Investigation on in-flight particle velocity in supersonic plasma spraying

In-flight particle velocity and flux distribution were measured using CCD thermal spray monitor system during supersonic plasma spray processing with nano-structured Al_2O_3-TiO_2 feed stocks. According to the results of particle flux measurement, the largest radian of the divergent particle stream is about 0.2. Within the measuring range, top speed of in-flight particles reached 800m/s. Particle acceleration was accomplished within 4cm down stream of the nozzle. Average particle velocity (about 450m/s) exceeded local sound speed (340m/s) even at a mean standoff distance of 17cm. With increasing mean standoff distance, average velocity of in-flight particle decreased according to a parabolic rule approximately. Image diagnosis showed that the result of in-flight particle velocity measurement is credible.

Numerical Analysis of Interaction Between Single-Pulse Laser-Induced Plasma and Bow Shock in a Supersonic Flow

The interaction of laser-induced plasma and bow shock over a blunt body is inves- tigated numerically in an M∞ =6.5 supersonic flow. A ray-tracing method is used for simulating the process of laser focusing. The gas located at the focused zone is ionized and broken down and transformed into plasma. In a supersonic flow the plasma moves downstream and begins to interact with the bow shock when it approaches the surface of the blunt body. The parameters of flowfield and blunt body surface are changed due to the interaction. By analyzing phenomena occurring in the complex unsteady flowfield during the interaction in detail, we can better under- stand the change of pressure on the blunt body surface and the mechanism of drag reduction by laser energy deposition. The results show that the bow shock is changed into an oblique shock due to the interaction of the laser-induced low-density zone with the bow shock, so the wave drag of the blunt body is reduced.

Preparation and properties of supersonic atmospheric plasma sprayed TiB2−SiC coating

With the TiB2−SiC powders after spray granulation and vacuum calcination as raw materials,the TiB2−SiC coating was prepared by supersonic atmospheric plasma spraying(SAPS).The effects of spraying power and spraying distance on the properties of the TiB2−SiC coating were investigated and the fabrication processing of SAPS was optimized.The results show that the sprayed powders after calcination have a uniform particle size distribution,good sphericity and enhanced fluidity.The coating prepared by the calcined powders has a dense structure and high deposition efficiency.When the calcined TiB2−SiC powders are used and the spraying power is 95 kW and the spraying distance is 150 mm during supersonic plasma spraying,the obtained TiB2−SiC coating behaves the best comprehensive performance with the porosity,microhardness,bonding strength and resistivity equal to 5.6%,3.57 GPa,18.3 MPa and 10.8 mΩ·cm,respectively.

Characterization of functionally graded ZrO_2 thermal barrier coatings sprayed by supersonic plasma spray with dual powder feed ports

The functionally graded thermal barrier coatings （FG-TBCs） with 80%ZrO2-13%CeO2-7%Y2O3 （C-YSZ）/NiCoCrAlY were prepared using a recently developed supersonic plasma spraying（S-PS） with dual powder feed ports system. The thermal shock experiment of FG-TBCs specimens was carried out by means of the automatic thermal cycle device, in which the samples were heated to 1200℃ by oxygen-acetylene flame jet then water-quenched to ambient temperature. The temperature—time curves of specimens and photographs can be watched on-line and recorded by a computer during the test. The results show that the totally 1mm-thick FG-TBCs have excellent thermal shock resistance due to the fact that the coatings have no any peeling-off after 200 thermal cycles. The microstructures and morphologies of FG-TBCs were characterized and analyzed by SEM.

Combustion characteristics of supersonic strut-cavity combustor under plasma jet-assisted combustion

Plasma jet has been widely used in supersonic combustor as an effective ignition and combustion assisted method,but currently it is mostly combined with the traditional wall fuel injection method,while the application combined with the central fuel injection method is less.In order to expand the combustion range,the plasma jet was introduced into a strut-cavity combustor with an alternating-wedge.The effects of total pressure of strut fuel injection,total pressure of cavity fuel injection,total pressure of plasma jet injection and plasma jet media on the combustion characteristics were analyzed in supersonic flow by numerical calculations in a three-dimensional domain.The combustion field structure,wall pressure distribution,combustion efficiency and distribution of H2O at the exit of the combustor with different injection conditions were analyzed.The results show that the combustion efficiency decreases with the increase of the strut fuel injection total pressure.However,the combustion area downstream increases when the total pressure of the strut fuel injection increases within the proper range.The combustion range is expanded and the combustion efficiency is improved when the cavity fuel injection total pressure is increased within the range of 0.5−2.0 MPa,but a sharp drop in combustion efficiency can be found due to limited fuel mixing when the total injection pressure of the cavity fuel is excessively increased.With the increased total injection pressure of the plasma jet,the height of the cavity shear layer is raised and the equivalence ratio of the gas mixture in the cavity is improved.When the total pressure of the plasma jet is 1.25 MPa,the combustion efficiency reaches a maximum of 82.1%.The combustion-assisted effect of different plasma jet media is significantly different.When the medium of the plasma jet is O2,the combustion-assisted effect on the combustor is most significant.

Time Characterization of High Density Gas Jet from a Pulsed Supersonic Nozzle via Laser Produced Plasma

A high-density gas jet supersonic nozzle is reported in this paper. The jitter and actuation time of the nozzle is determined by the pin discharge and laser spark radiation respectively. The jitter time of the nozzle is within 10μs with the backing pressure as high as 25 bar. With a nanosecond laser pulse focused on the gas jet about 1 mm below the nozzle, the actuation time is calculated to be about 15 ms by detecting the laser produced spark radiation, which reveals the existence of the gas jet and the relative gas density evolving with time. Consequently the gas density is estimated to be well above 10^19 cm^-3, compared with theoretical simulations from the nozzle parameters.

Interaction of supersonic molecular beam with low-temperature plasma

The interaction between the supersonic molecular beam(SMB)and the low-temperature plasma is a critical issue for the diagnosis and fueling in the Tokamak device.In this work,the interaction process between the argon SMB and the argon plasma is studied by a high-speed camera based on the Linear Experimental Advanced Device(LEAD)in Southwestern Institute of Physics,China.It is found that the high-density SMB can extinct the plasma temporarily and change the distribution of the plasma density significantly,while the low-density SMB can hardly affect the distribution of plasma density.This can be used as an effective diagnostic technique to study the evolution of plasma density in the interaction between the SMB and plasma.Moreover,the related simulation based on this experiment is carried out to better understand the evolution of electron density and ion density in the interaction.The simulation results can be used to analyze and explain the experimental results well.

Diagnosis for the Interaction of Supersonic Molecular Beam with Plasma

Supersonic Molecular Beam Injection (SMBI) is a new fuelling method for Tokamaks and has recently been improved to enhance the flux of the beam and to make a survey of the cluster effect within the beam. There are a series of new phenomena, which implicate the interaction of the beam (including clusters) with the toroidal plasma of HL-1M Tokamak. The Ha signals from the edge show a regular variation around the torus. Around the injection port, the edge Hα signals are positive rectangular wave, which is consistent with that of the injection beam pulses. The edge electron temperature, measured with movable Langmuir probes, decreases by an order of magnitude and the density increases by an order of magnitude. Hα emission at the beam injection port, measured with CCD camera at an angle of 13.4 degrees to the SMBI line, shows many separate peaks within the contour plot. These peaks may show the strong emission produced by the interaction of the hydrogen clusters with the plasma. Hydrogen clusters may be produced in the beam according to the empirical scaling (Hagena) law of clustering onset, * = .here d is the nozzle diameter in μm, Po the stagnation pressure in mbar, To the source temperature in K, and k is a constant related to the gas species. If * > 100, clusters will be formed. In present experiment * is about 127.

Simulation of Supersonic Molecular Beam Fueling on HL-1M Tokamak

The supersonic molecular beam (SMB) ablation and penetration processes in the HL-1M tokamak experiments are studied. The cluster formation and dissolution, SMB adiabatic expansion, shielding and cooling effect are all taken into account. An optimized numerical model is applied in the analysis and shown to be in good agreement with the experimental observations. The possibility of fueling large tokamak plasmas with SMB injection is explored.

Experimental study on nanosecond pulsed pin-to-plate discharge in supersonic air flow

Development of magnetohydrodynamic acceleration technology is expected to improve wind tunnel simulation capability and testing capability.The underlying premise is to produce uniform and stable plasma in supersonic air flow,and gas discharge is an effective way to achieve this.A nanosecond pulsed discharge experimental system under supersonic conditions was established,and a pin-to-plate nanosecond pulsed discharge experiment in Mach 2 air flow was performed to verify that the proposed method produced uniform and stable plasma under supersonic conditions.The results show that the discharge under supersonic conditions was stable overall,but uniformity was not as good as that under static conditions.Increasing the number of pins improved discharge uniformity,but reduced discharge intensity and hence plasma density.Under multi-pin conditions at 1000Hz,the discharge was almost completely corona discharge,with the main current component being the displacement current,which was smaller than that under static conditions.

煤化工装备中关键阀内件的失效行为及表面强化技术

针对煤化工装备中关键阀内件材质的劣化问题,采用宏/微观多尺度分析方法研究在不同服役工况下阀内件的失效风险因素,并提出阀内件表面的强化策略。结果表明:气-固稀相介质下阀内件失效行为是气-固两相冲蚀导致材料流失;气-固浓相介质下阀内件失效是气相和固相煤粉冲蚀、颗粒及黏着磨损等多种因素耦合,冲蚀所占比例较大;液-固介质下失效机理是腐蚀、冲蚀、磨损等多种因素耦合。基于阀内件失效风险,并结合材质的强-塑-韧适配性原理,提出了多功能一体化涂层的防控策略。通过超音速等离子喷涂技术在基体表面制备Ni Cr-Cr_(3)C_(2)金属-陶瓷涂层,涂层结构致密,硬度提高至HV_(0.3)1013。相比不锈钢材质,涂层硬度提高近5倍。拉伸测试表明,Ni Cr-Cr_(3)C_(2)涂层与基体结合强度达到67 MPa,且耐冲击性能优异,实现了材质表面的强化。

碳化钨复合涂层的制备技术及其耐磨耐蚀性的研究进展

碳化钨涂层具有化学稳定性高、硬度大和耐磨性好等特点,常用于金属表面涂层的制备。从碳化钨涂层的不同制备原理出发,综述了超声速火焰喷涂、等离子喷涂、等离子熔覆、激光熔覆和真空熔覆等碳化钨涂层制备技术的国内外研究进展,分析了不同制备技术下涂层的耐磨性和耐蚀性,探讨了涂层制备技术存在的问题和未来的研究方向。

镁合金基体超音速等离子喷涂Al-Al_(2)O_(3)复合涂层组织与耐腐蚀性能研究

镁合金的耐腐蚀性能差,在工程应用中往往因腐蚀而发生失效,通过表面工程技术对镁合金进行表面改性或防护,是工程应用中采用的重要手段。本工作采用超音速等离子喷涂(Supersonic plasma spray,SPS)工艺在AZ61镁合金表面制备Al-Al_(2)O_(3)复合涂层,其中Al_(2)O_(3)的质量分数分别为30%、50%和70%(下文简称AA30、AA50、AA70)。研究了Al_(2)O_(3)含量对Al-Al_(2)O_(3)复合涂层微观组织、孔隙率、电化学性能以及盐雾耐腐蚀性能的影响。结果表明,涂层的表面呈现熔滴铺展堆叠形成的浪花状形貌,粉末熔化充分,涂层内部结合紧密,各涂层均由Al、α-Al_(2)O_(3)和γ-Al_(2)O_(3)三种物相组成。AA70涂层的孔隙率较AA30和AA50明显升高,达到了6.71%;电化学极化试验研究表明,各涂层比AZ61镁合金基体表现出更高的电极电位和较低的自腐蚀电流密度,AZ61镁合金基体自腐蚀电流密度为5.144 mA·m^(-2),而AA30、AA50和AA70的自腐蚀电流密度分别为2.950 mA·m^(-2)、3.084 mA·m^(-2)和2.496 mA·m^(-2),三种涂层相比母材AZ61表现出较低的电化学腐蚀速率。电化学阻抗测试结果表明,三种涂层的R ct达到了AZ61镁合金基体的两倍左右,显示出较低的阳极溶解活性。在盐雾试验中,AZ61镁合金基体产生大量的腐蚀产物和龟裂纹;涂层AA30和AA50由于腐蚀产物的积累产生了大量裂纹,在涂层与基体的界面处发生了电偶腐蚀,最终随着基体表面的腐蚀,涂层产生了剥落;涂层AA70腐蚀程度最小,表现出最佳的抗腐蚀性能。

Experimental investigation for temperature and emissivity by flame emission spectrum in a cavity of rocket based combined cycle combustor chamber

Flame temperature and spectral emissivity were the important parameters characterizing the sufficient degree of fuel combustion and the particle radiative characteristics in the Rocket Based Combined Cycle(RBCC)combustor.To investigate the combustion characteristics of the complex supersonic flame in the RBCC combustor,a new radiation thermometry combined with Levenberg-Marquardt(LM)algorithm and the least squares method was proposed to measure the temperature,emissivity and spectral radiative properties based on the flame emission spectrum.In-situ measurements of the flame temperature,emissivity and spectral radiative properties were carried out in the RBCC direct-connected test bench with laser-induced plasma combustion enhancement(LIPCE)and without LIPCE.The flame average temperatures at fuel global equivalence ratio(a)of 1.0b and 0.6 with LIPCE were 4.51%and 2.08%higher than those without LIPCE.The flame combustion oscillation of kerosene tended to be stable in the recirculation zone of cavity with the thermal and chemical effects of laser induced plasma.The differences of flame temperature at a=1.0b and 0.6 were 503 K and 523 K with LIPCE,which were 20.07%and42.64%lower than those without LIPCE.The flame emissivity with methane assisted ignition was 80.46%lower than that without methane assisted ignition,due to the carbon-hydrogen ratio of kerosene was higher than that of methane.The spectral emissivities at 600 nm with LIPCE were 1.25%,22.2%,and 4.22%lower than those without LIPCE at a=1.0a(with methane assisted ignition),1.0b(without methane assisted ignition)and 0.6.The effect of concentration in the emissivity was removed by normalization to analyze the flame radiative properties in the RBCC combustor chamber.The maximum differences of flame normalized emissivity were 50.91%without LIPCE and 27.53%with LIPCE.The flame radiative properties were stabilized under the thermal and chemical effects of laser induced plasma at a=0.6.

超音速等离子喷涂Al-35Si-4Fe涂层制备工艺优化及摩擦学性能

为改善铝硅合金的摩擦学性能,以YL113铝硅合金为基体,喷涂功率、总气流量和喷涂距离为试验因素,显微硬度和孔隙率为考核指标,采用三因素三水平的正交试验法得到了超音速等离子喷涂Al-35Si-4Fe涂层的最佳制备工艺;研究了此工艺下涂层的摩擦学性能。结果表明:在喷涂功率65 kW,总气流量110 L min,喷涂距离95 mm时,涂层质量最佳,Al-35Si-4Fe涂层的显微硬度达到(465±24.4)HV_(0.2),涂层孔隙率为1.3%。试验条件下,Al-35Si-4Fe涂层的磨损机制以疲劳磨损为主,磨粒磨损为辅。Al-35Si-4Fe涂层的磨损率为1.88×10^(-4) mm^(3)(N·m),摩擦因数为0.37。优化后的Al-35Si-4Fe涂层能有效保护内部YL113铝硅合金,延长其使用寿命,并应对更加复杂的工况。

Experimental Investigation on Airfoil Shock Control by Plasma Aerodynamic Actuation

An experimental investigation on airfoil （NACA64-215） shock control is performed by plasma aerodynamic actuation in a supersonic tunnel （Ma -= 2）. The results of schlieren and pressure measurement show that when plasma aerodynamic actuation is applied, the position moves forward and the intensity of shock at the head of the airfoil weakens. With the increase in actuating voltage, the total pressure measured at the head of the airfoil increases, which means that the shock intensity decreases and the control effect increases. The best actuation effect is caused by upwind-direction actuation with a magnetic field, and then downwind-direction actuation with a magnetic field, while the control effect of aerodynamic actuation without a magnetic field is the most inconspicuous. The mean intensity of the normal shock at the head of the airfoil is relatively decreased by 16.33%, and the normal shock intensity is relatively reduced by 27.5% when 1000 V actuating voltage and upwind-direction actuation are applied with a magnetic field. This paper theoretically analyzes the Joule heating effect generated by DC discharge and the Lorentz force effect caused by the magnetic field. The discharge characteristics are compared for all kinds of actuation conditions to reveal the mechanism of shock control by plasma aerodynamic actuation.

Experimental Investigation on the Plasma Torch Used for Scramjet Ignition Enhancement

A high frequency arc discharge plasma torch was specially designed for ignition enhancement in scramjet combustor. At first, the process of plasma injection into quiescent air was investigated experimentally through CCD camera and schlieren technology. Then, the energy property characterization of active particle distribution was measured by emission spectrometry. Several kinds of working gas under different injection pressures were compared. Finally, the typical supersonic flow-field structure with plasma cross-injection was obtained. The results show that plasma jet energy is concentrated near the jet axis, which has the maximum attenuation in the downstream as far as 2 cm from the outlet. The working gas and injection pressure have great effect on emission spectrometry and the process of jet expansion. The case with N2 under higher injection pressure shows better performance of energy exchanging process when comparing with air and argon. From the emission spectroscopy, we can see that plasma from nitrogen consists of nitrogen and oxygen atom mainly, whose intensity decreases with increasing distance from the nozzle, while it increases with the increase of pressure. When plasma was vertically injected into supersonic flow-field, bow shock wave and mixing layer structure were formed with thicken mixing layer, which helps enhance the mixing process between active particle and incoming air.

不同工艺参数下超音速等离子喷涂层界面结合行为及其分形特性

随着研究不断深入,分形几何可以用来描述涂层的表面形貌和复杂性,分形维数可实现形貌结构的定性描述向定量表征转变。为研究超音速等离子喷涂层界面结合行为与其分形维数之间的关系,采用对比试验研究喷涂距离、喷涂电流等工艺参数对涂层结合界面形貌和结合强度的影响,并引入分形理论对界面结合行为进行定量表征,进而探究结合界面形貌、结合强度、分形维数三者的对应关系。结果表明:相比于喷涂电流,喷涂距离对分形维数的影响更为显著。当喷涂距离为80 mm和100 mm时,随着喷涂电流从400 A增大到500 A,分形维数呈先减小后增大趋势,最小为1.1150;当喷涂距离为120 mm时,粒子在等离子焰流中的飞行时间增长,随电流增大,涂层界面分形维数则先增大后减小。界面分形维数与涂层结合强度之间存在着正相关的对应关系。当分形维数在一定范围内呈增大趋势时,涂层/基体结合界面处孔隙减少、结合强度增大。因此,涂层/基体结合行为的分形特性研究对评价涂层质量具有重要意义。

纳米和微米ZrB_(2)-SiC粉末对涂层抗烧蚀性能的影响

310S耐热不锈钢因具有抗氧化、耐腐蚀等优良性能的同时,亦具有良好的耐高温性能,在工业中得到较为广泛的应用。但在高温高速焰流冲刷等极端环境下的氧化失效限制了其实际应用。表面涂层技术是提升基体耐高温、耐烧蚀能力的有效手段。选用纳米团聚粉末和常规微米ZrB_(2)-SiC粉末,利用超音速等离子喷涂在310S耐热不锈钢基体上制备以CoCrAlYTa为粘结层、ZrB_(2)-SiC为陶瓷层的复合涂层,对两种涂层分别进行了氧-乙炔高温烧蚀试验。采用XRD、EDS、SEM分析涂层组织结构。结果表明:纳米团聚粉末(n-ZS)涂层表面孔隙和微裂纹较微米商用粉末(m-ZS)涂层大幅减少,涂层更为致密;m-ZS涂层的耐烧蚀时长达600 s,较n-ZS涂层耐烧蚀时长提升12倍左右。

Mullite Oxidation Resistant Coating for SiC-coated Carbon/Carbon Composites by Supersonic Plasma Spraying

To improve the oxidation resistance of carbon/carbon （C/C） composites, mullite coating was prepared on the surface of SiC-coated C/C composites by supersonic plasma spraying. Phases and microstructures of mullite coating were characterized by X-ray diffraction （XRD） and scanning electron microscopy （SEM）. The coating primarily consists of a single phase of mullite （3AI203-2SIO2）. The SEM results show that mullite coating was continuous and well bonded with the SiC inner layer without penetrating crack. Mullite coating exhibited good oxidation resistance, After 98.5 h oxidation at 1773 K and 9 thermal shock cycles between 1773 K and room temperature, the weight loss of the coated C/C composites was only 2.57%.