Nothing Special   »   [go: up one dir, main page]

WO2022193067A1 - 用于抑制燃烧振荡的燃烧室和燃烧器 - Google Patents

用于抑制燃烧振荡的燃烧室和燃烧器 Download PDF

Info

Publication number
WO2022193067A1
WO2022193067A1 PCT/CN2021/080781 CN2021080781W WO2022193067A1 WO 2022193067 A1 WO2022193067 A1 WO 2022193067A1 CN 2021080781 W CN2021080781 W CN 2021080781W WO 2022193067 A1 WO2022193067 A1 WO 2022193067A1
Authority
WO
WIPO (PCT)
Prior art keywords
combustion
outlet end
stage
combustion stage
face
Prior art date
Application number
PCT/CN2021/080781
Other languages
English (en)
French (fr)
Inventor
韩啸
韩猛
林宇震
周宇晨
Original Assignee
北京航空航天大学
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 北京航空航天大学 filed Critical 北京航空航天大学
Priority to PCT/CN2021/080781 priority Critical patent/WO2022193067A1/zh
Publication of WO2022193067A1 publication Critical patent/WO2022193067A1/zh

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means

Definitions

  • the present application relates to the technical field of energy and power, and in particular, to a combustion chamber and a burner for suppressing combustion oscillation.
  • combustion oscillation is a common technical challenge in various types of burners, which are widely found in boilers, gas water heaters, gas turbines and other combustion devices.
  • advanced combustion devices often use lean premixed combustion mode, and combustion devices are often in a state near flameout Work is very sensitive to external disturbances, and is easily affected by external disturbances, resulting in heat release rate fluctuations.
  • active control is to use special monitors and active actuators to actively apply appropriate external excitation (for inlet air or fuel supply, etc.) according to the monitored signals such as pressure pulsation in the combustion system to suppress or eliminate the heat release rate. Coupling between pulsations and pressure oscillations (sound waves).
  • passive control refers to the addition of fixed devices to the combustion system to suppress or eliminate combustion oscillations.
  • acoustic components such as Helmholtz resonators
  • Helmholtz resonators can suppress combustion oscillations at specific frequencies.
  • the disadvantage is that the volume is large, and it can only be effective for a specific frequency, so a lot of experiments and debugging need to be done in advance.
  • the present application aims to solve at least one of the technical problems existing in the prior art. Therefore, the present application proposes a combustion chamber for suppressing combustion oscillation, so as to suppress the occurrence of the phenomenon of combustion oscillation.
  • the application also proposes a burner.
  • the pre-combustion stage including a central body and a pre-combustion stage swirler and an interstage disposed on the periphery of the central body;
  • the main combustion stage is arranged on the periphery of the pre-combustion stage, and the main combustion stage includes a main combustion stage swirler and a main combustion stage outer ring;
  • a combustion chamber main body comprising an end wall and a side wall, the end wall connecting the main combustion stage outer ring and the side wall;
  • an anti-vibration ring fixed on the inner surface of the end wall of the end wall and/or the outer ring outlet end face of the outer ring of the main combustion stage, and the anti-vibration ring is formed in a direction facing away from the main combustion stage
  • the flame channel is gradually expanding, the inlet end of the flame channel is butted with the outlet end of the main combustion stage, and the outlet end of the flame channel is communicated with the inner cavity of the combustion chamber main body.
  • combustion oscillation is generally suppressed by machining the end wall or the side wall of the combustion chamber to have a conical transition structure, while the combustion chamber described in the present application is at the end of the end wall.
  • the same effect can be achieved by installing the anti-vibration ring on the inner surface of the wall and/or the outlet end face of the outer ring of the outer ring of the main combustion stage; compared with the combustion chamber of the prior art, the combustion chamber of the present application has a retrofit cost Low, the advantages of a wide range of applications.
  • the pre-stage, the main combustion stage, the combustion chamber main body and the anti-vibration ring are all arranged coaxially.
  • the inner wall of the anti-vibration ring is formed with a flow spoiler.
  • the spoiler includes a plurality of steps distributed along the axis of the central body, or,
  • the spoiler portion includes a plurality of annular spoiler grooves distributed along the axis of the central body, or,
  • the spoiler portion includes a longitudinal spoiler groove penetrating the inner wall along the axis direction of the central body, and the number of the longitudinal spoilers is plural and distributed along the circumference of the inner wall.
  • the cross section of the inlet end and the cross section of the outlet end are both circular, or both the cross section of the inlet end and the cross section of the outlet end are oval.
  • the interstage section includes an outlet end face of the interstage section
  • the main combustion stage swirler includes an outlet end face of the main combustion stage swirler
  • the outlet end face of the interstage section is connected to the outer ring.
  • the outlet end face is misaligned.
  • the outlet end surface of the outer ring and the inner surface of the end wall are coplanar.
  • the distance between the outlet end face of the main combustion stage swirler and the outlet end face of the interstage section along the axial direction of the central body is a first distance; the main combustion stage swirler The distance between the outlet end face and the outlet end face of the outer ring along the axial direction of the central body is a second interval, and the first interval is greater than the second interval.
  • the distance between the outlet end face of the main combustion stage swirler and the outlet end face of the interstage section along the axial direction of the central body is a first distance; the main combustion stage swirler The distance between the outlet end face and the outlet end face of the outer ring along the axial direction of the central body is a second pitch, and the first pitch is smaller than the second pitch.
  • a burner according to an embodiment of the second aspect of the present application includes the combustion chamber for suppressing combustion oscillation according to any one of the above embodiments, and the burner is a swirl cup structure burner, a multi-swirl burner or a center burner Staged burners.
  • the burner according to the embodiment of the present application includes the above-mentioned combustion chamber, it has all the technical effects of the above-mentioned combustion chamber, which will not be repeated here.
  • FIG. 1 is a schematic diagram of a partial structure of a combustion chamber for suppressing combustion oscillation provided by an embodiment of the present application
  • FIG. 2 is a schematic diagram of a partial structure of a spoiler provided by an embodiment of the present application.
  • FIG. 3 is a schematic diagram of a partial structure of another spoiler provided by an embodiment of the present application.
  • FIG. 4 is a schematic diagram of a partial structure of still another spoiler provided by an embodiment of the present application.
  • FIG. 5 is a schematic diagram of another partial structure of a combustion chamber for suppressing combustion oscillation provided by an embodiment of the present application.
  • FIG. 6 is a schematic diagram of another partial structure of a combustion chamber for suppressing combustion oscillation provided by an embodiment of the present application.
  • connection and “connected” should be understood in a broad sense, for example, it may be a fixed connection or a detachable connection, Or integral connection; it can be mechanical connection or electrical connection; it can be directly connected or indirectly connected through an intermediate medium.
  • connection should be understood in a broad sense, for example, it may be a fixed connection or a detachable connection, Or integral connection; it can be mechanical connection or electrical connection; it can be directly connected or indirectly connected through an intermediate medium.
  • the first feature "on” or “under” the second feature may be in direct contact with the first and second features, or the first and second features pass through the middle indirect contact with the media.
  • the first feature being “above”, “over” and “above” the second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is level higher than the second feature.
  • the first feature being “below”, “below” and “below” the second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature has a lower level than the second feature.
  • the combustion chamber includes a pre-combustion stage, a main combustion stage, a combustion chamber main body and an anti-vibration ring 7
  • the pre-combustion stage includes a central body 1 and the pre-combustion stage swirler 2 and the interstage section 3 arranged on the periphery of the central body 1
  • the main combustion stage is arranged on the periphery of the pre-combustion stage
  • the main combustion stage includes the main combustion stage swirler 4 and the main combustion stage outer ring 5
  • the main combustion chamber body includes an end wall 6 and a side wall 8, and the end wall 6 is connected to the main combustion stage outer ring 5 and the side wall 8
  • Outlet end, and the anti-vibration ring 7 is formed with a flame channel 71 that is gradually expanding in the direction away from the main combustion stage, the inlet end of the flame channel 71 is butted with the outlet end of the main combustion stage, and the outlet end of the
  • the anti-vibration ring 7 is formed with a flame channel 71 that gradually expands in the direction away from the main combustion stage.
  • a flame channel 71 that gradually expands in the direction away from the main combustion stage.
  • the channel 71 flows, so that the flame front will flow as close to the inner wall of the flame channel 71 as possible, thereby reducing the heat release rate pulsation, decoupling it from the combustion system acoustic system, and finally suppressing combustion oscillation.
  • combustion oscillation is generally suppressed by processing the end wall 6 or side wall 8 of the combustion chamber to have a conical transition structure, while the combustion chamber of the present application is only located at the outlet end face 11 and/or end wall of the outer ring.
  • the same effect can be achieved by installing the anti-vibration ring 7 on the inner surface; compared with the combustion chamber of the prior art, the combustion chamber of the present application has the advantages of low modification cost and wide application range.
  • the anti-vibration ring 7 is connected with the end wall 6 and/or the main combustion stage outer ring 5 by means of integral processing, welding or fastener connection.
  • the connection manner between the anti-vibration ring 7 and the end wall 6 and/or the main combustion stage outer ring 5 is not limited by the examples herein.
  • the anti-vibration ring 7 is a hollow cylinder, a hollow truncated cone or a hollow cubic structure.
  • the shape of the anti-vibration ring 7 is similar to that of the flame channel 71 , and the anti-vibration ring 7 is a hollow circular truncated structure, and gradually expands in the direction away from the main combustion stage shape extension.
  • the anti-vibration ring 7 designed in this way can reduce its thickness to the limit on the premise of ensuring the structural strength and thermal load, thereby reducing the weight of the combustion chamber.
  • the pre-stage, the main combustion stage, the combustion chamber main body and the anti-vibration ring 7 are all arranged coaxially.
  • the anti-vibration ring 7 extends in the axial direction of the central body 1 . It should be noted that the anti-vibration ring 7 may also extend in other directions, as long as the anti-vibration ring 7 has a flame channel 71 formed in the anti-vibration ring 7 which is gradually expanding in the direction away from the main combustion stage.
  • a spoiler is formed in the flame channel 71 .
  • the spoiler can change the flow trajectory of the flame front in the flame channel 71, and further improve the effect of the anti-vibration ring 7 in suppressing combustion oscillation.
  • the spoiler includes one or more of a step 711, an annular spoiler groove 712 and a longitudinal spoiler groove 713.
  • the structure of the spoiler is not limited by the examples here, as long as the flame front can be changed in the flame passage.
  • the flow trajectory in 71 is sufficient.
  • the spoiler includes a plurality of steps 711 distributed along the axial direction of the central body 1 . Based on the Coanda effect, the flame front is close to the step 711, and the step 711 interferes with the normal flow of the flame.
  • the spoiler portion includes a plurality of annular spoiler grooves 712 distributed along the axial direction of the central body 1 . Based on the Coanda effect, the flame flows circumferentially around the annular spoiler groove 712 .
  • the width f and the height e of the annular spoiler groove 712 are both in the range of 2-10 mm.
  • the spoiler includes a plurality of longitudinal spoiler grooves 713 penetrating the flame channel 71 along the axial direction of the central body 1 , and the longitudinal spoiler grooves 713 are along the flame channel Circumferential distribution of 71. Based on the Coanda effect, the flame is divided at the entrance end of the flame channel 71 by the respective longitudinal spoiler grooves 713.
  • the cross section of the inlet end of the flame channel 71 and the cross section of the outlet end of the flame channel 71 are both circular, or the cross section of the inlet end of the flame channel 71 and the cross section of the outlet end of the flame channel 71 are circular All are oval.
  • the cross section is circular or oval to satisfy the Coanda effect.
  • the shape of the flame channel 71 may also be: the cross section of the inlet end is circular, and the shape of the cross section of the outlet end is oval.
  • the diameter of the cross section of the inlet end of the flame channel 71 is 1-3 times the diameter D of the outlet end of the main combustion stage, and the channel side wall of the flame channel 71
  • the included angle ⁇ between the plane where the plane is located and the plane where the outlet end face 51 of the outer ring is located is in the range of 0-90°.
  • the maximum channel length of the flame channel 71 is 3 times the diameter D of the outlet end of the main combustion stage.
  • the dimension of the long axis of the cross section of the inlet end is 1-3 times the diameter D of the outlet end of the main combustion stage
  • the dimension of the short axis of the cross section of the inlet end is the size of the main combustion stage 1-3 times the diameter D of the outlet end.
  • the main changes are the included angle ⁇ and the channel length L 0 , different channel lengths L 0 provide different attachment areas for the flame, thereby changing the flame shape and suppressing the combustion chamber oscillation; at the same time, the change of the included angle ⁇ , due to the Coanda effect, will cause the fluid to follow the channel wall of the flame channel 71 .
  • the anti-vibration ring 7 is fixed on the inner surface of the end wall 6 , and the main variable is the distance between the side wall at the inlet of the flame channel 71 and the inner side wall of the outlet end face 11 of the outer ring.
  • Difference L different differences will lead to changes in the shape of the flame.
  • the main combustion stage flame 9 will have a double root state, which can play a beneficial role in the stability of the flame.
  • the pre-combustion stage flame 10 is generally stabilized at the two edge points of the interstage section 3 at the same time, and serves to provide a high temperature recirculation zone to keep the entire flame sustaining combustion.
  • the interstage section 3 includes an outlet end face of the interstage section
  • the main combustion stage swirler 4 includes an outlet end face of the main combustion stage swirler
  • the main combustion stage outer ring 5 includes an outer ring outlet end face 11
  • the combustion chamber end wall 6 includes the inner surface of the end wall; the outlet end face of the interstage section and the outlet end face 11 of the outer ring are arranged in a staggered position.
  • the dislocation of the outlet end face of the interstage section and the outlet end face 11 of the outer ring can change the starting position of the inner and outer shear layers of the swirl flow, thereby affecting the flame position in the inner cavity of the combustion chamber main body, and realizing the regulation of combustion oscillation.
  • the outlet end surface 11 of the outer ring and the inner surface of the end wall are coplanar, so as to facilitate the installation of other equipment such as the anti-vibration ring 7 in the combustion chamber.
  • the distance between the outlet end face of the main combustion stage swirler and the outlet end face of the interstage section along the axis direction of the central body 1 is the first distance; the outlet end face of the main combustion stage swirler and the outlet of the outer ring
  • the spacing distance between the end faces 11 along the axis of the center body 1 is the second spacing, the first spacing is greater than the second spacing, and the value of the first spacing is S.
  • the separation distance of the direction is H, where S and H are both set values, and both can take values in the corresponding interval, and H/S ⁇ 1.
  • the first distance is greater than the second distance, and the value of the second distance is S, and H/S ⁇ 1.
  • the first distance is smaller than the second distance, and the value of the first distance is S, and H/S ⁇ 1.
  • the first distance is smaller than the second distance, and the value of the second distance is S, and H/S ⁇ 1.
  • Another embodiment of the present application provides a burner, including the combustion chamber provided by any of the technical solutions of the present application.
  • the burners include, but are not limited to, conventional swirl cup burners, multi-swirl burners, and center stage burners.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

一种用于抑制燃烧振荡的燃烧室及包括该燃烧室的燃烧器。燃烧室包括：预燃级、主燃级、燃烧室主体和防振环（7）；预燃级包括中心体（1）以及设置在中心体（1）外围的预燃级旋流器（2）和级间段（3）；主燃级设置在预燃级外围，主燃级包括主燃级旋流器（4）和主燃级外环（5）；燃烧室主体包括端壁（6）和侧壁（8），端壁（6）连接主燃级外环（5）和侧壁（8）；防振环（7）固定于端壁（6）的内表面和/或主燃级外环（5）的出口端，且防振环（7）形成有沿着背向主燃级的方向呈渐扩状的火焰通道（71）。该燃烧室具有改装成本低，适用范围广的优点。

Description

用于抑制燃烧振荡的燃烧室和燃烧器 技术领域
本申请涉及能源与动力技术领域，尤其涉及一种用于抑制燃烧振荡的燃烧室和燃烧器。
背景技术
人类获取能源和动力的方式依旧主要是化石燃料的燃烧。在能源与动力领域的相关应用设备中，燃烧振荡是各类燃烧器中常见的技术挑战，广泛的存在于锅炉，燃气热水器，燃气轮机等燃烧装置中。特别是在越来越严格的排放要求下，为了减少以氮氧化物(NOx)为主的污染物排放，现在先进燃烧装置常采用贫油预混燃烧模式，燃烧装置常常在临近熄火的状态下工作，对外界的扰动十分敏感，容易受到外界扰动，产生释热率脉动。当释热率脉动与燃烧系统声学耦合时(可简单理解为满足瑞利准则)，则容易引发大幅度的释热率脉动和压力脉动，轻则影响燃烧装置的稳定工作，重则造成燃烧装置或其他部件的结构损坏，严重地还会威胁到整个系统的运行安全。因此，燃烧振荡是现代先进燃烧装置必须尽力规避的。
为了解决燃烧振荡的问题，多种方法被提出用于控制燃烧振荡，主要可分为主动控制和被动控制两大类。主动控制是使用专门的监测器和主动作动器，根据监测到的燃烧系统内的压力脉动等信号，主动地施加合适的外部激励(对进口空气或燃料供应等)，抑制或消除释热率脉动和压力振荡(声波)之间的耦合。但这类方法需要额外的控制系统和执行装置，对控制算法的要求也很高，会增加额外的成本，适用场景有限。被动控制是指在燃烧系统中加入固定地某些装置，从而抑制或消除燃烧振荡。常见的有各类声学元器件，比如亥姆霍兹共振器，可以抑制特定频率的燃烧振荡。缺点是体积较大，且仅能对特定频率有效，需提前做大量的实验和调试。
发明内容
本申请旨在至少解决现有技术中存在的技术问题之一。为此，本申请提出一种用于抑制燃烧振荡的燃烧室，以抑制燃烧振荡的现象发生。
本申请还提出一种燃烧器。
根据本申请第一方面实施例的用于抑制燃烧振荡的燃烧室，包括：
预燃级，所述预燃级包括中心体以及设置在所述中心体外围的预燃级旋流器和级间段；
主燃级，所述主燃级设置在所述预燃级的外围，所述主燃级包括主燃级旋流器和主燃级外环；
燃烧室主体，包括端壁和侧壁，所述端壁连接所述主燃级外环和所述侧壁；
防振环，固定于所述端壁的端壁内表面和/或所述主燃级外环的外环出口端面，且所述防振环形成有沿着背向所述主燃级的方向呈渐扩状的火焰通道，所述火焰通道的入口端与所述主燃级的出口端对接，所述火焰通道的出口端连通所述燃烧室主体的内腔。
现有技术中，一般通过将燃烧室的所述端壁或所述侧壁加工成具有锥形过渡结构的方式来抑制燃烧振荡，而本申请所述的燃烧室在所所述端壁的端壁内表面和/或所述主燃级外环的外环出口端面安装所述防振环可实现相同的效果；相较于现有技术的燃烧室，本申请所述的燃烧室具有改装成本低，适用范围广的优点。
根据本申请的一个实施例，所述预然级、主燃级、燃烧室主体和所述防振环均同轴设置。
根据本申请的一个实施例，所述防振环的内壁形成有扰流部。
根据本申请的一个实施例，所述扰流部包括沿着所述中心体轴线方向分布的多个台阶，或者，
所述扰流部包括沿着所述中心体轴线方向分布的多个环形扰流槽，或者，
所述扰流部包括沿着所述中心体轴线方向贯穿所述内壁的纵向扰流槽，所述纵向扰流的数量为多个且沿着所述内壁的周向分布。
根据本申请的一个实施例，所述入口端的横截面以及所述出口端的横截面均呈圆形，或者，所述入口端的横截面以及所述出口端的横截面均呈椭圆形。
根据本申请的一个实施例，所述级间段包括级间段出口端面，所述主燃级旋流器包括主燃级旋流器出口端面，所述级间段出口端面与所述外环 出口端面错位设置。
根据本申请的一个实施例，所述外环出口端面和所述端壁内表面共面。
根据本申请的一个实施例，所述主燃级旋流器出口端面与所述级间段出口端面沿所述中心体的轴线方向的间隔距离为第一间距；所述主燃级旋流器出口端面与所述外环出口端面沿所述中心体的轴线方向的间隔距离为第二间距，所述第一间距大于所述第二间距。
根据本申请的一个实施例，所述主燃级旋流器出口端面与所述级间段出口端面沿所述中心体的轴线方向的间隔距离为第一间距；所述主燃级旋流器出口端面与所述外环出口端面沿所述中心体的轴线方向的间隔距离为第二间距，所述第一间距小于所述第二间距。
根据本申请第二方面实施例的燃烧器，包括上述任一项实施例所述的用于抑制燃烧振荡的燃烧室，所述燃烧器为旋流杯结构燃烧器、多旋流燃烧器或中心分级燃烧器。
根据本申请实施例的燃烧器，由于其包括上述燃烧室，因此具有上述燃烧室的所有技术效果，此处不再赘述。
本申请的附加方面和优点将在下面的描述中部分给出，部分将从下面的描述中变得明显，或通过本申请的实践了解到。
附图说明
为了更清楚地说明本申请实施例或现有技术中的技术方案，下面将对实施例或现有技术描述中所需要使用的附图作简单地介绍，显而易见地，下面描述中的附图仅仅是本申请的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据这些附图获得其他的附图。
图1是本申请实施例提供的一种用于抑制燃烧振荡的燃烧室局部结构示意图；
图2是本申请实施例提供的一种扰流部的局部结构示意图；
图3是本申请实施例提供的另一种扰流部的局部结构示意图；
图4是本申请实施例提供的再一种扰流部的局部结构示意图；
图5是本申请实施例提供的另一种用于抑制燃烧振荡的燃烧室局部结构示意图；
图6是本申请实施例提供的再一种用于抑制燃烧振荡的燃烧室局部结构示意图；
附图标记：
1、中心体；2、预燃级旋流器；3、级间段；4、主燃级旋流器；5、主燃级外环；6、端壁；7、防振环；71、火焰通道；711、台阶；712、环形扰流槽；713、纵向扰流槽；8、侧壁；9、主燃级火焰；10、预燃级火焰；11、外环出口端面。
具体实施方式
下面结合附图和实施例对本申请的实施方式作进一步详细描述。以下实施例用于说明本申请，但不能用来限制本申请的范围。
在本申请实施例的描述中，需要说明的是，术语“中心”、“纵向”、“横向”、“上”、“下”、“前”、“后”、“左”、“右”、“竖直”、“水平”、“顶”、“底”、“内”、“外”等指示的方位或位置关系为基于附图所示的方位或位置关系，仅是为了便于描述本申请实施例和简化描述，而不是指示或暗示所指的装置或元件必须具有特定的方位、以特定的方位构造和操作，因此不能理解为对本申请实施例的限制。此外，术语“第一”、“第二”、“第三”仅用于描述目的，而不能理解为指示或暗示相对重要性。
在本申请实施例的描述中，需要说明的是，除非另有明确的规定和限定，术语“相连”、“连接”应做广义理解，例如，可以是固定连接，也可以是可拆卸连接，或一体连接；可以是机械连接，也可以是电连接；可以是直接相连，也可以通过中间媒介间接相连。对于本领域的普通技术人员而言，可以具体情况理解上述术语在本申请实施例中的具体含义。
在本申请实施例中，除非另有明确的规定和限定，第一特征在第二特征“上”或“下”可以是第一和第二特征直接接触，或第一和第二特征通过中间媒介间接接触。而且，第一特征在第二特征“之上”、“上方”和“上面”可是第一特征在第二特征正上方或斜上方，或仅仅表示第一特征水平高度高于第二特征。第一特征在第二特征“之下”、“下方”和“下面”可以是第一特征在第二特征正下方或斜下方，或仅仅表示第一特征水平高度小于第二特征。
在本说明书的描述中，参考术语“一个实施例”、“一些实施例”、“示例”、“具体示例”、或“一些示例”等的描述意指结合该实施例或示例描述的具体特征、结构、材料或者特点包含于本申请实施例的至少一个实施例或示例中。在本说明书中，对上述术语的示意性表述不必须针对的是相同的实施例或示例。而且，描述的具体特征、结构、材料或者特点可以在任一个或多个实施例或示例中以合适的方式结合。此外，在不相互矛盾的情况下，本领域的技术人员可以将本说明书中描述的不同实施例或示例以及不同实施例或示例的特征进行结合和组合。
本申请实施例提供了一种用于抑制燃烧振荡的燃烧室，如图1所示，该燃烧室包括预燃级、主燃级、燃烧室主体和防振环7，预燃级包括中心体1以及设置在中心体1外围的预燃级旋流器2和级间段3；主燃级设置在预燃级外围，主燃级包括主燃级旋流器4和主燃级外环5；燃烧室主体包括端壁6和侧壁8，端壁6连接主燃级外环5和侧壁8；防振环7固定于端壁6的内表面和/或主燃级外环5的出口端，且防振环7形成有沿着背向主燃级的方向呈渐扩状的火焰通道71，火焰通道71的入口端与主燃级的出口端对接，火焰通道71的出口端连通燃烧室主体的内腔。
防振环7形成有沿着背向主燃级的方向呈渐扩状的火焰通道71，工作过程中，基于康达效应，进入火焰通道71的空气和燃料的未燃混合气会贴合火焰通道71流动，从而火焰锋面将会尽可能地贴近火焰通道71的内壁流动，进而减小释热率脉动，使其与燃烧系统声学系统解耦，最终抑制燃烧振荡。
现有技术中，一般通过将燃烧室的端壁6或侧壁8加工成具有锥形过渡结构的方式来抑制燃烧振荡，而本申请的燃烧室仅在外环出口端面11和/或端壁内表面安装防振环7便可实现相同的效果；相较于现有技术的燃烧室，本申请的燃烧室具有改装成本低，适用范围广的优点。
根据本申请的其中一个实施例，防振环7通过整体加工、焊接或紧固件连接的方式与端壁6和/或主燃级外环5连接。当然，防振环7和端壁6和/或主燃级外环5之间的连接方式不受此处举例限制。
根据本申请的其中一个实施例，防振环7为空心的圆柱体、空心的圆台或者空心的立方体结构。
根据本申请的另外一个实施例，如图1所示，防振环7与火焰通道71的形状相似，防振环7为空心的圆台结构，且沿着背向主燃级的方向呈渐扩状延伸。如此设计的防振环7可在保证结构强度和热负荷的前提下使自身厚度缩小到极限，从而减轻燃烧室的重量。
根据本申请的其中一个实施例，如图1所示，预然级、主燃级、燃烧室主体和防振环7均同轴设置。
根据本申请的其中一个实施例，防振环7沿中心体1的轴向方向延伸。值得说明的是，防振环7还可沿其它方向进行延伸，只要防振环7内形成有沿着背向主燃级的方向呈渐扩状的火焰通道71即可。
根据本申请的其中一个实施例，火焰通道71内形成有扰流部。
扰流部可改变火焰锋面在火焰通道71中的流动轨迹，进一步提高防振环7抑制燃烧振荡的效果。
扰流部包括台阶711、环形扰流槽712和纵向扰流槽713中的一种或多种，当然，扰流部的结构形式不受此处举例的限制，只要可以改变火焰锋面在火焰通道71中的流动轨迹即可。
根据本申请的其中一个实施例，如图2所示，扰流部包括沿着中心体1的轴线方向分布的多个台阶711。基于康达效应，火焰锋面贴近台阶711，台阶711对火焰的正常流动起到干扰作用。
根据本申请的另外一个实施例，台阶711平行于中心体1的轴线方向的长度L 1＝L 0/n；台阶711垂直于中心体1的轴线方向的长度L 2＝L 0/n/tanɑ；其中，L0为火焰通道71沿中心体1的轴线方向形成的通道长度，n为台阶711的个数。
根据本申请的另外一个实施例，如图3所示，扰流部包括沿着中心体1的轴线方向分布的多个环形扰流槽712。基于康达效应，火焰绕环形扰流槽712做圆周流动。
根据本申请的另外一个实施例，环形扰流槽712的宽度f和高度e的范围均为2-10mm。
根据本申请的另外一个实施例，如图4所示，扰流部包括沿着中心体1的轴线方向贯穿火焰通道71的多个纵向扰流槽713，且纵向扰流槽713沿着火焰通道71的周向分布。基于康达效应，火焰在火焰通道71的入口 端被各纵向扰流槽713分流。
根据本申请的另外一个实施例，纵向扰流槽713的深度范围为2-10mm，纵向扰流槽713的宽度S＝2π/2m，其中，m为纵向扰流槽713的个数。
根据本申请的其中一个实施例，火焰通道71的入口端的横截面以及火焰通道71的出口端的横截面均呈圆形，或者，火焰通道71的入口端的横截面以及火焰通道71的出口端的横截面均呈椭圆形。横截面呈圆形或椭圆形，以满足康达效应。当然，本申请不受上述举例限制，例如，火焰通道71的形状还可以是：入口端横截面为圆形，出口端横截面的形状为椭圆形。
根据本申请的另外一个实施例，当火焰通道71的入口端的横截面呈圆形时，入口端的横截面的直径是主燃级出口端直径D的1-3倍，火焰通道71的通道侧壁所在平面与外环出口端面51所在平面的夹角α范围为0-90°。火焰通道71的最大通道长度是主燃级出口端直径D的3倍。
当火焰通道71的入口端的横截面呈椭圆形时，入口端的横截面上的长轴尺寸是主燃级出口端直径D的1-3倍，入口端的横截面上的短轴尺寸是主燃级出口端直径D的1-3倍。
根据本申请的其中一个实施例，如图5所示，当防振环7固定于主燃级外环5的出口端和端壁6的内表面时，主要变化为夹角α和通道长度L 0，不同的通道长度L 0给火焰所提供的附着区域不同，从而改变火焰形态和抑制燃烧室振荡；同时夹角α的变化，由于康达效应，会使流体随着火焰通道71的通道壁面流动，进而改变流动的物理扩张角，进而改变火焰的的张角以及主燃级火焰9的相对位置，从而达到改变火焰形态和燃烧室振荡的能力。
根据本申请的其中一个实施例，如图6所示，防振环7固定于端壁6的内表面，主要变量为火焰通道71的进口处侧壁与外环出口端面11的内侧壁间的差值L，不同的差值会导致火焰形态的变化如图6所示，当差值L达到一定状态时，主燃级火焰9会出现双根部状态，对于火焰的稳定能够起到有益作用，进而达到抑制振荡的效果。预燃级火焰10一般会同时稳定于级间段3的两个边缘点，并起到提供高温回流区保持整个火焰维持燃烧的作用。
根据本申请的其中一个实施例，级间段3包括级间段出口端面，主燃级旋流器4包括主燃级旋流器出口端面，主燃级外环5包括外环出口端面11，燃烧室端壁6包括端壁内表面；级间段出口端面与外环出口端面11错位设置。
级间段出口端面与外环出口端面11错位设置，可改变旋流流动的内外剪切层的起始位置，进而影响燃烧室主体的内腔中的火焰位置，实现对燃烧振荡的调控。
根据本申请的其中一个实施例，外环出口端面11和端壁内表面共面，以方便在燃烧室内安装防振环7等其他设备。
根据本申请的其中一个实施例，主燃级旋流器出口端面与级间段出口端面沿中心体1的轴线方向的间隔距离为第一间距；主燃级旋流器出口端面与外环出口端面11沿中心体1的轴线方向的间隔距离为第二间距，第一间距大于第二间距，第一间距的数值为S，级间段出口端面与外环出口端面11沿中心体1的轴线方向的间隔距离为H，其中，S和H均为设定好的数值，且均可以在对应区间中取值，H/S≤1。相较于现有技术，如此设计的主燃级外环5的长度更短，从而使燃烧室在实现抑制燃烧振荡的同时，还具有更轻的重量。
根据本申请的另外一个实施例，第一间距大于第二间距，第二间距的数值为S，H/S≤1。
根据本申请的另外一个实施例，第一间距小于第二间距，第一间距的数值为S，H/S≤1。
根据本申请的另外一个实施例，第一间距小于第二间距，第二间距的数值为S，H/S≤1。
本申请另一实施例提供了一种燃烧器，包括本申请任一技术方案所提供的燃烧室。
根据本申请的其中一个实施例，燃烧器包括但不限于传统的旋流杯结构燃烧器、多旋流燃烧器和中心分级燃烧器。
以上实施方式仅用于说明本申请，而非对本申请的限制。尽管参照实施例对本申请进行了详细说明，本领域的普通技术人员应当理解，对本申请的技术方案进行各种组合、修改或者等同替换，都不脱离本申请技术方 案的精神和范围，均应涵盖在本申请的权利要求范围之内。

Claims (10)

  1. 一种用于抑制燃烧振荡的燃烧室，其特征在于，包括：
    预燃级，所述预燃级包括中心体(1)以及设置在所述中心体(1)外围的预燃级旋流器(2)和级间段(3)；
    主燃级，所述主燃级设置在所述预燃级的外围，所述主燃级包括主燃级旋流器(4)和主燃级外环(5)；
    燃烧室主体，包括端壁(6)和侧壁(8)，所述端壁(6)连接所述主燃级外环(5)和所述侧壁(8)；
    防振环(7)，所述防振环(7)固定于所述端壁(6)的端壁内表面和/或所述主燃级外环(5)的外环出口端面(11)，且所述防振环(7)形成有沿着背向所述主燃级的方向呈渐扩状的火焰通道(71)，所述火焰通道(71)的入口端与所述主燃级的出口端对接，所述火焰通道(71)的出口端连通所述燃烧室主体的内腔。
  2. 根据权利要求1所述的用于抑制燃烧振荡的燃烧室，其特征在于，所述预然级、主燃级、燃烧室主体和所述防振环(7)均同轴设置。
  3. 根据权利要求1所述的用于抑制燃烧振荡的燃烧室，其特征在于，所述防振环(7)的内壁形成有扰流部。
  4. 根据权利要求3所述的用于抑制燃烧振荡的燃烧室，其特征在于，所述扰流部包括沿着所述中心体(1)轴线方向分布的多个台阶(711)，或者，
    所述扰流部包括沿着所述中心体(1)轴线方向分布的多个环形扰流槽(712)，或者，
    所述扰流部包括沿着所述中心体(1)轴线方向贯穿所述内壁的纵向扰流槽(713)，所述纵向扰流的数量为多个且沿着所述内壁的周向分布。
  5. 根据权利要求2至4中任一项所述的用于抑制燃烧振荡的燃烧室，其特征在于，所述入口端的横截面以及所述出口端的横截面均呈圆形，或者，所述入口端的横截面以及所述出口端的横截面均呈椭圆形。
  6. 根据权利要求5所述的用于抑制燃烧振荡的燃烧室，其特征在于，所述级间段(3)包括级间段出口端面，所述主燃级旋流器(4)包括主燃级旋流器出口端面，所述级间段出口端面与所述外环出口端面(11)错位 设置。
  7. 根据权利要求6所述的用于抑制燃烧振荡的燃烧室，其特征在于，所述外环出口端面和所述端壁内表面共面。
  8. 根据权利要求7所述的用于抑制燃烧振荡的燃烧室，其特征在于，所述主燃级旋流器出口端面与所述级间段出口端面沿所述中心体(1)的轴线方向的间隔距离为第一间距；所述主燃级旋流器出口端面与所述外环出口端面(11)沿所述中心体(1)的轴线方向的间隔距离为第二间距，所述第一间距大于所述第二间距。
  9. 根据权利要求7所述的用于抑制燃烧振荡的燃烧室，其特征在于，所述主燃级旋流器出口端面与所述级间段出口端面沿所述中心体(1)的轴线方向的间隔距离为第一间距；所述主燃级旋流器出口端面与所述外环出口端面(11)沿所述中心体(1)的轴线方向的间隔距离为第二间距，所述第一间距小于所述第二间距。
  10. 一种燃烧器，其特征在于，所述燃烧器包括权利要求1-9任一项所述的用于抑制燃烧振荡的燃烧室，所述燃烧器为旋流杯结构燃烧器、多旋流燃烧器或中心分级燃烧器。
PCT/CN2021/080781 2021-03-15 2021-03-15 用于抑制燃烧振荡的燃烧室和燃烧器 WO2022193067A1 (zh)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/CN2021/080781 WO2022193067A1 (zh) 2021-03-15 2021-03-15 用于抑制燃烧振荡的燃烧室和燃烧器

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2021/080781 WO2022193067A1 (zh) 2021-03-15 2021-03-15 用于抑制燃烧振荡的燃烧室和燃烧器

Publications (1)

Publication Number Publication Date
WO2022193067A1 true WO2022193067A1 (zh) 2022-09-22

Family

ID=83321749

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2021/080781 WO2022193067A1 (zh) 2021-03-15 2021-03-15 用于抑制燃烧振荡的燃烧室和燃烧器

Country Status (1)

Country Link
WO (1) WO2022193067A1 (zh)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116182198A (zh) * 2023-01-29 2023-05-30 中国航发沈阳发动机研究所 一种对冲式多模态燃烧室

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1426689A1 (en) * 2002-11-19 2004-06-09 Siemens Westinghouse Power Corporation Gas turbine combustor having staged burners with dissimilar mixing passage geometries
CN103123122A (zh) * 2012-12-31 2013-05-29 南京航空航天大学 一种主级燃油直接喷射的贫油预混预蒸发低污染燃烧室
CN108561898A (zh) * 2017-12-27 2018-09-21 中国航发四川燃气涡轮研究院 一种同轴分区高温升燃烧室头部
CN109737386A (zh) * 2018-12-11 2019-05-10 北京航空航天大学 双旋流低排放燃烧室
CN110107917A (zh) * 2019-04-23 2019-08-09 中国航空发动机研究院 径向燃油分级的槽道气帘淬熄燃烧室

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1426689A1 (en) * 2002-11-19 2004-06-09 Siemens Westinghouse Power Corporation Gas turbine combustor having staged burners with dissimilar mixing passage geometries
CN103123122A (zh) * 2012-12-31 2013-05-29 南京航空航天大学 一种主级燃油直接喷射的贫油预混预蒸发低污染燃烧室
CN108561898A (zh) * 2017-12-27 2018-09-21 中国航发四川燃气涡轮研究院 一种同轴分区高温升燃烧室头部
CN109737386A (zh) * 2018-12-11 2019-05-10 北京航空航天大学 双旋流低排放燃烧室
CN110107917A (zh) * 2019-04-23 2019-08-09 中国航空发动机研究院 径向燃油分级的槽道气帘淬熄燃烧室

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116182198A (zh) * 2023-01-29 2023-05-30 中国航发沈阳发动机研究所 一种对冲式多模态燃烧室

Similar Documents

Publication Publication Date Title
JP4559616B2 (ja) 燃焼室
EP1288577B1 (en) Gasturbine and the combustor thereof
JP6059902B2 (ja) ガスタービンエンジンに用いられる音響減衰装置
US6732527B2 (en) Combustion chamber
JP5882285B2 (ja) 燃焼室の脈動を低減するためのダンパ配列
US9664391B2 (en) Gas turbine combustor
US5471840A (en) Bluffbody flameholders for low emission gas turbine combustors
US20130192245A1 (en) Gas Turbine Combustor and Operating Method Thereof
JP5052783B2 (ja) ガスタービンエンジンおよび燃料供給装置
US9869473B2 (en) Conical-flat heat shield for gas turbine engine combustor dome
WO2022193067A1 (zh) 用于抑制燃烧振荡的燃烧室和燃烧器
CN112066412B (zh) 燃烧室、燃气轮机以及抑制振荡燃烧的方法
CN110925799B (zh) 用于抑制燃烧不稳定的燃烧室结构
CN215982677U (zh) 燃烧室和燃烧器
CN215175235U (zh) 用于抑制燃烧振荡的燃烧室和燃烧器
US11215361B2 (en) Cooling structure with ribs for gas turbine engine
CN217109651U (zh) 一种用于抑制燃烧振荡的燃烧室和燃烧器
CN115076724A (zh) 用于抑制燃烧振荡的燃烧室和燃烧器
CN115076725A (zh) 燃烧室和燃烧器
CN116263249A (zh) 一种用于抑制燃烧振荡的燃烧室和燃烧器
CN115704563B (zh) 燃烧室和燃烧器
US6773257B2 (en) Burner for the production of a hot gas
CN118442612A (zh) 一种蜂窝型增强掺混喷嘴结构
CN116498997A (zh) 一种空气自吹扫防回火中心喷嘴结构
JPH04260720A (ja) ガスタービン燃焼器とその保炎構造

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 21930664

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 21930664

Country of ref document: EP

Kind code of ref document: A1