Effect of Radial Density Configuration on Wave Field and Energy Flow in Axially Uniform Helicon Plasma

The effect of the radial density configuration in terms of width, edge gradient and volume gradient on the wave field and energy flow in an axially uniform helicon plasma is studied in detail. A three-parameter function is employed to describe the density, covering uniform,parabolic, linear and Gaussian profiles. It finds that the fraction of power deposition near the plasma edge increases with density width and edge gradient, and decays in exponential and "bumpon-tail" profiles, respectively, away from the surface. The existence of a positive second-order derivative in the volume density configuration promotes the power deposition near the plasma core, which to our best knowledge has not been pointed out before. The transverse structures of wave field and current density remain almost the same during the variation of density width and gradient, confirming the robustness of the m=1 mode observed previously. However, the structure of the electric wave field changes significantly from a uniform density configuration, for which the coupling between the Trivelpiece-Gould(TG) mode and the helicon mode is very strong, to non-uniform ones. The energy flow in the cross section of helicon plasma is presented for the first time, and behaves sensitive to the density width and edge gradient but insensitive to the volume gradient. Interestingly, the radial distribution of power deposition resembles the radial profile of the axial component of current density, suggesting the control of the power deposition profile in the experiment by particularly designing the antenna geometry to excite a required axial current distribution.     

Dynamic Control of Defective Gap Mode Through Defect Location

A one dimensional model is developed for defective gap mode (DGM) with two types of boundary conditions:conducting mesh and conducting sleeve.For a periodically modulated system without defect,the normalized width of spectral gaps equals to the modulation factor,which is consistent with previous studies.For a periodic system with local defects introduced by the boundary conditions,it shows that the conducting-mesh-induced DGM is always well confined by spectral gaps while the conducting-sleeve-induced DGM is not.The defect location can be a useful tool to dynamically control the frequency and spatial periodicity of DGM inside spectral gaps.This controllability can be potentially applied to the interaction between gap eigenmodes and energetic particles in fusion plasmas,and optical microcavities and waveguides in photonic crystals.     

激光冲击强化K403镍基高温合金表面纳米化

针对K403镍基高温合金铸造构建易发生裂纹、腐蚀、磨损的问题,采用激光冲击强化技术对K403薄片试件进行处理,使试件表面纳米化提高材料力学性能。利用X射线衍射、SEM扫描电镜、TEM透射电镜分析了材料表面纳米晶层的形成机理。实验结果表明:激光诱导的高压等离子体冲击波可以在样品表面上形成226 nm厚的纳米晶层;从SEM和TEM结果可以看出,激光冲击强化不会改变材料表面物相。在高冲击波压力下,K403试样表面组织产生了位错和纳米级晶粒细化。     

Investigation of the interaction between NS-DBD plasma-induced vortexes and separated flow over a swept wing

The effect of nanosecond pulsed dielectric barrier discharge(NS-DBD) plasma flow separation control is closely related to the actuation frequency,because it involves the interaction between plasma-induced vortexes and separated flow.In order to study the mechanism of NS-DBD plasma flow separation control over a swept wing,especially the influence of the actuation frequency,at first,experimental studies of the actuation frequencies at 100 Hz are conducted to validate the numerical simulation meth...     

Discharge and jet characteristics of gliding arc plasma igniter driven by pressure difference

Stable combustion in an afterburner can help increase the thrust of the engine in a short time, thereby improving the maneuverability of a fighter. To improve the ignition performance of an afterburner, a twin-duct ignition platform was designed to study the performance of a gliding arc plasma igniter in close-to-real afterburner conditions. The research was carried out by a combination of experiments and simulations. The working environment of the igniter was explored through a numerical simulation. The results showed that the airflow ejected from the radiating holes formed a swirling sheath, which increased the anti-interference ability of the airflow jet. The influence of the pressure difference between the inlet and outlet of the igniter (Δp), the flow rate outside the igniter outlet (W₂), and the installation angle (α) on the single-cycle discharge energy (E) as well as the maximum arc length (L) were studied through experiments. Three stages were identified: the airflow breakdown stage, the arc evolution stage, and the arc fracture stage. E and L increased by 107.3% and 366.2%, respectively, with Δp increasing from 10 to 70 Torr. The relationship between L and Δp obtained by data fitting is L = 3 − 2.47/(1 + (Δp/25)⁴). The relationship of L at different α is L_α=0° > (L_α=45° and L_α=135°) > L_α=180° > L_α=90°. E and L decrease by 18.2% and 37.3%, respectively, when Δp = 45 Torr and W₂ is increased from 0 to 250 l min⁻¹.     

激光冲击对K403合金激光熔覆修复微观组织和性能的影响

针对激光熔覆修复K403镍基高温合金构件组织粗大和力学性能下降的问题,提出采用激光冲击强化技术对修复区进行表面强化。利用SEM观察不同区域微观组织,利用显微硬度、残余应力和高温拉伸强度测试研究其力学性能。结果表明,激光冲击强化细化试样表层晶粒;强化后,试样基体区和熔覆区表面硬度分别提高21%和8%,影响深度约0.8 mm;激光冲击在试样表层引入约610 MPa且均匀分布的残余压应力,影响深度层达1.2 mm,经保温处理后,应力释放约18%,但在表面仍残留较大的残余压应力;激光冲击提高了材料高温拉伸强度约15%,解决了激光熔覆修复K403镍基构件力学性能下降的问题。     

无保护层激光冲击对K24镍基合金力学性能的影响

激光冲击强化是一种有效提高材料疲劳强度的表面处理技术。针对K24镍基高温合金模拟叶片特点,文中提出采用无保护层激光冲击强化进行表面处理。同时采用X射线衍射、显微硬度计表征了不同参数冲击下材料截面残余应力和显微硬度变化规律,并利用高周振动疲劳试验验证其强化效果。结果表明:无保护层激光冲击强化处理后在材料表层形成一定数值的残余压应力,冲击1、3、5次后表面残余应力分别为-428、-595、-675 MPa,影响深度分别约为110、150、160 m;显微硬度冲击一次后提升了29.2%,影响深度约为60 m。采用不等应力冲击后K24镍基合金模拟叶片疲劳强度由原始试件的282 MPa提高到327 MPa,提高了16%。     

激光喷丸与渗铝复合工艺提高K417 合金力学性能研究

对渗铝、渗铝后强化、强化后渗铝的K417合金试件分别进行振动疲劳试验。试验结果表明,相对于渗铝处理,强化后渗铝试样的疲劳强度提高了50%,而渗铝后强化试样的疲劳强度提高了30%,这说明渗铝与激光喷丸强化复合工艺可以提高材料的疲劳性能,且强化后渗铝效果更好。采用X射线衍射(XRD)、扫描电子显微镜(SEM)和透射电子显微镜(TEM)分析激光喷丸强化与渗铝复合工艺顺序对材料力学性能的影响,讨论了疲劳性能的改善机理。结果表明,激光喷丸强化促进了渗铝过程,生成大量柱状晶,渗层厚度增加,渗层与基体的结合更加紧密,从而有效提升疲劳性能;而渗铝后强化主要对渗层表面进行了形变强化,疲劳性能的提升有限。     

斜激光冲击对航空发动机风扇轴弯曲疲劳性能的影响

采用激光斜入方法对航空发动机扇轴转接圆角部位进行激光冲击强化试验。分析了斜冲击机理及方法,计算优化斜激光冲击强化试验参数,对冲击前后试件的显微硬度、残余应力进行对比分析,并进行旋转了弯曲疲劳对比验证试验。其结果表明,风扇轴经过激光斜冲击强化后,表面显微硬度提高了11%,残余应力不均匀性得到改善,旋转弯曲疲劳寿命提高了160%;断口观察分析可知,激光冲击强化可以使疲劳源位置内移,降低裂纹扩展速率,从而提高试件的疲劳性能。     

无保护层激光冲击对GH3044涡轮机匣围观组织和性能的影响

针对激光冲击强化涡轮机匣部件难以贴覆吸收保护涂层的问题,提出无保护层激光冲击（LSPwC）+水砂纸磨除烧蚀层的复合工艺,研究LSPwC对GH3044合金微观组织和力学性能的影响,验证复合工艺的可行性。采用能谱仪（EDS）、扫描电子显微镜（SEM）和金相显微镜分析试样表层元素组成和微观组织,通过测试残余应力和高周疲劳寿命表征其力学性能。结果表明,LSPwC在试样表层产生约10~15 m的烧蚀层,烧蚀层内碳、氧元素富集且残余拉、压应力交替存在,烧蚀层以下晶粒和碳化物不同程度地均匀细化;相比原始试样,LSPwC对GH3044合金疲劳寿命提升不明显;水砂纸磨除烧蚀层后,试样表面残余压应力约510 MPa,影响深度层达1 mm,疲劳寿命提高到原始试样的3倍。