技术领域technical field
本发明属于内嵌火箭冲压组合发动机技术领域，具体涉及一种来流参数宽范围可调的亚-超剪切层研究实验装置。The invention belongs to the technical field of embedded rocket ramjet combined engine, and in particular relates to a sub-supershear layer research experiment device with adjustable incoming flow parameters in a wide range.
背景技术Background technique
内嵌火箭冲压组合发动机以其能够兼顾火箭发动机的大推力性能以及冲压发动机的高比冲性能而被广泛关注，自然其工作过程中所涉及的流动燃烧问题的研究则具有重要意义。超声速火箭尾流与亚声速冲压气流之间的混合流动过程对于燃烧室的高效燃烧及发动机性能具有直接影响关系。因此，对于亚-超剪切层一类的可压缩剪切层研究十分必要。相比于一般可压缩剪切混合流动而言，火箭尾气与冲压气流之间形成的剪切层具有速度梯度大、温度梯度大、发展空间受限等特点，从而导致剪切混合流可压缩性更强，流场结构更加复杂。而目前，对于亚-超剪切层的实验研究多针对相对较小的速度梯度以及温度梯度工况展开。例如，比较典型的Stanford大学高温气动实验室(Journal of FluidMechanical,1995)的可压缩剪切层实验装置为二维平面亚-超剪切，主要包括增压段、试验段、扩张段等，其中增压段内由超声速喷管和亚声速喷管组成，中间由隔板隔开；而亚声速和超声速气流均是经过空压机压缩进入一定规格的储箱，并分别在各自控制阀的作用下提供来流条件。该装置实验过程中速度范围为110～508m/s,温度为常温；后期经过改进(Tobias Rossmann的博士论文)，温度最高可达700K。国内国防科学技术大学的超声速混合层风洞(赵玉新博士论文)为真空抽吸式结构，主要用于研究超-超气流之间的剪切作用，实验温度为常温，速度范围为400～670m/s。综合国内外的研究发现，目前亚-超剪切层研究的实验装置大多针对对流马赫数Mc<1，的情况开展研究，Mc＝(u1-u2)/(c1+c2),其中u为气流速度，c为气流的当地声速，而对于更高的Mc状态相应的实验研究则较少。因此，一种来流参数大梯度宽范围可调节的亚-超剪切层研究实验装置的设计尤为重要。Embedded rocket ramjet engine has attracted extensive attention because it can take into account the high thrust performance of rocket engine and the high specific impulse performance of ramjet engine. Naturally, the research on the flow combustion problems involved in its working process is of great significance. The mixing flow process between the supersonic rocket wake and the subsonic ram jet has a direct impact on the efficient combustion of the combustor and the performance of the engine. Therefore, it is very necessary to study the compressible shear layers such as sub-hypershear layers. Compared with the general compressible shear mixed flow, the shear layer formed between the rocket exhaust gas and the ram airflow has the characteristics of large velocity gradient, large temperature gradient, and limited development space, which leads to the compressibility of the shear mixed flow. Stronger, the flow field structure is more complex. At present, the experimental research on the sub-hypershear layer is mostly carried out for relatively small velocity gradient and temperature gradient conditions. For example, the typical compressible shear layer experimental device of Stanford University High Temperature Pneumatic Laboratory (Journal of Fluid Mechanical, 1995) is a two-dimensional plane sub-supershear, mainly including pressurization section, test section, expansion section, etc., among which The pressurized section is composed of a supersonic nozzle and a subsonic nozzle, separated by a partition in the middle; while the subsonic and supersonic airflows are compressed by an air compressor and enter a storage tank of a certain specification, and are respectively controlled by the respective control valves. The flow conditions are provided below. During the experiment, the speed range of the device is 110-508m/s, and the temperature is normal temperature; after improvement (Tobias Rossmann's doctoral thesis), the temperature can reach up to 700K. The supersonic mixed-layer wind tunnel of the National University of Defense Technology (Zhao Yuxin’s doctoral dissertation) is a vacuum pumping structure, mainly used to study the shearing effect between super-superflow, the experimental temperature is normal temperature, and the speed range is 400-670m/ s. Based on domestic and foreign researches, most of the current experimental devices for sub-supershear layer research are conducted for the convective Mach number Mc<1, where Mc=(u1-u2)/(c1+c2), where u is the air flow Velocity, c is the local sound velocity of the gas flow, and there are less experimental studies for the corresponding higher Mc states. Therefore, the design of an experimental device for sub-hypershear layer research with large gradients and wide ranges of incoming flow parameters is particularly important.
发明内容Contents of the invention
本发明所要解决的技术问题在于针对上述现有技术的不足，提供一种来流参数宽范围可调的亚-超剪切层研究实验装置，能够满足来流参数宽范围可调节的亚-超剪切层发展特性研究。The technical problem to be solved by the present invention is to provide a sub-hypershear layer research experimental device with wide-range adjustable incoming flow parameters, which can meet the wide-range adjustable incoming flow parameters. Study on the characteristics of shear layer development.
为解决上述技术问题，本发明采用的技术方案是，一种来流参数宽范围可调的亚-超剪切层研究实验装置，包括相连接且内部连通的试验段腔体和观察段腔体，试验段腔体的前端用于与亚声速气流装置相连通；试验段腔体内沿轴向安装有超声速喷管，超声速喷管与高温气流相连通，其内用于高温气流贯穿通过，变为超声速气流；超声速喷管与试验段腔体的走向相一致，其后端穿出试验段腔体的后端；超声速喷管的宽度与试验段腔体的宽度相一致，安装超声速喷管后，将试验段腔体内分成上下两个独立的流道，使进入的亚声速气流分成对应的两路，由该两个流道贯穿通行，超声速气流与亚声速气流由对应的出口进入观察段腔体内，进入的同时，两种气流进行剪切混合。In order to solve the above-mentioned technical problems, the technical solution adopted in the present invention is a sub-hypershear layer research experimental device with adjustable incoming flow parameters in a wide range, including a connected and internally connected test section cavity and an observation section cavity , the front end of the cavity of the test section is used to communicate with the subsonic airflow device; the cavity of the test section is installed with a supersonic nozzle along the axial direction, and the supersonic nozzle is connected with the high-temperature airflow, and is used for the high-temperature airflow to pass through it. Supersonic air flow; the supersonic nozzle is consistent with the direction of the test section cavity, and its rear end passes through the rear end of the test section cavity; the width of the supersonic nozzle is consistent with the width of the test section cavity. After installing the supersonic nozzle, Divide the chamber of the test section into two separate upper and lower flow channels, so that the incoming subsonic air flow is divided into two corresponding paths, which pass through the two flow channels, and the supersonic air flow and subsonic air flow enter the cavity of the observation section through the corresponding outlets. , while entering, the two air streams are shear mixed.
进一步地，还包括燃气发生器，燃气发生器与超声速喷管相连通，其内用于不同当量比的乙烯与空气混合燃烧，以提供不同温度的高温气流。Further, a gas generator is also included, and the gas generator is connected with the supersonic nozzle, and the gas generator is used for mixed combustion of ethylene and air in different equivalent ratios, so as to provide high-temperature airflows of different temperatures.
进一步地，该声速喷管沿气流流向上包括依次相连接的支板、燃气整流段和拉法尔喷管段；支板沿气流流向包括一体连接的实心楔形段和等直段，等直段与燃气整流段的进口端一体密封连接；燃气整流段和拉法尔喷管段一体连接、且相连通，形成贯通的腔体，且在沿气流方向上，拉法尔喷管段的内型面为拉法尔结构；燃气整流段上、且位于其前端开设有连通外部与腔体的通孔。Further, the sonic nozzle includes a support plate, a gas rectification section and a Rafal nozzle section connected in sequence along the airflow direction; the support plate includes an integrally connected solid wedge section and a straight section along the flow direction of the airflow, and the straight section and the The inlet end of the gas rectification section is integrally sealed and connected; the gas rectification section and the Lafal nozzle section are integrally connected and communicated to form a through cavity, and along the airflow direction, the inner surface of the Lafal nozzle section is drawn Farr structure; on the gas rectifying section and at its front end, there is a through hole connecting the outside and the cavity.
进一步地，该试验段腔体上、且位于其前端，开设有垂直腔体、并与腔体相连通的高温气流通道，用于连通燃气发生器和超声速喷管；在装配时，高温气流通道的位置与通孔的位置相对应。Further, on the cavity of the test section and at its front end, there is a vertical cavity and a high-temperature airflow channel communicating with the cavity, which is used to communicate with the gas generator and the supersonic nozzle; during assembly, the high-temperature airflow channel The position corresponds to the position of the through hole.
进一步地，该试验段腔体与超声速喷管可拆卸安装，试验段腔体的前后侧的内壁上轴向设置有凸棱，超声速喷管的外壁上，其相对侧轴向开设有与凸棱相配装的凹槽。Further, the cavity of the test section and the supersonic nozzle can be detachably installed, the inner walls of the front and rear sides of the cavity of the test section are axially provided with ribs, and the outer wall of the supersonic nozzle is axially provided with ribs on the opposite side. matching grooves.
进一步地，该试验段腔体和观察段腔体可拆卸连接，实现方式为：在试验段腔体和观察段腔体上、且位于连接处开设连接孔，连接孔通过固定销连接固定。Further, the cavity of the test section and the cavity of the observation section are detachably connected, and the realization method is: a connection hole is opened on the cavity of the test section and the cavity of the observation section at the joint, and the connection hole is connected and fixed by a fixing pin.
进一步地，该燃气整流段内，且与通孔相对侧面，内侧壁沿气流流向方向为圆弧状。Further, in the gas straightening section, and on the side opposite to the through hole, the inner side wall is arc-shaped along the direction of air flow.
进一步地，该超声速喷管安装于试验段腔体的中轴线位置处。Further, the supersonic nozzle is installed at the central axis of the cavity of the test section.
进一步地，该观察段腔体的壁体采用光学玻璃，光学玻璃通过设置于其上的盖板与试验段腔体固定，并且盖板只覆盖于光学玻璃的四边上。Further, the wall of the cavity of the observation section is made of optical glass, and the optical glass is fixed to the cavity of the test section through a cover plate arranged thereon, and the cover plate only covers the four sides of the optical glass.
本发明还公开了上述的一种超声速喷管，其内部用于气流贯通穿过，沿气流流向上包括依次相连接的支板、燃气整流段和拉法尔喷管段；支板沿气流流向包括一体连接的实心楔形段和等直段，等直段与燃气整流段的进口端一体密封连接；燃气整流段和拉法尔喷管段一体连接、且相连通，形成贯通的腔体，且在沿气流方向上，拉法尔喷管段的内型面为拉法尔结构；燃气整流段上、且位于其前端开设有连通外部与腔体的通孔。The invention also discloses the above-mentioned supersonic nozzle, the inside of which is used for airflow to pass through, and includes a support plate, a gas rectification section and a Lafal nozzle section connected in sequence along the airflow direction; the support plate includes a The integrally connected solid wedge section and equal straight section, the equal straight section is integrally sealed with the inlet end of the gas rectification section; the gas rectification section and the Lafal nozzle section are integrally connected and connected to form a through cavity, and along the In the airflow direction, the inner surface of the Rafal nozzle section is a Rafal structure; on the gas rectifying section and at its front end, there is a through hole connecting the outside and the cavity.
本发明一种来流参数宽范围可调的亚-超剪切层研究实验装置具有如下优点：采用乙烯燃烧加热方式获得高温燃气，并通过调整燃料和空气的当量比以实现温度的宽范围调节，通过调整可拆卸的超声速喷管段拉伐尔喷管的扩张比实现速度的宽范围调节，并由此获得来流参数宽范围可调节的亚-超剪切层；这样能够更加真实的模拟实际工作过程中高温燃气与常温冲压气流之间的剪切混合作用，结合测试技术掌握亚-超剪切层发展规律及来流参数对剪切层增长率的影响特性，对于工程实际应用中提出合理适用的增强混合措施奠定基础，同时对于深入了解亚-超剪切混合流这类湍流流动问题提供实验数据支撑。同时，本发明具有简单、易实现的优势。A sub-hypershear layer research experimental device with wide-range adjustable incoming flow parameters has the following advantages: high-temperature gas is obtained by means of ethylene combustion heating, and wide-range adjustment of temperature can be realized by adjusting the equivalent ratio of fuel and air , by adjusting the expansion ratio of the detachable supersonic nozzle Laval nozzle to achieve a wide range of velocity adjustment, and thus obtain a sub-supershear layer with a wide range of adjustable flow parameters; this can more realistically simulate the actual During the working process, the shear mixing effect between high-temperature gas and normal temperature ram airflow, combined with test technology to grasp the development law of sub-hypershear layer and the influence characteristics of incoming flow parameters on the growth rate of shear layer, is useful for engineering practical application. Applicable enhanced mixing measures lay the foundation, and at the same time provide experimental data support for in-depth understanding of turbulent flow problems such as sub-supershear mixed flow. At the same time, the present invention has the advantages of being simple and easy to realize.
附图说明Description of drawings
图1是本发明一种来流参数宽范围可调的亚-超剪切层研究实验装置的后视结构示意图。Fig. 1 is a rear view structural schematic diagram of a sub-hypershear layer research experimental device with adjustable incoming flow parameters in a wide range of the present invention.
图2为本发明一种来流参数宽范围可调的亚-超剪切层研究实验装置的后视结构示意图的D-D剖面图；Fig. 2 is the D-D sectional view of the rear view structure schematic diagram of a sub-hypershear layer research experimental device with adjustable incoming flow parameters in a wide range of the present invention;
图3为本发明中超声速喷管的纵剖面图；Fig. 3 is the longitudinal sectional view of supersonic nozzle among the present invention;
图4为试验段腔体内纹影实验结果；Figure 4 is the result of the schlieren experiment in the cavity of the test section;
图5为纹影实验获得的归一化厚度增长率与理论结果对比图；Figure 5 is a comparison chart between the normalized thickness growth rate obtained by the schlieren experiment and the theoretical result;
其中：1.试验段腔体；2.观察段腔体；3超声速喷管；3-1.支板；3-2.燃气整流段；3-3.拉法尔喷管段；4.燃气发生器；5.观测窗；6.盖板；7.高温气流通道；8.连接孔；9.固定销。Among them: 1. Test section cavity; 2. Observation section cavity; 3 Supersonic nozzle; 3-1. Support plate; 3-2. Gas rectification section; 3-3. Lafal nozzle section; 4. Gas generation 5. Observation window; 6. Cover plate; 7. High temperature air flow channel; 8. Connection hole; 9. Fixed pin.
具体实施方式Detailed ways
本发明一种来流参数宽范围可调的亚-超剪切层研究实验装置，如图1和图2所示，包括相连接且内部连通的试验段腔体1和观察段腔体2，试验段腔体1的前端用于与亚声速气流装置相连通；试验段腔体1内沿轴向安装有超声速喷管3，超声速喷管3与高温气流相连通，其内用于高温气流贯穿通过，变为超声速气流；超声速喷管3与试验段腔体1的走向相一致，其后端穿出试验段腔体1的后端；超声速喷管3的宽度与试验段腔体1的宽度相一致，安装超声速喷管3后，将试验段腔体1内分成上下两个独立的流道，使进入的亚声速气流分成对应的两路，由该两个流道贯穿通行，超声速气流与亚声速气流由对应的出口进入观察段腔体2内，进入的同时，两种气流进行剪切混合。A kind of sub-hypershear layer research experimental device with adjustable incoming flow parameters in a wide range of the present invention, as shown in Figure 1 and Figure 2, comprises a test section cavity 1 and an observation section cavity 2 which are connected and internally communicated, The front end of the chamber 1 of the test section is used to communicate with the subsonic airflow device; the chamber 1 of the test section is installed with a supersonic nozzle 3 along the axial direction, and the supersonic nozzle 3 is connected with the high-temperature airflow, and is used for the high-temperature airflow to pass through Pass through and become a supersonic airflow; the supersonic nozzle 3 is consistent with the direction of the test section cavity 1, and its rear end passes through the rear end of the test section cavity 1; the width of the supersonic nozzle 3 is the same as the width of the test section cavity 1 Consistently, after the supersonic nozzle 3 is installed, the cavity 1 of the test section is divided into upper and lower two independent flow channels, so that the incoming subsonic air flow is divided into two corresponding paths, and the two flow channels pass through, and the supersonic air flow and The subsonic airflow enters the cavity 2 of the observation section from the corresponding outlet, and at the same time as entering, the two airflows are sheared and mixed.
还包括燃气发生器4，燃气发生器4与超声速喷管3相连通，其内用于不同当量比的乙烯与空气混合燃烧，以提供不同温度的高温气流。It also includes a gas generator 4, which communicates with the supersonic nozzle 3, and is used for mixed combustion of ethylene and air in different equivalent ratios to provide high-temperature airflows at different temperatures.
如图3所示，超声速喷管3沿气流流向上包括依次相连接的支板3-1、燃气整流段3-2和拉法尔喷管段3-3；支板3-1沿气流流向包括一体连接的实心楔形段和等直段，等直段与燃气整流段3-2的进口端一体密封连接；燃气整流段3-2和拉法尔喷管段3-3一体连接、且相连通，形成贯通的腔体，且在沿气流方向上，拉法尔喷管段3-3的内型面为拉法尔结构；燃气整流段3-2上、且位于其前端开设有连通外部与腔体的通孔3-4。试验段腔体1上、且位于其前端，开设有垂直腔体、并与腔体相连通的高温气流通道7，用于连通燃气发生器4和超声速喷管3；在装配时，高温气流通道7的位置与通孔3-4的位置相对应。支板3-1的前端楔形结构及等直段能够将亚声速气流平滑分流为上下两股气流。As shown in Figure 3, the supersonic nozzle 3 includes a support plate 3-1, a gas rectification section 3-2 and a Rafael nozzle section 3-3 connected in sequence along the airflow direction; the support plate 3-1 includes The integrally connected solid wedge-shaped section and the equal straight section, the equal straight section is integrally sealed and connected to the inlet end of the gas rectification section 3-2; the gas rectification section 3-2 and the Lafal nozzle section 3-3 are integrally connected and communicated, A through cavity is formed, and along the airflow direction, the inner surface of the Rafal nozzle section 3-3 is a Rafal structure; on the gas rectifying section 3-2, and located at its front end, there is a cavity connecting the outside and the cavity. via holes 3-4. On the cavity 1 of the test section and at its front end, there is a vertical cavity and a high-temperature airflow channel 7 communicating with the cavity, which is used to communicate with the gas generator 4 and the supersonic nozzle 3; during assembly, the high-temperature airflow channel The position of 7 corresponds to the position of the through hole 3-4. The front wedge-shaped structure and the straight section of the support plate 3-1 can smoothly split the subsonic airflow into two upper and lower airflows.
为改变拉法尔喷管段3-3的不同扩张比，达到速度的宽范围变化，试验段腔体1与超声速喷管3可拆卸安装，试验段腔体1的前后侧的内壁上轴向设置有凸棱，超声速喷管3的外壁上，其相对侧轴向开设有与凸棱相配装的凹槽。In order to change the different expansion ratios of the Rafal nozzle section 3-3 and achieve a wide range of speed changes, the test section cavity 1 and the supersonic nozzle 3 are detachable and installed, and the inner walls of the front and rear sides of the test section cavity 1 are axially arranged There are ribs, and on the outer wall of the supersonic nozzle 3, grooves matched with the ribs are axially provided on the opposite side.
本发明中，试验段腔体1和观察段腔体2可拆卸连接，实现方式为：在试验段腔体1和观察段腔体2上、且位于连接处开设连接孔8，连接孔8通过固定销9连接固定。燃气整流段3-2内，且与通孔3-4相对侧面，内侧壁沿气流流向方向为圆弧状。超声速喷管3安装于试验段腔体1的中轴线位置处。观察段腔体2的壁体采用光学玻璃，光学玻璃通过设置于其上的盖板6与试验段腔体1固定，并且盖板6只覆盖于光学玻璃的四边上，即四面开窗方式，未被覆盖的玻璃形成观测窗5。In the present invention, the test section cavity 1 and the observation section cavity 2 are detachably connected, and the realization method is: on the test section cavity 1 and the observation section cavity 2, and at the joint, a connection hole 8 is opened, and the connection hole 8 passes through Fixed pin 9 is connected and fixed. Inside the gas rectifying section 3-2, and on the side opposite to the through hole 3-4, the inner side wall is arc-shaped along the direction of air flow. The supersonic nozzle 3 is installed at the central axis of the cavity 1 of the test section. The wall body of the observation section cavity 2 is made of optical glass, and the optical glass is fixed to the test section cavity 1 through the cover plate 6 arranged thereon, and the cover plate 6 is only covered on the four sides of the optical glass, that is, the four-sided windowing method, The uncovered glass forms the viewing window 5 .
本发明还公开了上述的一种超声速喷管，其内部用于气流贯通穿过，沿气流流向上包括依次相连接的支板3-1、燃气整流段3-2和拉法尔喷管段3-3；支板3-1沿气流流向包括一体连接的实心楔形段和等直段，等直段与燃气整流段3-2的进口端一体密封连接；燃气整流段3-2和拉法尔喷管段3-3一体连接、且相连通，形成贯通的腔体，且在沿气流方向上，拉法尔喷管段3-3的内型面为拉法尔结构；燃气整流段3-3上、且位于其前端开设有连通外部与腔体的通孔3-4。该燃气整流段3-2内，且与通孔3-4相对侧面，内侧壁沿气流流向方向为圆弧状。减小气流总压损失，同时对燃气整流段起到一定的加厚保护作用，避免高温燃气流将结构烧坏；燃气发生器4是通过螺钉与试验段腔体1进行固定连接，并采用石墨密封环进行密封；保证其高温气流通道7与燃气发生器4的出口对应。超声速喷管3则直接插入到试验段腔体1内，等直段的一侧还开设螺纹孔，并与试验段腔体1相同位置的圆孔连通，通过螺钉对超声速喷管3定位。燃气发生器4的头部分别与乙烯供应系统和空气供应系统连接，其中含氧量为30％，并在高能点火器的作用下燃烧产生高温燃气。低速流供应系统则通过螺栓与试验段腔体1连接，并用O型圈进行密封，以提供亚声速气流。亚声速气流则由一系列高压气瓶并联，在减压器和流量计的调节控制作用下获得，气流为常温气体，速度范围为0～300m/s。The present invention also discloses the above-mentioned supersonic nozzle, the inside of which is used for airflow to pass through, and includes a support plate 3-1, a gas rectification section 3-2 and a Lafal nozzle section 3 which are connected in sequence along the airflow direction. -3; The support plate 3-1 includes an integrally connected solid wedge-shaped section and an equal straight section along the air flow direction, and the equal straight section is integrally sealed with the inlet end of the gas rectification section 3-2; the gas rectification section 3-2 and the Rafael The nozzle sections 3-3 are integrally connected and communicated to form a through cavity, and along the airflow direction, the inner surface of the Rafal nozzle section 3-3 is a Rafal structure; the gas rectification section 3-3 , and a through hole 3-4 communicating with the outside and the cavity is opened at the front end thereof. Inside the gas rectifying section 3-2, and on the side opposite to the through hole 3-4, the inner side wall is arc-shaped along the direction of air flow. Reduce the total pressure loss of the air flow, and at the same time play a certain role in thickening the gas rectification section to prevent the structure from being burned by the high-temperature gas flow; the gas generator 4 is fixedly connected to the test section cavity 1 through screws, and uses graphite The sealing ring is sealed; it is ensured that the high-temperature gas flow channel 7 corresponds to the outlet of the gas generator 4 . The supersonic nozzle 3 is directly inserted into the cavity 1 of the test section, and a threaded hole is provided on one side of the straight section, which communicates with the round hole at the same position of the cavity 1 of the test section, and the supersonic nozzle 3 is positioned by screws. The head of the gas generator 4 is respectively connected with the ethylene supply system and the air supply system, wherein the oxygen content is 30%, and it burns under the action of a high-energy igniter to generate high-temperature gas. The low-velocity flow supply system is connected to the chamber 1 of the test section through bolts and sealed with an O-ring to provide subsonic airflow. The subsonic air flow is obtained by a series of high-pressure gas cylinders connected in parallel under the adjustment and control of a pressure reducer and a flow meter. The air flow is a normal temperature gas with a speed range of 0-300m/s.
本发明中采用乙烯燃烧加热方式获得高温燃气，并通过调整乙烯和空气的当量比以实现温度的宽范围调节，通过调整可拆卸的超声速喷管3扩张比实现速度的宽范围调节，并由此获得来流参数宽范围可调节的亚-超剪切层；这样能够更加真实的模拟实际工作过程中高温燃气与常温冲压气流之间的剪切混合作用，结合测试技术掌握亚-超剪切层发展规律及来流参数对剪切层增长率的影响特性，对于工程实际应用中提出合理适用的增强混合措施奠定基础，同时对于深入了解亚-超剪切混合流这类湍流流动问题提供实验数据支撑。In the present invention, high-temperature gas is obtained by ethylene combustion heating, and a wide range of temperature adjustment is realized by adjusting the equivalent ratio of ethylene and air, and a wide range of speed adjustment is realized by adjusting the expansion ratio of the detachable supersonic nozzle 3, and thus Obtain a sub-super-shear layer with a wide range of adjustable flow parameters; this can more realistically simulate the shear mixing between high-temperature gas and normal temperature ram airflow in the actual working process, and combine testing technology to master the sub-hypershear layer The development law and the influence characteristics of incoming flow parameters on the growth rate of the shear layer lay the foundation for proposing reasonable and applicable enhanced mixing measures in engineering practical applications, and provide experimental data for in-depth understanding of turbulent flow problems such as sub-supershear mixed flow support.
燃气发生器4中乙烯与氧气的化学反应公式为：The chemical reaction formula of ethylene and oxygen in gas generator 4 is:
由CEA燃温计算程序可知乙烯在当量比条件下燃气温度可达到2795K，能够模拟真实工作条件下的燃气温度，能够提供对流马赫数Mc>1条件下的实验条件；此外，为了能够模拟不同对流马赫数条件下的亚-超剪切层发展特性，可通过调整乙烯和空气的当量比实现对燃气温度的控制；同时可通过调整拉法尔喷管段3-3的扩张比以实现超声速气流速度的宽范围变化，进而实现高对流马赫数Mc条件下的亚超剪切层实验研究。From the CEA combustion temperature calculation program, it can be known that the gas temperature of ethylene under the condition of equivalence ratio can reach 2795K, which can simulate the gas temperature under real working conditions and can provide experimental conditions under the condition of convection Mach number Mc>1; in addition, in order to simulate different convection The development characteristics of the sub-supershear layer under the condition of Mach number can realize the control of the gas temperature by adjusting the equivalent ratio of ethylene and air; at the same time, the supersonic gas flow velocity can be realized by adjusting the expansion ratio of the Rafal nozzle section 3-3 A wide range of changes, and then realize the experimental study of the sub-supershear layer under the condition of high convective Mach number Mc.
为了实现对亚-超剪切层发展特性的研究，实验开始前首先需要确定本次的试验状态，根据实验规划的对流马赫数Mc值，确定出亚声速气流和超声速气流的来流参数压力、总温以及马赫数或速度。然后将相应设计马赫数的超声速喷管3安装到试验段腔体1内，并用定位销进行固定；然后将观测窗安装到位，并采用螺钉进行固定。此外，根据计算获得的超声速气流总温，结合CEA燃温计算程序，对乙烯控制系统和空气供应系统的流量进行调节，达到预期燃温；同时，调节低速流供应系统压力，控制亚声速气流马赫数及压力与设计状态一致。最后将测试系统安装到位，本次试验中采用纹影系统对亚超剪切层发展特性进行研究。至此，实验前准备工作已完全就绪。In order to realize the research on the development characteristics of the sub-supershear layer, it is first necessary to determine the test state before the experiment starts. According to the convective Mach number Mc value of the experimental plan, the inflow parameters of subsonic airflow and supersonic airflow are determined. Total temperature and Mach number or velocity. Then install the supersonic nozzle 3 corresponding to the designed Mach number into the cavity 1 of the test section and fix it with positioning pins; then install the observation window in place and fix it with screws. In addition, according to the total temperature of the supersonic flow obtained through calculation, combined with the CEA combustion temperature calculation program, the flow rate of the ethylene control system and the air supply system is adjusted to achieve the expected combustion temperature; at the same time, the pressure of the low-speed flow supply system is adjusted to control the subsonic flow Mach The number and pressure are consistent with the design state. Finally, the test system was installed in place. In this test, the schlieren system was used to study the development characteristics of the sub-supershear layer. So far, the preparatory work for the experiment has been fully completed.
实验过程中首先打开低速流供应系统，保证亚声速气流先进入试验段腔体1内；3s后乙烯供应系统和空气供应系统开启，分别供应乙烯和空气进入到燃气发生器4内，为乙烯充分燃烧提供均匀混合的环境，与此同时打开纹影系统对通过观测窗5进行观测；再2s后启动高能点火器，点燃乙烯，并在燃气发生器4内充分燃烧，产生的高温燃气在超声速喷管3的加速作用下实现超声速流动并进入试验段腔体1内，与亚声速气流发生剪切混合作用。8s后关闭高能点火器，3s后再关闭乙烯供应系统和空气供应系统，同时关闭纹影测试系统，最后再关闭低速流供应系统。至此，本次实验已全部完成。During the experiment, the low-velocity flow supply system was first turned on to ensure that the subsonic flow first entered the chamber 1 of the test section; 3 seconds later, the ethylene supply system and the air supply system were turned on, and ethylene and air were respectively supplied into the gas generator 4 to provide sufficient ethylene flow. Combustion provides a uniformly mixed environment, and at the same time, open the schlieren system to observe through the observation window 5; after another 2 seconds, start the high-energy igniter, ignite ethylene, and fully burn in the gas generator 4. Under the acceleration of the tube 3, the supersonic flow is realized and enters the chamber 1 of the test section, where it shears and mixes with the subsonic airflow. Turn off the high-energy igniter after 8s, turn off the ethylene supply system and the air supply system after 3s, turn off the Schlieren test system at the same time, and finally turn off the low-speed flow supply system. So far, this experiment has been completed.
表1显示为采用该实验装置对常温条件下亚-超剪切层的发展特性研究的实验工况及结果处理。其中，Dc为可压缩剪切层厚度增长率；Di为相同速度比和密度比条件下的不可压缩剪切层厚度增长率之比，Dc/Di为归一化厚度增长率由表1得出该实验装置获得的亚-超剪切层厚度增长率当量厚度增长率与理论结果基本一致，误差仅为2％。Table 1 shows the experimental conditions and result processing for the study of the development characteristics of the sub-hypershear layer under normal temperature conditions using the experimental device. Among them, Dc is the thickness growth rate of the compressible shear layer; Di is the ratio of the thickness growth rate of the incompressible shear layer under the same velocity ratio and density ratio, and Dc/Di is the normalized thickness growth rate, which is obtained from Table 1 The equivalent thickness growth rate of the sub-supershear layer thickness obtained by the experimental device is basically consistent with the theoretical result, and the error is only 2%.
表1亚-超剪切层来流条件及结果Table 1 Sub-hypershear laminar flow conditions and results
图4为表1亚、超声速气流来流条件下的纹影实验结果，其中上、下两路为亚声速气流，中心流为超声速气流，可以看到在出口位置，上层亚声速气流和超声速气流以及下层超声速气流与亚声速气流之间形成明显的剪切混合层，边界较明显，可开展亚-超剪切层沿流向增长特性的研究；此外中心超声速气流在出口出现膨胀波，经过剪切层的反射作用向下游发展，形成一系列波系结构，由图4可以发现剪切层在波系结构作用下厚度呈现非均匀增长特性，该特点可详细展开研究。Figure 4 shows the results of Schlieren experiments under the conditions of incoming subsonic and supersonic airflow in Table 1. The upper and lower paths are subsonic airflow, and the center flow is supersonic airflow. It can be seen that at the exit position, the upper layer of subsonic airflow and supersonic airflow Moreover, an obvious shear mixed layer is formed between the supersonic flow and the subsonic flow in the lower layer, and the boundary is more obvious, so the research on the growth characteristics of the sub-supershear layer along the flow direction can be carried out; The reflection of the layer develops downstream, forming a series of wave system structures. From Fig. 4, it can be found that the thickness of the shear layer shows a non-uniform growth characteristic under the action of the wave system structure. This feature can be studied in detail.
图5显示本实验状态下由纹影获得的剪切层归一化厚度增长率与理论结果之间的对比，发现误差较小，由表1可知误差为2％，满足实验要求。理论结果参见参考文献Turbulent Free Shear Layer Mixing and Combustion,P.E.Dimotakis,AIAA,1991,Chapter 5。由此确定实验装置能够满足来流参数宽范围可调的亚-超剪切层研究工作。Figure 5 shows the comparison between the normalized thickness growth rate of the shear layer obtained from schlieren and the theoretical results in this experimental state. It is found that the error is small. From Table 1, it can be seen that the error is 2%, which meets the experimental requirements. Theoretical results can be found in references Turbulent Free Shear Layer Mixing and Combustion, P.E. Dimotakis, AIAA, 1991, Chapter 5. Therefore, it is determined that the experimental device can meet the research work of the sub-hypershear layer with wide range adjustable flow parameters.
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