WO2019134645A1 - 模拟两级增压压端/涡端旁通对喷雾特性影响的装置和方法 - Google Patents

模拟两级增压压端/涡端旁通对喷雾特性影响的装置和方法 Download PDF

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WO2019134645A1
WO2019134645A1 PCT/CN2019/070087 CN2019070087W WO2019134645A1 WO 2019134645 A1 WO2019134645 A1 WO 2019134645A1 CN 2019070087 W CN2019070087 W CN 2019070087W WO 2019134645 A1 WO2019134645 A1 WO 2019134645A1
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pressure
bypass
compressor
pressure stage
air
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PCT/CN2019/070087
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English (en)
French (fr)
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韩志强
刘智
田维
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西华大学
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Publication of WO2019134645A1 publication Critical patent/WO2019134645A1/zh

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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/04—Testing internal-combustion engines
    • G01M15/05—Testing internal-combustion engines by combined monitoring of two or more different engine parameters

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  • the invention relates to the technical field of automobile engines, in particular to an apparatus and a method for simulating the influence of two-stage supercharging end/vortex end bypass on spray characteristics.
  • the vortex bypass is different from the pressure bypass.
  • the air pressure at the turbine outlet is not higher than the inlet air pressure. Therefore, when the vortex valve is opened, part of the airflow flows from the bypass to the outlet end of the turbine without passing through the turbine.
  • the efficiency of the turbine affects the operating state of the compressor.
  • the opening of the pressure end/vortex end bypass valve not only reduces the amount of intake air, but also affects the flow characteristics of the gas, thereby affecting the spray cone angle at the time of fuel injection and the particle size distribution and concentration field distribution after oil droplet breakage.
  • an object of the present invention is to provide an apparatus and method for simulating the influence of a two-stage supercharging pressure end/vortex end bypass on a spray characteristic, which can solve the spray characteristics of a pressure end/vortex end bypass in an actual internal combustion engine.
  • the invisible problem can simulate the effect of the end/vortex bypass on the spray characteristics when the piston approaches the top dead center.
  • the spray/vortex bypass is used to improve spray atomization and mixing to achieve high efficiency. Clean combustion provides theoretical data support.
  • a device for simulating the influence of a two-stage supercharging pressure end/vortex end bypass on a spray characteristic including a pressure end bypass simulation system, a variable volume combustion bomb device, and a spray photographing system;
  • the pressure end bypass simulation system includes an air compressor, a low pressure stage turbine, a high pressure stage turbine, an air filter, a low pressure stage compressor, and a high pressure stage compressor;
  • the air outlet of the air compressor is connected to the air inlet of the low-pressure stage turbine, the air outlet of the low-pressure stage turbine is connected to the air inlet of the high-pressure stage turbine, and the vortex end temperature sensor I and the vortex end pressure are arranged near the low-pressure stage turbine outlet
  • the sensor I has a vortex bypass bypass between the inlet and the outlet of the high-pressure stage turbine, and a solenoid valve I is provided on the bypass branch of the vortex, and the side of the solenoid valve I connected to the outlet of the high-pressure stage turbine a vortex end temperature sensor II and a vortex end pressure sensor II are provided; the air outlet of the high pressure stage turbine is also connected to the air pipe leading to the atmosphere;
  • the air outlet of the air filter is connected to the air inlet of the low pressure stage compressor, the air outlet of the low pressure stage compressor is connected to the air inlet of the high pressure stage compressor, and the temperature sensor I is arranged near the air outlet of the low pressure stage compressor.
  • Pressure sensor I; a temperature sensor II and a pressure sensor II are arranged near the air outlet of the high-pressure compressor; a pressure bypass bypass branch is provided between the air inlet and the air outlet of the high-pressure compressor, and the pressure bypass bypass branch a solenoid valve II is provided, and a side of the electromagnetic valve II connected to the air outlet of the high pressure stage compressor is provided with a pressure sensor III and a temperature sensor III;
  • the low-pressure stage turbine and the low-pressure stage compressor are connected to each other by a common rotating shaft, and the high-pressure stage turbine and the high-pressure stage compressor are connected to each other through a common rotating shaft;
  • the variable volume combustion bomb device comprises a cylindrical combustion chamber and a piston inside thereof; an upper end cap of the combustion bomb is arranged above the combustion chamber, an upper end of the combustion bomb is mounted with an injector, and is connected to the exhaust pipe through an exhaust pipe a through hole of the vacuum pump and a through hole connected to the air outlet of the high pressure stage compressor; a venting pipe and an intake pipe are arranged at the bottom of the combustion chamber; the intake pipe is connected to the gas storage cylinder, and the electromagnetic valve III and the decompression are further provided on the intake pipe a valve; a venting valve is arranged on the venting pipe; a combustion blast window ⁇ and an incendiary window II are arranged on the side wall of the combustion chamber; and the position sensor is arranged at the bottom of the piston;
  • the spray photographing system includes a beam splitter, a Xecl excimer laser, a high-speed camera ICCD for photographing a gas phase, and a high-speed camera ICCD for photographing a liquid phase; a spectroscope placed outside the combustion bullet window, a high-speed camera ICCD, and a high-speed camera.
  • the focus of the ICCD is combined on the beam splitter; the laser emitted by the Xecl excimer laser is reflected by the mirror ⁇ and the mirror II, and sequentially converted into a beam of light by the beam expander, collimator and compression mirror, and then passed through the incendiary window. II is irradiated into the combustion chamber;
  • combustion bullet window ⁇ is distributed at an angle of 90° to the combustion bomb window II on the combustion chamber wall.
  • the top of the piston is in the shape of an ⁇ combustion chamber; the inner wall of the combustion chamber is provided with a retaining ring for limiting the piston; and a sealing ring is arranged between the inner wall of the combustion chamber of the piston.
  • An experimental method for simulating a device that affects spray characteristics by a two-stage booster end/vortex bypass comprising the following steps:
  • Step 1 Fill the fuel tank with a fluorescent agent to simulate the diesel spray, and adjust the injector to extend into the combustion chamber to a suitable depth;
  • Step 2 Turn on the Xecl excimer laser, adjust the mirror ⁇ and mirror II, and make the laser emitted by the Xecl excimer laser to the beam expander, change the diameter of the laser through the beam expander, and converge the beam through the collimator. Finally, through the compression mirror, the beam is converted into a beam of light and vertically irradiated in the combustion chamber;
  • Step 3 Adjust the angles of the two high-speed cameras and the beam splitter to direct the beam in the incendiary to the front of the camera;
  • Step 4 Open the air compressor and adjust the control valve in the air compressor to make the boost pressure reach the preset value
  • Step 5 Control the solenoid valve II or the solenoid valve to open, and then control the solenoid valve III to open;
  • Step 6 When the piston is ascended to a predetermined position, the injector is controlled to open to generate a spray, and the fluorescent agent is illuminated by the induction of the laser;
  • Step 7 Control two high-speed cameras to shoot, and collect data of the temperature sensor and pressure sensor at the same time;
  • Step 8 Close all solenoid valves, open the bleed valve, return the piston, and open the vacuum pump to extract air and spray droplets from the combustion chamber.
  • step 4 if the boost pressure is lower than the preset boost pressure, the control valve in the air compressor opens the valve according to the signal from the electronic control and the collecting unit and increases its power to the target value. If the boost pressure is higher than the preset boost pressure, the control valve in the air compressor closes the valve according to the signal from the electronic control and the acquisition unit and reduces its power to bring it closer to the target value.
  • the present invention provides a device for simulating a spray characteristic of a two-stage supercharging end/vortex end bypass, which can provide a basis for further optimizing the fuel injection strategy;
  • the present invention utilizes a compressor instead of an exhaust gas to drive a turbine, which is advantageous for simplifying the device and making the simulation device closer to the real situation, making the solution easier to implement;
  • the present invention utilizes an installed temperature and pressure sensor to better analyze changes in the flow field of the airflow after the bypass valve is opened;
  • the present invention utilizes a variable volume incendiary bomb to more realistically simulate the flow field of the airflow compressing the top dead center within the engine;
  • the invention shapes the shape of the combustion chamber on the movable piston, which is beneficial to realistically simulate the influence of the combustion chamber on the spray.
  • FIG. 1 is a schematic view showing the structure of a device for simulating the spray characteristics of a two-stage supercharging end/vortex end bypass according to the present invention.
  • FIG. 2 is a flow chart of an experimental method for simulating the influence of a two-stage supercharging end/vortex end bypass on a spray characteristic according to the present invention.
  • a device simulating the influence of two-stage supercharging end/vortex bypass on the spray characteristics including a pressure end bypass simulation system, a variable volume incendiary device, and a spray photographing system.
  • the pressure end bypass simulation system includes an air compressor 1, a low pressure stage turbine 3, a high pressure stage turbine 12, an air cleaner 2, a low pressure stage compressor 4, and a high pressure stage compressor 13.
  • the air outlet of the air compressor 1 is connected to the air inlet of the low pressure stage turbine 3, the air outlet of the low pressure stage turbine 3 is connected to the air inlet of the high pressure stage turbine 12, and the vortex end temperature sensor is arranged near the air outlet of the low pressure stage turbine 3.
  • I7 and vortex end pressure sensor I8; a vortex bypass bypass branch is provided between the intake port and the air outlet of the high pressure stage turbine 12, and a solenoid valve I9, a solenoid valve I9 and a high pressure stage turbine 12 are provided on the vortex bypass bypass branch.
  • the side of the air outlet connection is provided with a vortex end temperature sensor II10 and a vortex end pressure sensor II11.
  • the air outlet of the air cleaner 2 is connected to the air inlet of the low pressure stage compressor 4, and the air outlet of the low pressure stage compressor 4 is connected to the air inlet of the high pressure stage compressor 13, near the air outlet of the low pressure stage compressor 4.
  • the pressure end bypass branch is provided with a solenoid valve II16, and the electromagnetic valve II16 is connected to the outlet of the high pressure stage compressor 13 with a pressure sensor III17 and a temperature sensor III18.
  • the air outlet of the high pressure stage compressor 13 is connected to the air inlet of the indeterminate combustion bomb through a pipeline.
  • the low-pressure stage turbine 3 and the low-pressure stage compressor 4 are connected to each other by a common rotating shaft, and the high-pressure stage turbine 12 and the high-pressure stage compressor 13 are connected to each other by a common rotating shaft.
  • the variable-volume incendiary device includes a cylindrical combustion chamber and a piston 27 therein; an upper end of the combustion chamber is provided above the combustion chamber, and the upper end cover 34 of the incendiary is mounted with an injector 19 and is arranged through the row.
  • the gas pipe 41 is connected to the through hole of the vacuum pump 42, and the through hole connected to the air outlet of the high pressure stage compressor 13; the upper end cover 34 of the combustion bomb is connected to the cylinder by bolts, and has three holes in the upper portion thereof.
  • a hole is provided for the injector 19, one for connection to the inside of the incendiary bomb and the other for connection to the exhaust pipe 41 for exhaust.
  • the bottom of the combustion chamber is provided with a venting pipe 25 and an intake pipe 30; the intake pipe 30 is connected to the gas storage cylinder 33, and the intake pipe 30 is further provided with a solenoid valve III31 and a pressure reducing valve 32; the venting pipe 25 is provided with a venting valve 24 .
  • a combustion blast window ⁇ and an incendiary window II are provided on the side wall of the combustion chamber; the position sensor 29 is at the bottom of the piston 27.
  • four windows are arranged on the side wall of the incendiary device of the present embodiment at intervals of 90 degrees for photographing.
  • the top of the piston 27 is in the shape of an ⁇ combustion chamber; the inner wall of the combustion chamber is provided with a retaining ring 26 for limiting the piston 27; and the inner wall of the combustion chamber of the piston 27 is provided with a sealing ring 28.
  • the spray photographing system includes a beam splitter 22, a Xecl excimer laser 40, and a high-speed camera ICCD ⁇ 21 for photographing a gas phase and a high-speed camera ICCD ⁇ 23 for photographing a liquid phase; the spectroscope 22 is placed outside the combustion bullet window, and the high-speed camera ICCD ⁇ 21
  • the focus of the high-speed camera ICCD ⁇ 23 is merged on the beam splitter 22; the laser light emitted by the Xecl excimer laser 40 is reflected by the mirror ⁇ 39 and the mirror II38, and sequentially converted into a bundle by the beam expander 37, the collimator mirror 36 and the compression mirror. Light is then irradiated into the combustion chamber through the incendiary window II;
  • the electric control and acquisition unit can control the opening degree of the control valve and the working power of the air compressor in the air compressor, and can simultaneously receive the gas pressure and flow signal fed back by the air compressor and the collected temperature and pressure sensor signals.
  • the preset boost pressure that needs to be simulated is input, and the electronic control and acquisition unit roughly calculates the flow rate and pressure of the air compressor to output the gas, and controls the air compressor to start working at a certain power.
  • the electronic control and acquisition unit sends a control signal to fine tune the air compressor according to the signal of the collected pressure sensor III and the gas pressure and flow signal fed back by the air compressor.
  • the control valve in the air compressor opens the valve according to the signal from the electronic control and the acquisition unit and increases its power to bring it closer to the target value.
  • the control valve in the air compressor closes the valve according to the signal from the electronic control and the acquisition unit and reduces its power to bring it closer to the target value.
  • the data collected by the temperature sensor ⁇ and the pressure sensor ⁇ are used to calculate the outlet flow of the low pressure stage compressor and to monitor the change in the gas pressure at the inlet end of the high pressure stage compressor.
  • the same temperature sensor II and pressure sensor II are used to calculate the flow rate of the gas passing through the bypass branch when the pressure bypass valve is opened, and the temperature sensor III and the pressure sensor III are used to calculate the flow rate of the high pressure stage compressor outlet, and monitor the high pressure. The change in gas pressure at the outlet end of the compressor.
  • the fuel tank is first filled with a fluorescent agent (physical properties similar to diesel) to simulate a diesel spray.
  • a fluorescent agent physical properties similar to diesel
  • the depth of the injector into the chamber can be adjusted to more realistically simulate the distance between the injector and the combustion chamber when the engine is at top dead center.
  • the compression mirror converts the beam into a beam of light that is vertically incident on the spray. Adjust the high-speed camera and beam splitter angle to bring the beam inside the incendiary to the camera and prepare for shooting
  • the air compressor is turned on.
  • the air compressor supplies power to the turbine to simulate the action of the exhaust gas.
  • the boost pressure reaches a preset value by adjusting the control valve in the air compressor
  • the synchronization signal is first sent to the electronic control unit by the computer.
  • the electronic control unit simultaneously controls the opening of the electromagnetic electromagnetic valve II, and then controls the opening of the electromagnetic valve III, and the piston rapidly ascends under the push of the high pressure gas (using In the simulation engine, the piston is up), the position sensor determines that the feedback signal is to be reached to the electronic control unit, and the electronic control unit immediately turns on the injector.
  • the Xecl excimer laser is irradiated to the spray, the phosphor is induced to emit light.
  • two high-speed cameras are controlled for shooting, and the acquisition system collects data of the temperature sensor and the pressure sensor.
  • the effect of the vortex bypass on the spray characteristics is the same as the above process, except that the solenoid valve II is closed and the solenoid valve ⁇ is opened.

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Abstract

一种模拟两级增压压端/涡端旁通对喷雾特性影响的装置和方法，装置包括压端旁通模拟系统、可变容积燃烧弹装置和喷雾拍摄系统，采用复合激光诱导荧光技术在可变容积燃烧弹内研究压端/涡端旁通对喷雾化、混合，发展历程，浓度分布以及微观特性况的影响，能够较真实的模拟在活塞（27）接近上止点时压端/涡端旁通对喷雾特性的影响，为深入研究采用压/涡端旁通后改善喷雾雾化和混合从而实现高效清洁燃烧提供理论数据支持。

Description

模拟两级增压压端/涡端旁通对喷雾特性影响的装置和方法 技术领域
本发明涉及汽车发动机技术领域，具体为一种模拟两级增压压端/涡端旁通对喷雾特性影响的装置和方法。
背景技术
随着对内燃机热效率的追求，以及排放法规的日益严格，单级涡轮增压满足不了柴油机对大流量的使用需求。在两级增压系统中，压端旁通的出现对两级增压系统具有重大的意义。目前，最常用的是在高压级增压器压端并联一条旁通道，它的存在对进气量的调节更为灵活，尤其针对变工况时对气量的不同需求。当压端旁通阀开启后，高压级压气机出口的气体倒流回高压级压气机入口端，这样就在高压级和旁通阀之间形成了个气流循环，从而减少了进入气缸内的气流量。涡端旁通与压端旁通则不同，涡轮出口的气压不会高于入口的气压，所以当涡端阀开启后部分气流从旁边的支路流到涡轮的出口端而不经过涡轮，这样降低了涡轮的效率从而影响了压气机的工作状态。压端/涡端旁通阀的开启不仅减少了进气量，还对气体的流通特性产生影响，从而影响了燃料喷射时的喷雾锥角以及油滴破碎后粒径分布，浓度场分布。
发明内容
针对上述问题，本发明的目的在于提供一种模拟两级增压压端/涡端旁通对喷雾特性影响的装置和方法，能够解决实际的内燃机中，压端/涡端旁通对喷雾特性不可见的问题，能够较真实的模拟在活塞接近上止点时压端/涡端旁通对喷雾特性的影响，为深入研究采用压/涡端旁通后改善喷雾雾化和混合从而实现高效清洁燃烧提供理论数据支持。技术方案如下：
一种模拟两级增压压端/涡端旁通对喷雾特性影响的装置，包括压端旁通模拟系统、可变容积燃烧弹装置和喷雾拍摄系统；
所述压端旁通模拟系统包括空气压缩机、低压级涡轮、高压级涡轮、空气滤清器、低压级压气机和高压级压气机；
空气压缩机的出气口连接到低压级涡轮的进气口，低压级涡轮的出气口连接到高压级涡轮的进气口，靠近低压级涡轮出气口处设有涡端温度传感器Ⅰ和涡端压力传感器Ⅰ；高压级涡轮的进气口和出气口之间设有涡端旁通支路，涡端旁通支路上设有电磁阀Ⅰ，电磁阀Ⅰ与高压级涡轮的出气口连接的一侧设有涡端温度传感器Ⅱ和涡端压力传感器Ⅱ；高压级涡轮的出气 口还连接到通向大气的气管；
空气滤清器的出气口连接到低压级压气机的进气口，低压级压气机的出气口连接到高压级压气机的进气口，靠近低压级压气机出气口处设有温度传感器Ⅰ和压力传感器Ⅰ；靠近高压级压气机出气口处设有温度传感器Ⅱ和压力传感器Ⅱ；高压级压气机的进气口和出气口之间设有压端旁通支路，压端旁通支路上设有电磁阀Ⅱ，电磁阀Ⅱ与高压级压气机出气口连接的一侧设有压力传感器Ⅲ和温度传感器Ⅲ；
所述低压级涡轮与低压级压气机通过共同的旋转轴相互连接，所述高压级涡轮与高压级压气机通过共同的旋转轴相互连接；
所述可变容积燃烧弹装置包括圆筒状的燃烧室和其内部的活塞；燃烧室上方设有燃烧弹上端盖，燃烧弹上端盖安装有喷油器，并设有通过排气管连接到真空泵的通孔，及连接到高压级压气机出气口的通孔；燃烧室底部设有放气管和进气管；进气管连接到储气的钢瓶，进气管上还设有电磁阀Ⅲ和减压阀；放气管上设有放气阀；燃烧室侧壁上设有燃烧弹视窗Ι与燃烧弹视窗Ⅱ；所述活塞底部这样位置传感器；
所述喷雾拍摄系统包括分光镜、Xecl准分子激光器，及用于拍摄气相的高速摄影机ICCDΙ和用于拍摄液相的高速摄影机ICCDΠ；分光镜置于燃烧弹视窗Ι外，高速摄影机ICCDΙ和高速摄影机ICCDΠ的焦点于分光镜上合并；Xecl准分子激光器发出的激光经反光镜Ι和反光镜Ⅱ反射，并依次经扩束镜、准直镜和压缩镜转化成一束片光，再通过燃烧弹视窗Ⅱ照射到燃烧室内；
以上所有的传感器、电磁阀和高速摄影机ICCD，以及喷油器、空气压缩机、Xecl准分子激光器均连接到电控与采集单元，电控与采集单元接收计算机发出的控制信号，实现喷油、摄影，及电磁阀启闭的控制。
进一步的，所述燃烧弹视窗Ι与燃烧弹视窗Ⅱ在燃烧室壁上呈90°角分布。
更进一步的，所述活塞顶部为ω燃烧室形状；燃烧室内壁上设有用于对活塞限位的挡圈；活塞燃烧室内壁间设有密封圈。
一种采用模拟两级增压压端/涡端旁通对喷雾特性影响的装置的实验方法，包括以下步骤：
步骤1：将油箱中填充荧光剂用来模拟柴油喷雾，调整喷油器伸入燃烧室到合适的深度；
步骤2：打开Xecl准分子激光器，调整反光镜Ι和反光镜Ⅱ，使Xecl准分子激光器发出的激光到扩束镜前，经过扩束镜改变激光的直径，并且经过准直镜将光束汇聚，最后经过压缩镜将光束转化为一束片光垂直照射在燃烧室内；
步骤3：调整两台高速摄影机和分光镜的角度，将燃烧弹内的光束引到摄影机前；
步骤4：打开空气压缩机，并调节空气压缩机内的控制阀使增压压力达到预设值；
步骤5：控制电磁阀Ⅱ或电磁阀Ι开启，随后控制电磁阀Ⅲ开启；
步骤6：当活塞上行到预定位置，控制喷油器打开产生喷雾，因荧光剂受激光的诱导而发光；
步骤7：控制两台高速摄像机进行拍摄，同时采集所以温度传感器和压力传感器的数据；
步骤8：关闭所有电磁阀，打开放气阀，使活塞回位，打开真空泵抽出燃烧室内的空气和喷雾滴液。
进一步的，所述步骤4中，增压压力若低于预设增压压力，空气压缩机中控制阀根据电控与采集单元发出的信号将阀门开大并且提高其功率，使之向目标值靠近；增压压力若高于预设增压压力，空气压缩机中控制阀根据电控与采集单元发出的信号将阀门关小并且减小其功率，使之向目标值靠近。
本发明的有益效果是：
1.本发明提供了一个模拟两级增压压端/涡端旁通对喷雾特性影响装置，能够为进一步优化喷油策略提供依据；
2.本发明利用压气机代替废气驱动涡轮，有利于简化装置，并且使模拟装置更加接近真实情况，使方案更容易实现；
3.本发明利用安装的温度和压力传感器可更好的分析出在旁通阀开启后气流流场的变化；
4.本发明利用可变容积燃烧弹更加真实的模拟出在发动机内压缩上止点的气流的流场；
5.本发明在可移动的活塞上加工出燃烧室的形状，有利于真实的模拟出燃烧室对喷雾的影响。
附图说明
图1为本发明模拟两级增压压端/涡端旁通对喷雾特性影响装置结构示意图。
图2为本发明模拟两级增压压端/涡端旁通对喷雾特性影响实验方法流程图。
图中：1-空气压缩机；2-空气滤清器；3-低压级涡轮；4-低压级压气机；5-温度传感器Ⅰ；6-压力传感器Ⅰ；7-涡端温度传感器Ⅰ；8-涡端压力传感器Ⅰ；9-电磁阀；10-涡端温度传感器Ⅱ；11-涡端压力传感器Ⅱ；12-高压级涡轮；13-高压级压气机；14温度传感器Ⅱ；15-压力传感器Ⅱ；16-电磁阀Ⅱ；17-压力传感器Ⅲ；18-温度传感器Ⅲ；19-喷油器；20-计算机；21-高速摄影机1CCDⅠ；22-分光镜23-高速摄影机lCCDΠ；24-放气 阀；25-放气管；26-挡圈；27-活塞；28-密封圈；29-位置传感器；30-进气管；31-电磁阀Ⅲ；32-减压阀；33-钢瓶；34-燃烧弹上端盖；35-压缩镜；36-准直镜；37-扩束镜；38-反光镜Ⅰ；39-反光镜Ⅱ；40-Xecl准分子激光器；41-排气管；42-真空泵；43-电控与采集单元。
具体实施方式
下面结合附图和具体实施例对本实用新型做进一步详细说明。如图1所示，一种模拟两级增压压端/涡端旁通对喷雾特性影响的装置，，包括压端旁通模拟系统、可变容积燃烧弹装置和喷雾拍摄系统。
所述压端旁通模拟系统包括空气压缩机1、低压级涡轮3、高压级涡轮12、空气滤清器2、低压级压气机4和高压级压气机13。
空气压缩机1的出气口连接到低压级涡轮3的进气口，低压级涡轮3的出气口连接到高压级涡轮12的进气口，靠近低压级涡轮3出气口处设有涡端温度传感器Ⅰ7和涡端压力传感器Ⅰ8；高压级涡轮12的进气口和出气口之间设有涡端旁通支路，涡端旁通支路上设有电磁阀Ⅰ9，电磁阀Ⅰ9与高压级涡轮12的出气口连接的一侧设有涡端温度传感器Ⅱ10和涡端压力传感器Ⅱ11。电磁阀Ⅰ打开时，涡端旁通支路可使空气不经过高压级涡轮，直接从低压级涡轮出口端到高压级涡轮出口端；高压级涡轮的出气口还连接到通向大气的气管。
空气滤清器2的出气口连接到低压级压气机4的进气口，低压级压气机4的出气口连接到高压级压气机13的进气口，靠近低压级压气机4出气口处设有温度传感器Ⅰ5和压力传感器Ⅰ6；靠近高压级压气机13出气口处设有温度传感器Ⅱ14和压力传感器Ⅱ15；高压级压气机13的进气口和出气口之间设有压端旁通支路，压端旁通支路上设有电磁阀Ⅱ16，电磁阀Ⅱ16与高压级压气机13出气口连接的一侧设有压力传感器Ⅲ17和温度传感器Ⅲ18。高压级压气机13出气口通过管路与不定容燃烧弹的进气口相连。
所述低压级涡轮3与低压级压气机4通过共同的旋转轴相互连接，所述高压级涡轮12与高压级压气机13通过共同的旋转轴相互连接。
所述可变容积燃烧弹装置包括圆筒状的燃烧室和其内部的活塞27；燃烧室上方设有燃烧弹上端盖34，燃烧弹上端盖34安装有喷油器19，并设有通过排气管41连接到真空泵42的通孔，及连接到高压级压气机13出气口的通孔；所述燃烧弹上端盖34通过螺栓与缸体连接在一起，其上部有三个孔。一个孔用于安装喷油器19，一个与管路相接，用于让空气进入燃烧弹内，另一个与排气管41相连用于排气。
燃烧室底部设有放气管25和进气管30；进气管30连接到储气的钢瓶33，进气管30 上还设有电磁阀Ⅲ31和减压阀32；放气管25上设有放气阀24。燃烧室侧壁上设有燃烧弹视窗Ι与燃烧弹视窗Ⅱ；所述活塞27底部这样位置传感器29。为了方便布置外部设备，本实施例的燃烧弹装置侧壁上相隔90度分布有四个视窗用于拍摄。
所述活塞27顶部为ω燃烧室形状；燃烧室内壁上设有用于对活塞27限位的挡圈26；活塞27燃烧室内壁间设有密封圈28。
所述喷雾拍摄系统包括分光镜22、Xecl准分子激光器40，及用于拍摄气相的高速摄影机ICCDΙ21和用于拍摄液相的高速摄影机ICCDΠ23；分光镜22置于燃烧弹视窗Ι外，高速摄影机ICCDΙ21和高速摄影机ICCDΠ23的焦点于分光镜22上合并；Xecl准分子激光器40发出的激光经反光镜Ι39和反光镜Ⅱ38反射，并依次经扩束镜37、准直镜36和压缩镜转化成一束片光，再通过燃烧弹视窗Ⅱ照射到燃烧室内；
以上所有的传感器、电磁阀和高速摄影机ICCD，以及喷油器19、空气压缩机1、Xecl准分子激光器40均连接到电控与采集单元43，电控与采集单元43接收计算机20发出的控制信号，实现喷油、摄影，及电磁阀启闭的控制。
控制方法：
电控与采集单元可控制空气压缩机内控制阀的开度和空气压缩机工作功率，并且可同时接收到空气压气机反馈的气体压力和流量信号和采集到的各温度压力传感器信号。
在电控系统中输入需要模拟的预设增压压力，电控与采集单元粗略计算出空气压缩机应该输出气体的流量与压力，并且控制空气压缩机以一定的功率开始工作。与此同时，电控与采集单元根据接收采集压力传感器Ⅲ的信号和空气压气机反馈的气体压力和流量信号后，发出控制信号微调空气压缩机。
增压压力若低于预设增压压力，空气压缩机中控制阀根据电控与采集单元发出的信号将阀门开大并且提高其功率，使之向目标值靠近。
增压压力若高于预设增压压力，空气压缩机中控制阀根据电控与采集单元发出的信号将阀门关小并且减小其功率，使之向目标值靠近。
试验原理：
温度传感器Ι和压力传感器Ι采集到的数据用于计算低压级压气机出口流量，并且监测高压级压气机入口端气体压力的变化。利用理想气体状态方程PV＝mRT，可算出质量流量m，式中P理想气体为压力，V为体积，R为理想气体常数，T理想气体为热力学温度。同理温度传感器Ⅱ和压力传感器Ⅱ用于当压端旁通阀开启后计算经过旁通支路的气体流量，温度传感器Ⅲ和压力传感器Ⅲ用于计算高压级压气机出口的流量，并且监测高压级压气机出口端气体 压力的变化。分析在压端旁通阀开启的过程中高压级压气机进出口端气体压力的变化、进入旁通支路的气体流量占高压级出口气体流量的比例以及支路中气体流动速度，为更好说明压端旁通不仅减少了气体流量还对气路的流动特性产生影响。结合激光诱导荧光的拍摄结果，为进一步解释压端旁通对喷雾的影响提供数据支持。
试验流程：
首先将油箱中填充荧光剂(物理性质与柴油相似)用来模拟柴油喷雾。通过加垫片的方式可调整喷油器伸入腔室的深度，更真实的模拟发动机内在上止点时喷油器和燃烧室之间的距离。
然后打开Xecl准分子激光器，调整反光镜Ι和调整反光镜Ⅱ使Xecl准分子激光器发出的激光到扩束镜前，经过扩束镜改变激光的直径，并且经过准直镜将光束汇聚，最后经过压缩镜将光束转化为一束片光垂直照射在喷雾上。调整高速摄影机和分光镜角度将燃烧弹内的光束引到摄影机前，为拍摄做准备
打开空气压缩机，在模拟两级增压系统中，空气压缩机为涡轮提供动力，模拟废气的作用。通过调节空气压缩机内的控制阀使增压压力达到预设值
需要模拟压端旁通时，先利用计算机发出同步信号给电控单元，电控单元同时控制电磁电磁阀Ⅱ的开启，随后控制电磁阀Ⅲ的开启，活塞在高压气体的推动下迅速上行(用于模拟发动机中活塞的上行)，位置传感器判断出将要到达挡圈处反馈信号给电控单元，电控单元立即打开喷油器，这时Xecl准分子激光器照射到喷雾时，诱导荧光剂发光，这时控制两高速摄影机进行拍摄，同时采集系统采集温度传感器和压力传感器的数据。
在模拟结束后，关闭所有电磁阀，打开放气阀24，使活塞回位，打开真空泵抽出内的空气和喷雾液滴为下次模拟做准备。
涡端旁通对喷雾特性的影响实验过程与上述过程同理，区别在于关闭电磁阀Ⅱ，开启电磁阀Ι。

Claims (5)

  1. 一种模拟两级增压压端/涡端旁通对喷雾特性影响的装置，其特征在于，包括压端旁通模拟系统、可变容积燃烧弹装置和喷雾拍摄系统；
    所述压端旁通模拟系统包括空气压缩机(1)、低压级涡轮(3)、高压级涡轮(12)、空气滤清器(2)、低压级压气机(4)和高压级压气机(13)；
    空气压缩机(1)的出气口连接到低压级涡轮(3)的进气口，低压级涡轮(3)的出气口连接到高压级涡轮(12)的进气口，靠近低压级涡轮(3)出气口处设有涡端温度传感器Ⅰ(7)和涡端压力传感器Ⅰ(8)；高压级涡轮(12)的进气口和出气口之间设有涡端旁通支路，涡端旁通支路上设有电磁阀Ⅰ(9)，电磁阀Ⅰ(9)与高压级涡轮(12)的出气口连接的一侧设有涡端温度传感器Ⅱ(10)和涡端压力传感器Ⅱ(11)；高压级涡轮(12)的出气口还连接到通向大气的气管；
    空气滤清器(2)的出气口连接到低压级压气机(4)的进气口，低压级压气机(4)的出气口连接到高压级压气机(13)的进气口，靠近低压级压气机(4)出气口处设有温度传感器Ⅰ(5)和压力传感器Ⅰ(6)；靠近高压级压气机(13)出气口处设有温度传感器Ⅱ(14)和压力传感器Ⅱ(15)；高压级压气机(13)的进气口和出气口之间设有压端旁通支路，压端旁通支路上设有电磁阀Ⅱ(16)，电磁阀Ⅱ(16)与高压级压气机(13)出气口连接的一侧设有压力传感器Ⅲ(17)和温度传感器Ⅲ(18)；
    所述低压级涡轮(3)与低压级压气机(4)通过共同的旋转轴相互连接，所述高压级涡轮(12)与高压级压气机(13)通过共同的旋转轴相互连接；
    所述可变容积燃烧弹装置包括圆筒状的燃烧室和其内部的活塞(27)；燃烧室上方设有燃烧弹上端盖(34)，燃烧弹上端盖(34)安装有喷油器(19)，并设有通过排气管(41)连接到真空泵(42)的通孔，及连接到高压级压气机(13)出气口的通孔；燃烧室底部设有放气管(25)和进气管(30)；进气管(30)连接到储气的钢瓶(33)，进气管(30)上还设有电磁阀Ⅲ(31)和减压阀(32)；放气管(25)上设有放气阀(24)；燃烧室侧壁上设有燃烧弹视窗Ι与燃烧弹视窗Ⅱ；所述活塞(27)底部这样位置传感器(29)；
    所述喷雾拍摄系统包括分光镜(22)、Xecl准分子激光器(40)，及用于拍摄气相的高速摄影机ICCDΙ(21)和用于拍摄液相的高速摄影机ICCDΠ(23)；分光镜(22)置于燃烧弹视窗Ι外，高速摄影机ICCDΙ(21)和高速摄影机ICCDΠ(23)的焦点于分光镜(22)上合并；Xecl准分子激光器(40)发出的激光经反光镜Ι(39)和反光镜Ⅱ(38)反射，并依次经扩束镜(37)、准直镜(36)和压缩镜转化成一束片光，再通过燃烧弹视窗Ⅱ照射到燃烧室内；
    以上所有的传感器、电磁阀和高速摄影机ICCD，以及喷油器(19)、空气压缩机(1)、Xecl准分子激光器(40)均连接到电控与采集单元(43)，电控与采集单元(43)接收计算机(20)发出的控制信号，实现喷油、摄影，及电磁阀启闭的控制。
  2. 根据权利要求1所述的模拟两级增压压端/涡端旁通对喷雾特性影响的装置，其特征在于，所述燃烧弹视窗Ι与燃烧弹视窗Ⅱ在燃烧室壁上呈90°角分布。
  3. 根据权利要求1所述的模拟两级增压压端/涡端旁通对喷雾特性影响的装置，其特征在于，所述活塞(27)顶部为ω燃烧室形状；燃烧室内壁上设有用于对活塞(27)限位的挡圈(26)；活塞(27)燃烧室内壁间设有密封圈(28)。
  4. 一种采用权利要求1所述的模拟两级增压压端/涡端旁通对喷雾特性影响的装置的实验方法，其特征在于，包括以下步骤：
    步骤1：将油箱中填充荧光剂用来模拟柴油喷雾，调整喷油器伸入燃烧室到合适的深度；
    步骤2：打开Xecl准分子激光器，调整反光镜Ι和反光镜Ⅱ，使Xecl准分子激光器发出的激光到扩束镜前，经过扩束镜改变激光的直径，并且经过准直镜将光束汇聚，最后经过压缩镜将光束转化为一束片光垂直照射在燃烧室内；
    步骤3：调整两台高速摄影机和分光镜的角度，将燃烧弹内的光束引到摄影机前；
    步骤4：打开空气压缩机，并调节空气压缩机内的控制阀使增压压力达到预设值；
    步骤5：控制电磁阀Ⅱ或电磁阀Ι开启，随后控制电磁阀Ⅲ开启；
    步骤6：当活塞上行到预定位置，控制喷油器打开产生喷雾，因荧光剂受激光的诱导而发光；
    步骤7：控制两台高速摄像机进行拍摄，同时采集所以温度传感器和压力传感器的数据；
    步骤8：关闭所有电磁阀，打开放气阀，使活塞回位，打开真空泵抽出燃烧室内的空气和喷雾滴液。
  5. 根据权利要求4所述的模拟两级增压压端/涡端旁通对喷雾特性影响的装置的实验方法，其特征在于，所述步骤4中，增压压力若低于预设增压压力，空气压缩机中控制阀根据电控与采集单元发出的信号将阀门开大并且提高其功率，使之向目标值靠近；增压压力若高于预设增压压力，空气压缩机中控制阀根据电控与采集单元发出的信号将阀门关小并且减小其功率，使之向目标值靠近。
PCT/CN2019/070087 2018-01-05 2019-01-02 模拟两级增压压端/涡端旁通对喷雾特性影响的装置和方法 WO2019134645A1 (zh)

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