes on 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,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,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入燃烧区,形成贫油预混燃烧。 Most of combustion air in the combustion chamber is fed from the head, the other with a gas cylinder from the flames were fed, and the combustion chamber head includes value classes I and the main stage 2ο in value in class I, fuel (total fuel 5 % ~ 50%) by the centrifugal ejection nozzle 7 and initial atomization, surrounded by the impact from the level at around 8 axial cyclone airflow crushing, secondary atomization is formed, then the value of the class-divergent section 20 export of primary and secondary axial cyclone 8 9 axial cyclone outlet stream atomizing shear broken three times, blended fuel-air mixture into the combustion chamber after the main combustion zone is partially diffusion combustion to form a stable ignition source; for the main stage, fuel (50% ~ 95% of total fuel) into the main stage set oil chamber 16 from the supply pipe 15, and then were directed by the primary fuel ejection port 17, you can adjust the main stage direct fuel type angular and axial position of the ejection orifice, to adjust the primary fuel atomization case, since the primary fuel direct-injection port 17 is disposed in the primary passage 11 of the swirler vane, and the fuel injection direction due to the air flow direction with the primary mutual vertical or relative, the fuel in the primary aerodynamic role in achieving the crushing, atomization, after entering the main stage premix ring chamber 22, continue mixing fuel and air in the chamber after 22 premix ring and partially evaporate into the combustion zone to form lean premixed combustion.

[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。 [0038] as described above in conjunction with the accompanying drawings of the preferred embodiment of the present invention is used to illustrate specific embodiments of the invention only, and not as a limitation on the content and scope of the foregoing object of the invention and the appended claims, all in accordance with the inventive technique the substance of any of the above cases simple modifications made to the implementation of equivalent variations and modification are still technical and rights protection scope of the present invention.

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Classifications
International ClassificationF23R3/38, F23R3/30
Legal Events
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29 May 2013C06Publication
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12 Aug 2015C14Granted