WO2019228376A1 - 重油发动机的缸头及航空发动机 - Google Patents

重油发动机的缸头及航空发动机 Download PDF

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Publication number
WO2019228376A1
WO2019228376A1 PCT/CN2019/088893 CN2019088893W WO2019228376A1 WO 2019228376 A1 WO2019228376 A1 WO 2019228376A1 CN 2019088893 W CN2019088893 W CN 2019088893W WO 2019228376 A1 WO2019228376 A1 WO 2019228376A1
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Prior art keywords
combustion chamber
spark plug
cylinder head
heavy oil
engine
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PCT/CN2019/088893
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English (en)
French (fr)
Inventor
石晓东
唐程
刘小林
翟明明
闪颂武
罗晏
林成
Original Assignee
隆鑫通用动力股份有限公司
重庆隆鑫发动机有限公司
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Publication of WO2019228376A1 publication Critical patent/WO2019228376A1/zh

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02F—CYLINDERS, PISTONS OR CASINGS, FOR COMBUSTION ENGINES; ARRANGEMENTS OF SEALINGS IN COMBUSTION ENGINES
    • F02F1/00—Cylinders; Cylinder heads 
    • F02F1/24—Cylinder heads
    • F02F1/242—Arrangement of spark plugs or injectors
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Definitions

  • the present invention relates to engines and applications, and in particular, to a cylinder head of a heavy oil engine and an aero engine.
  • Heavy oil as the fuel of the engine will become the power trend of small and medium-sized drones; however, heavy oil has a high viscosity and poor low-temperature fluidity, resulting in a poorer atomization effect than ordinary light oil, affecting the combustion effect, and even causing the engine Difficult startup and substandard emissions.
  • the heavy oil engine in order to ensure that the heavy oil engine can have good atomization and start, it has a fuel supply method such as carburetor + auxiliary warm-up technology, mechanical injection (direct fuel injection), electronically controlled fuel injection; Among them, the electronically controlled fuel injection uses auxiliary air, and high-pressure air is used to impact the fuel particles to achieve sufficient atomization of the fuel.
  • the effect is better than the first two methods.
  • the timing of the air addition, the overall structure, and the degree of air participation have not been optimized.
  • the structure is still the original EFI method, and the reliable atomization of heavy oil and the efficient combustion of mixed fuels cannot be organized.
  • the engine's power, economy, and emissions can not achieve the desired effect, so that the application of heavy oil cannot be widely spread.
  • an object of the present invention is to provide a cylinder head of a heavy oil engine and a heavy oil engine.
  • the combustion chamber structure can enable the heavy oil to be sufficiently mixed, and can organize efficient fuel combustion to ensure that the heavy oil is applied to the engine.
  • the power, economy, and emissions of the engine achieve energy saving, environmental protection, and low cost after the heavy oil is applied to the engine.
  • a cylinder head of a heavy oil engine is processed with a pre-combustion chamber, and the pre-combustion chamber has Connected to the injection port of the combustion chamber, and the ignition electrode of the spark plug is located in the pre-combustion chamber.
  • the ignition point of the spark plug is located in the pre-combustion chamber.
  • the mixed fuel combined with auxiliary low-pressure air atomization and direct injection in the cylinder structure, ensures that more direct atomization is formed after the direct injection enters the combustion chamber in the later stage, thereby achieving the full combustion and utilization of heavy oil; not only ensuring the further development of fuel mist droplets Atomization can also ensure uniform mixing between the auxiliary air and the droplets, and eventually can uniformly burn.
  • the pre-combustion chamber is a Laval nozzle structure, and the Laval nozzle structure is directly formed on the cylinder head and the injection port communicates with the combustion chamber; the working process of the pre-combustion chamber is that the fuel is injected into the combustion chamber After entering the pre-combustion chamber at the same time, it was ignited by a spark plug (the ignition point is located at the inlet end of the Laval nozzle, which is relative to the Laval nozzle, not the port communicating with the combustion chamber).
  • the pre-combustion chamber is a Laval nozzle structure along the ignition direction of the spark plug, and further structurally adapts to the combustion and injection process, avoiding inconsistencies in the combustion direction and the injection direction to interfere or reduce the injection effect.
  • a double spark plug formed by a spark plug i and a spark plug n is installed on the cylinder head, and the double spark plug is used to provide ignition, which has the characteristics of high-energy ignition, combined with the aforementioned air-assisted atomization and premixing scheme, to ensure that the engine Reliable and safe ignition under various operating conditions and conditions, compared with the traditional heavy oil compression ignition engine, further reducing the engine volume and weight, suitable for use by drones; and the spark plug i is located at a middle position on the top of the combustion chamber or Nearby; because the spark plug i is located at or near the middle position, it is ensured that the spark plug n is also located at the center line, which is conducive to sufficient mixing of the heavy oil and sufficient combustion after ignition.
  • the pre-combustion chamber is disposed at a spark plug I and the ignition electrode of the spark plug I extends into the pre-combustion chamber; the main spark plug is located in or near the middle of the combustion chamber, and the combustion gas emitted by the pre-combustion chamber is more conducive to the entire combustion
  • the mixture in the chamber is turbulent and fully burned.
  • the ignition angle of the spark plug n is 40 ° -50 °; this structure makes the incoming combustion mixture correspond to the ignition orientation of the spark plug, and forms a rich gas mixing zone near the spark plug, which is beneficial to further combustion with the combustion air Blend to organize efficient fuel combustion.
  • the center lines of the spark plug i and the spark plug n are substantially coplanar, and the coplanar surface is substantially perpendicular to the plane where the intake and exhaust valves are located.
  • the coplanar arrangement refers to the spark plug n and the spark plug i.
  • the central axis is located on the same plane.
  • the plane where the intake and exhaust valves are located means that the axes of the intake and exhaust valves are located on the same plane.
  • Basic coplanar and substantially vertical means that certain errors are allowed, such as minor tilt and misalignment. It does not affect the coplanarity and vertical understanding of this solution; this structure ensures the simple arrangement of the various components on the cylinder head, and at the same time facilitates the sufficient mixing of the intake air and the gas, facilitates the formation of tumble flow and further atomization, and ensures uniform and efficient combustion .
  • the invention also discloses an aero engine, which is equipped with a cylinder head of the heavy oil engine.
  • a pre-combustion chamber is provided at the ignition point of the spark plug, and the pre-combustion chamber has an injection port connected to the combustion chamber, and the fuel in the pre-combustion chamber is ignited by the injection port.
  • the ejection which further impacts the mixed fuel entering the combustion chamber, has the effect of fully mixing the gas, which is beneficial to the formation of a uniform combustion mixture.
  • the pre-combustion chamber can accelerate the flame propagation, improve combustion efficiency, increase engine power and reduce knocking. Risks, can also organize efficient fuel combustion, ensure the power, economy and emissions of heavy oil applied to the engine, and achieve energy saving, environmental protection and low cost after heavy oil is applied to the engine.
  • FIG. 1 is a cross-sectional view of the present invention (mounted on an engine).
  • the cylinder head of the heavy oil engine of this embodiment is processed with a pre-combustion chamber 17, the pre-combustion chamber 17 has an injection port communicating with the combustion chamber, and a spark plug ignition electrode It is located in the pre-combustion chamber.
  • the pre-combustion chamber structure can be used to further homogenize the mixed fuel by using the combustion air flow in the pre-combustion chamber.
  • a fuel injection assembly is also installed on the combustion chamber, which is formed by the fuel nozzle 6, the pre-mixing chamber 7, and the oil-gas mixing nozzle 8 in a sealed connection in order, and the fuel nozzle 6 and the oil-gas mixing nozzle 8 are installed through a mounting seat. Sealed The connection is fixed, and the premixing chamber is directly formed in the mounting seat, and the structure is simple and compact.
  • the pre-combustion chamber 17 is a Laval nozzle structure, and the Laval nozzle structure is formed directly on the cylinder head and the injection port communicates with the combustion chamber;
  • the working process of the pre-combustion chamber is that the fuel is After being injected into the combustion chamber, it also entered the pre-combustion chamber at the same time, and was spark plug (the ignition point is located at the inlet end of the Laval nozzle, which is relative to the Laval nozzle, not the port communicating with the combustion chamber) After ignition, it expands and passes through the Laval nozzle quickly through the throat and is ejected from the nozzle of the Laval nozzle (higher speed than the combustion explosion)
  • the pre-combustion chamber can accelerate the flame propagation, improve combustion efficiency, increase engine power and reduce the risk of knocking. It can also organize efficient fuel combustion to ensure the power, economy, and emissions of heavy oil applied to the engine, and achieve energy conservation, environmental protection and low cost after heavy oil is applied to the engine.
  • the pre-combustion chamber 17 is a Laval nozzle structure along the ignition direction of the spark plug, which is further adapted to the combustion and injection process in structure, to avoid interference between the combustion direction and the injection direction, or to reduce the injection effect. .
  • a double spark plug formed by a spark plug 13 and a spark plug 114 is installed on the cylinder head 2.
  • the installation structure of the spark plug is to extend into the combustion chamber (pre-combustion chamber) for ignition.
  • the installation structure is not repeated here, and the double spark plug is used to provide ignition.
  • the ignition angle of the spark plug n4 is 40 ° -50 °; this structure allows the mixed gas entering by direct injection in the cylinder to flow through the top of the piston and the wall of the cylinder block, and then the spark plug Corresponding to the ignition orientation, a rich gas mixing zone is formed near the spark plug, which is beneficial for further mixing with the combustion air, thereby forming an efficient tissue combustion.
  • the present invention is suitable for a direct injection structure in a cylinder.
  • the fuel injection assembly formed by the nozzle 6, the premixing chamber 7, and the oil-gas mixing nozzle 8 is hermetically connected, and has a set injection angle.
  • the spark plug 13 is located at or near the middle position on the top of the combustion chamber. Since the spark plug 13 is located at or near the middle position, this structure ensures that the structural arrangement of the spark plug 114 and the oil-gas mixing nozzle 8 is also located at the center line. And it is good for full mixing and combustion after ignition. [0026]
  • the center line of the spark plug 13 and the spark plug 114 (this embodiment also includes that the center line of the oil-gas mixing nozzle 8 is also provided on the same surface) are substantially coplanar, and the coplanar surface and The plane on which the exhaust valve is located is basically vertical in space.
  • the coplanar arrangement means that the central axes of the oil and gas mixing nozzle 8, the spark plug 114 and the spark plug 13 are on the same plane.
  • the plane on which the intake and exhaust valves are located refers to the intake and exhaust valves.
  • the axes are located on the same plane.
  • Basic coplanarity and verticality mean that certain errors are allowed, such as minor tilts and misalignments, and do not affect the understanding of the coplanarity of this solution.
  • This structure ensures a simple arrangement of the various components on the cylinder head. At the same time, it is conducive to the sufficient mixing of the intake air and the gas, which is conducive to the formation of tumble flow and further atomization, ensuring uniform and efficient combustion.
  • the pre-combustion chamber is disposed at the spark plug 13 and the ignition electrode of the spark plug 13 extends into the pre-combustion chamber; the main spark plug is located in the middle or near the combustion chamber, and the combustion gas ejected from the pre-combustion chamber is more conducive to The mixture in the entire combustion chamber is turbulent and fully burned.
  • the present invention also discloses an aero engine.
  • the engine includes a cylinder head 2, a cylinder block 1, and a piston assembly 5.
  • the aero engine is equipped with a cylinder head of the heavy oil engine, and the engine. Suitable for drones.

Abstract

一种重油发动机的缸头（2），燃烧室由缸头上加工的燃烧室面形成，缸头上还加工有预燃烧室（17），预燃烧室位于火花塞点火处且具有连通于燃烧室的喷射口。还涉及一种航空发动机。该装置预燃烧室内的燃料被点燃后由喷射口喷出，对进入燃烧室的混合燃料进一步冲击具有使气体充分混合的作用，利于形成均匀的燃烧混合气，同时，预燃烧室可加速火焰的传播，提高燃烧效率，提升发动机功率并降低爆震风险，实现重油应用于发动机后的节能、环保以及低成本。

Description

重油发动机的缸头及航空发动机 技术领域
[0001] 本发明涉及发动机及应用， 特别涉及一种重油发动机的缸头及航空发动机。
背景技术
[0002] 重油作为发动机的燃料， 将成为中小型无人机的动力趋势； 但重油黏度高， 低 温流动性差， 导致雾化效果要比普通的轻质油差， 影响了燃烧效果， 甚至导致 发动机启动困难以及排放不达标。
[0003] 5见有技术中， 为了保证重油发动机能够具有良好的雾化以及启动， 具有采用化 油器 +辅助预热技术、 机械喷射 （燃油直喷） 、 电控燃油喷射等供油方式； 其中 电控燃油喷射采用辅助空气， 利用高压空气对燃油颗粒进行冲击， 实现燃油的 充分雾化， 效果优于前两种方式。 但是， 没能优化空气加入的时机、 总体结构 和空气参与程度， 结构上依然是原始的电喷方式， 则无法实现重油的可靠雾化 以及无法组织混合燃料高效的燃烧， 也就使得重油应用于发动机的动力性、 经 济性和排放性无法达到期待的效果， 从而使重油的应用无法大范围普及。
发明概述
技术问题
[0004] 因此， 需要对现有的重油发动机进行改进， 能够使得重油实现较为充分的混合 ， 并能够组织燃料高效的燃烧， 保证重油在应用于发动机的动力性、 经济性和 排放性， 实现重油应用于发动机后的节能、 环保以及低成本。
问题的解决方案
技术解决方案
[0005] 有鉴于此， 本发明的目的是提供一种重油发动机的缸头以及重油发动机， 燃烧 室构造能够使得重油实现较为充分的混合， 并能够组织燃料高效的燃烧， 保证 重油在应用于发动机的动力性、 经济性和排放性， 实现重油应用于发动机后的 节能、 环保以及低成本。
[0006] 本发明的重油发动机的缸头， 所述缸头上加工有预燃烧室， 所述预燃烧室具有 连通于燃烧室的喷射口， 且火花塞点火电极位于预燃烧室内， 当然， 火花塞的 点火点位于预燃烧室内； 采用预燃烧室结构， 可利用预燃烧室内的燃烧气流进 一步混合、 雾化以及匀化混合燃料， 配合以辅助低压空气雾化以及缸内直喷结 构， 保证后期直喷进入燃烧室后形成较为更充分的雾化， 从而实现重油的充分 燃烧和利用； 不但保证了燃油雾滴的进一步雾化， 还能保证辅助空气与雾滴之 间的均匀混合， 最终能够均匀燃烧。
[0007] 进一步， 所述预燃烧室为拉瓦尔喷管结构， 所述拉瓦尔喷管结构直接形成于缸 头且喷射口连通燃烧室； 预燃烧室工作过程是， 在燃料被喷入燃烧室后， 同时 进入预燃烧室， 被火花塞 （点火点位于拉瓦尔喷管的进气端， 该进气端是相对 于拉瓦尔喷管而言， 而不是与燃烧室连通的口） 点火后， 膨胀并通过拉瓦尔喷 管急速通过喉部由拉瓦尔喷管的喷射口喷出 （比燃烧爆炸更高的速度） ， 利于 燃烧室内其他混合气的进一步充分混合以及燃烧， 从而更利于且更适应于重油 的燃烧。
[0008] 进一步， 所述预燃烧室为沿着火花塞点火方向的拉瓦尔喷管结构， 结构上进一 步适应燃烧及喷射过程， 避免燃烧方向和喷射方向的不一致而干涉或者降低喷 射效果。
[0009] 进一步， 所述缸头上安装由火花塞 i和火花塞 n形成的双火花塞， 采用双火花塞 提供点火， 具有高能点火的特性， 结合前述的空气辅助雾化以及预混方案， 保 证发动机在各种工况和条件下可靠安全的点火， 相对于传统的重油压燃式发动 机， 进一步减小发动机体积和重量， 适合于无人机使用； 且所述火花塞 i位于燃 烧室顶部的中间位置或附近； 由于火花塞 i位于中间位置或附近， 保证了火花塞 n也位于中线， 点火后利于重油的充分混合以及充分的燃烧。
[0010] 进一步， 所述预燃烧室设置于火花塞 I处且所述火花塞 I点火电极伸入预燃烧室 ; 主火花塞处于燃烧室中部或附近， 预燃烧室喷出的燃烧气体更利于对整个燃 烧室的混合气形成扰动以及充分燃烧。
[0011] 进一步， 所述火花塞 n的点火夹角为 40°-50° ; 该结构使得进入的燃烧混合气与 火花塞的点火方位相对应， 在火花塞附近形成浓燃气混合区， 利于与燃烧空气 进一步混合， 从而组织燃料高效的燃烧。 [0012] 进一步， 所述火花塞 i和火花塞 n的中心线基本共面， 且该共面与进、 排气门所 在的平面在空间上基本垂直， 共面布置指的是火花塞 n和火花塞 i的中心轴线位 于同一面上， 进、 排气门所在的平面指的是进排气门的轴线位于同一平面， 基 本共面和基本垂直是指允许具有一定的误差， 比如较小的倾斜和错位， 并不影 响对本方案共面以及垂直的理解； 该结构保证了缸头上各个部件的简单布置， 同时利于进气与燃气的充分混合， 利于形成滚流而进一步雾化， 保证了均匀高 效的燃烧。
[0013] 本发明还公开了一种航空发动机， 所述航空发动机安装有所述的重油发动机的 缸头。
[0014] 本发明的重油发动机的缸头及航空发动机， 在火花塞的点火处设置预燃烧室 ， 且预燃烧室具有连通于燃烧室的喷射口， 预燃烧室内的燃了被点燃后由喷射 口喷出， 对进入燃烧室的混合燃料进一步冲击具有使气体充分混合的作用， 利 于形成均匀的燃烧混合气， 同时， 预燃烧室可加速火焰的传播， 提高燃烧效率 ， 提升发动机功率并降低爆震风险， 还能够组织燃料高效的燃烧， 保证重油在 应用于发动机的动力性、 经济性和排放性， 实现重油应用于发动机后的节能、 环保以及低成本。
[0015]
[0016] 下面结合附图和实施例对本发明作进一步描述。
[0017] 图 1为本发明的剖视图 （安装于发动机） 。
[0018]
[0019] 如图所示： 本实施例的重油发动机的缸头， 所述缸头 2上加工有预燃烧室 17， 所述预燃烧室 17具有连通于燃烧室的喷射口， 且火花塞点火电极位于预燃烧室 内； 采用预燃烧室结构， 可利用预燃烧室内的燃烧气流进一步匀化混合燃料， 配合以辅助低压空气雾化以及缸内直喷结构， 保证后期直喷进入燃烧室后形成 较为更充分的雾化的前提下实现重油的充分燃烧和利用； 不但保证了辅助空气 与雾滴之间在冲击力的条件下的均匀混合， 最终能够均匀而充分的燃烧。
[0020] 如图所示， 燃烧室上还安装有燃油喷射组件， 依次由燃油喷嘴 6、 预混室 7和油 气混合喷嘴 8密封连接形成， 燃油喷嘴 6与油气混合喷嘴 8之间通过安装座密封连 接形成固定， 而预混室直接形成于安装座内， 结构简单紧凑。
[0021] 本实施例中， 所述预燃烧室 17为拉瓦尔喷管结构， 所述拉瓦尔喷管结构直接形 成于缸头且喷射口连通燃烧室； 预燃烧室工作过程是， 在燃料被喷入燃烧室后 ， 同时进入预燃烧室， 被火花塞 （点火点位于拉瓦尔喷管的进气端， 该进气端 是相对于拉瓦尔喷管而言， 而不是与燃烧室连通的口） 点火后， 膨胀并通过拉 瓦尔喷管急速通过喉部由拉瓦尔喷管的喷射口喷出 （比燃烧爆炸更高的速度）
， 对进入燃烧室的混合燃料进一步冲击具有使气体充分混合的作用， 利于形成 均匀的燃烧混合气， 同时， 预燃烧室可加速火焰的传播， 提高燃烧效率， 提升 发动机功率并降低爆震风险， 还能够组织燃料高效的燃烧， 保证重油在应用于 发动机的动力性、 经济性和排放性， 实现重油应用于发动机后的节能、 环保以 及低成本。
[0022] 本实施例中， 所述预燃烧室 17为沿着火花塞点火方向的拉瓦尔喷管结构， 结构 上进一步适应燃烧及喷射过程， 避免燃烧方向和喷射方向的不一致而干涉或者 降低喷射效果。
[0023] 缸头 2上安装由火花塞 13和火花塞 114形成的双火花塞， 火花塞的安装结构为伸 入燃烧室 （预燃烧室） 进行点火， 安装结构在此不再赘述， 采用双火花塞提供 点火， 具有高能点火的特性， 结合前述的空气辅助雾化以及预混方案， 保证发 动机在各种工况和条件下可靠安全的点火， 相对于传统的重油压燃式发动机， 进一步减小发动机体积和重量， 适合于无人机使用。
[0024] 本实施例中， 所述火花塞 n4的点火夹角为 40°-50° ; 该结构使得采用缸内直喷 的方式进入的混合气经活塞顶部与缸体壁面导流后， 与火花塞的点火方位相对 应， 在火花塞附近形成浓燃气混合区， 且利于与燃烧空气进一步混合， 从而形 成高效的组织燃烧； 使用时， 本发明适用于缸内直喷结构， 缸头上设置依次由 燃油喷嘴 6、 预混室 7和油气混合喷嘴 8密封连接形成的燃油喷射组件， 且具有设 定的喷射角。
[0025] 本实施例中， 所述火花塞 13位于燃烧室顶部的中间位置或附近， 由于火花塞 13 位于中间位置或附近， 该结构保证了火花塞 114和油气混合喷嘴 8结构布置上也位 于中线， 喷射以及点火后利于充分混合以及充分的燃烧。 [0026] 本实施例中， 所述火花塞 13的中心线和火花塞 114 （本实施例还包括油气混合喷 嘴 8的中心线也同面设置） 的中心线基本共面， 且该共面与进、 排气门所在的平 面在空间上基本垂直， 共面布置指的是油气混合喷嘴 8、 火花塞 114和火花塞 13的 中心轴线位于同一面上， 进排气门所在的平面指的是进排气门的轴线位于同一 平面， 基本共面和基本垂直是指允许具有一定的误差， 比如较小的倾斜和错位 ， 并不影响对本方案共面的理解； 该结构保证了缸头上各个部件的简单布置， 同时利于进气与燃气的充分混合， 利于形成滚流而进一步雾化， 保证了均匀高 效的燃烧。
[0027] 本实施例中， 预燃烧室设置于火花塞 13处且所述火花塞 13的点火电极伸入预燃 烧室； 主火花塞处于燃烧室中部或附近， 预燃烧室喷出的燃烧气体更利于对整 个燃烧室的混合气形成扰动以及充分燃烧。
[0028] 本发明还公开了一种航空发动机， 如图所示， 发动机包括缸头 2、 缸体 1和活塞 组件 5 , 所述航空发动机安装有所述的重油发动机的缸头， 且该发动机适用于无 人机。
[0029] 最后说明的是， 以上实施例仅用以说明本发明的技术方案而非限制， 尽管参照 较佳实施例对本发明进行了详细说明， 本领域的普通技术人员应当理解， 可以 对本发明的技术方案进行修改或者等同替换， 而不脱离本发明技术方案的宗旨 和范围， 其均应涵盖在本发明的权利要求范围当中。
[0030]
发明的有益效果

Claims

权利要求书
[权利要求 1] 一种重油发动机的缸头， 其特征在于： 所述缸头上加工有预燃烧室， 所述预燃烧室具有连通于燃烧室的喷射口， 且火花塞点火电极位于预 燃烧室内。
[权利要求 2] 根据权利要求 i所述的重油发动机的缸头， 其特征在于： 所述预燃烧 室为拉瓦尔喷管结构， 所述拉瓦尔喷管结构直接形成于缸头且喷射口 连通燃烧室。
[权利要求 3] 根据权利要求 2所述的重油发动机的缸头， 其特征在于： 所述预燃烧 室为沿着火花塞点火方向的拉瓦尔喷管结构。
[权利要求 4] 根据权利要求 2所述的重油发动机的缸头， 其特征在于： 所述缸头上 安装由火花塞 i和火花塞 n形成的双火花塞， 且所述火花塞 i位于燃烧 室顶部的中间位置或附近。
[权利要求 5] 根据权利要求 4所述的重油发动机的缸头， 其特征在于： 所述预燃烧 室设置于火花塞 I处且所述火花塞 I点火电极伸入预燃烧室。
[权利要求 6] 根据权利要求 5所述的重油发动机的缸头， 其特征在于： 所述火花塞 n的点火夹角为 40°-50°。
[权利要求 7] 根据权利要求 6所述的重油发动机的缸头， 其特征在于： 所述火花塞 I 和火花塞 n的中心线基本共面， 且该共面与进、 排气门所在的平面在 空间上基本垂直。
[权利要求 8] 一种航空发动机， 其特征在于： 所述航空发动机安装有权利要求 1至 7 任一权利要求的重油发动机的缸头。
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