RESEARCH ON PARALLEL GRINDING METHOD OF NON-AXISYMMETRIC ASPHERIC LENS

In order to resolve the problems of machining non-axisymmetric aspheric lens,which is short of flexibility in mould grinding and needs high accuracy CNC machine center in globediamond wheel grinding, a new parallel grinding method that utilizes common arc diamond wheel isput forward. Base on the approach calculation of machining locus, the advantages of parallelgrinding that machines non-axisymmetric aspheric lens by 2.5-axis CNC machine center have beenobtained. The results of grinding experiment show the new method can meet the need of grinding highaccuracy non-axisymmetric aspheric lens.

THE NON-AXISYMMETRICAL DYNAMIC RESPONSE OF TRANSVERSELY ISOTROPIC SATURATED POROELASTIC MEDIA

The Blot's wave equations of transversely isotropic saturated poroelastic media excited hy non-axisymmetrical harmonic source were solved by means of Fourier expansion and Hankel transform. Then the components of total stress in porous media are expressed with the solutions of Biot's wave equations. The method of research on non-axisymmetrical dynamic response of saturated porous media is discussed, and a numerical result is presented.

Finite Element Simulation on the Spin-forming of the 3D Non-axisymmetric Thin-Walled Tubes

The roller movement trace for the 3D non-axisymmetric thin-walled tubes is a complex space curve. Besides the roller rotation caused by contact with the blank, the roller rotates around the workpiece together with the main spindle, and also moves simultaneously along the direction of the revolution radius. The method to correctly establish the finite element （FE） models of the metal spinning is based on the MSC. MARC software was introduced. The calculation formulas considering both the revolution and rotation of the roller were obtained by the mathematical deduction. The saving calculation points m should be a multiple of 4 for one revolution of the roller around the workpiece to obtain the maximum forming force for the spinning of the 3D non-axisymmetric thin-walled tubes. The simulation results conform well to the experimental ones for several spinning methods; the maximum error is less than ±15%.

Reconstruction of Emission Coefficients for a Non-axisymmetric Coupling Arc Based on MALDONADO's Method

The reconstruction of emission coefficient is a key factor for the calculation of temperature field.However,most of the researches for determining arc plasmas are based on axisymmetric sources,little has been done to study non-axisymmetric arc plasmas.In order to reveal temperatures of a non-axisymmetric coupling arc,the distribution of emission coefficients must be reconstructed in advance.In this paper,the argon atomic line intensities of the coupling arc are obtained by using the imaging system that involves a high speed camera in conjunction with a neutral and a narrow-band filter.The converted programme between emission coefficients and emitted intensities is programmed based on MALDONADO＇s method.A displaced Gaussian model is used for evaluating the validity of the converted programme.Then,the emission coefficients of a free burning arc are reconstructed by MALDONADO＇s method and an Abel inversion,respectively,and good agreement is obtained.Finally,the emission coefficient profiles of the coupling arc are achieved.The results show that the distribution of emission coefficient for the coupling arc is non-axisymmetric.The emission coefficient profile is similar to an ellipse,and the short axis of the ellipse is in the direction that the two electrodes are arranged along.The peak temperature of the coupling arc is in the middle of both electrodes.There is a strong interaction between both arcs within the coupling arc.The proposed research solves difficulties for determining asymmetric arcs and enlarges the application scope of spectroscopic techniques.

STUDY ON THE NUMERICAL SIMULATION OF MULTI-STAGE ROTARY FORGING OF A NON-AXISYMMETRIC PART AND THE CAE ANALYSIS OF THE DIE STRENGTH

Traditionally a rotary forging process is a kind of metal forming method where a conic upper die, whose axis is deviated an angle from the axis of machine, forges a billet continuously and partially to finish the whole deformation. For the rotary forging process simulation, more researches were focused on simulating the simple stage forming process with axisymmetric part geometry. Whereas in this paper, the upper die is not cone-shaped, and the billet is non-axisymmetric. So the movement of the punch is much more complicated than ever. The 3D FEM simulation models for the preforming ＆ final forming processes are set up aider carefully studying the complicated movement pattern. Deform-3D is used to simulate the material flow, and the boundary nodal resisting forces calculated by the final stage process simulation is used to analyze the final forming die strength. The CAE analysis of the die shows that the design of the final forming die is not reasonable with lower pre-stress which is easy to crack at the critical corners. An optimum die design is also provided with higher pre-stress, and verified by CAE analysis.

Thermo-electromechanical behavior of functionally graded piezoelectric hollow cylinder under non-axisymmetric loads

This paper presents an analytical solution of a thick walled cylinder composed of a functionally graded piezoelectric material （FGPM） and subjected to a uniform electric field and non-axisymmetric thermo-mechanical loads. All material properties, except Poisson＇s ratio that is assumed to be constant, obey the same power law. An exact solution for the resulting Navier equations is developed by the separation of variables and complex Fourier series. Stress and strain distributions and a displacement field through the cylinder are obtained by this technique. To examine the analytical approach, different examples are solved by this method, and the results are discussed.

BUCKLING AND POST-BUCKLING OF ANNULAR PLATES UNDER NON-AXISYMMETRIC PLANE EDGE FORCES

On the basis of both the general theory[1,2]and the finite element method[4]of perforated thin plates with large deflection,the buckling and post-buckling of annular plates under non-axisymmetric plane edge forces are studied.

Optimal Design of Non-axisymmetric Endwall with Variable-fidelity CFD Model

Non-axisymmetric endwall is numerically investigated to suppress the secondary endwall flow in a HP turbine suction surface.The endwall contour is represented by a non-uniform rational B-spline surface.Two solution spaces are designed by the rule of hypercube sampling through variation of nodal radial extension.Final most effective endwall contour is obtained through screening all available samples with surrogate-based model.Results show that non axisymmetric endwall reduces the turbulence kinetic energy of the passage vortex by 5.5%and the total pressure loss 1.6%.Local heat transfer coefficient is lowered on the afore passage endwall surface with a certain increment on the aft passage endwall.Overall averaged heat transfer coefficient is reduced.

Experimental investigation about the effect of non-axisymmetric wake impact on a low speed axial compressor

Non-axisymmetric wake impact experiments were carried out after the best exciting frequency for a low speed axial compressor had been found by axisymmetric wake impact experiments. When the number and circumferential distribution of inlet guide vanes （IGV） are logical, the wakes of non-axisymmetric IGVs can exert beneficial unsteady exciting effect on their downstream rotor flow fields and improve the compressor＇s performance. In the present paper, four non-axisymmetric wake impact plans were found working better than the axisymmetric wake impact plan. Compared with the base plan, the best non-axisymmetric plan increased the compressor＇s peak efficiency, and the total pressure rise by 1.1 and 2%, and enhanced the stall margin by 4.4%. The main reason why non-axisymmetric plans worked better than the axisymmetric plan was explained as the change of the unsteady exciting signal arising from IGV wakes. Besides the high-frequency components, the nonaxisymmetric plan generated a beneficial low-frequency square-wave exciting signal and other secondary frequency components. Compared with the axisymmetric plan, multifrequency exciting wakes arising from the non-axisymmetric plans are easier to get coupling relation with complex vortices such as clearance vortices, passage vortices and shedding vortices.

INSTABILITY OF HAGEN-POISEUILLE FLOW FOR NON-AXISYMMETRIC MODE

An investigation is described for instability problem of flow through a pipe of circular cross section. As a disturbance motion, we consider a general non-axisym-metric mode. An associated amplitude or modulation equation has been derived for this disturbance motion. This equation belongs to a diffusion type.The coefficient of it can be negative while Reynolds number increases, because of the complex interaction between molecular diffusion and convection. The negative diffusivity, when it occurs, causes a concentration and focussing of energy within decaying slugs, acting as a role of reversing natural decays.

AN EFFICIENT FINITE-DIFFERENCE ALGORITHM FOR COMPUTING AXISYMMETRIC TRANSONIC NACELLE FLOW FIELDS

A finite difference method for computing the axisymmetric, transonic flows over a nacelle is presented in this paper. By use of the conservative full-potential equation, body-fitted grid, and the exact boundary conditions, a new AF scheme is constructed according to the criterion of optimum convergence. The proposed scheme has been applied to transonic nacelle flow problems. Computation for several nacelles shows the rapid convergence of this scheme and excellent agreement with the experimental results.

Design and Numerical Investigation to Predict the FlowPattern of Non-axisymmetric Convergent Nozzle:AComponent of Turboexpander

Current work proposes a novel design methodology using curve-fitting approach for a non-axisymmetric airfoil convergent nozzle used in small-sized cryogenic turboexpander.The curves used for designing the nozzle are based on a combination of fifth and third order curve at upper and lower surface respectively.Four different turbulence model such as k-ε,SST,BSL and SSG Reynolds stress turbulence model is used to visualize and compare the fluid flow characteristics and thermal behaviors at various cross-sections.It is interesting to observe that the Mach number obtained at the outlet of the nozzle is highest and temperature drop is maximum for SSG model under similar boundary conditions.It is also observed that the designed nozzle with curve fitting approach is appropriate for impulse type turbine with a small amount of reaction.The key feature of this implementation is to obtain subsonic velocity at the nozzle exit and reduce the irreversible losses through the nozzle,which can affect the performance of a turboexpander.

湍流风况下风电机组机舱近尾流的数值模拟研究

水平轴风电机组机舱风速是机组控制的主要信号参数。机舱风速受风电机组来流湍流与风电机组近尾流影响,变化复杂,对风电机组的优化控制有重要的影响。本文采用计算流体力学(CFD)方法,对湍流风况下风电机组机舱近尾流进行了详细分析。对比研究了稳态均匀风况和湍流风况下的近尾流的结构、机舱速度分布及其对风电机组总体性能的影响。研究发现,风电机组总体性能随湍流风况波动也呈现多尺度波动特征。湍流风况下,经过滤波后的机舱风速的时间序列和来流风速的时间序列体现出很强的相关性。对于湍流风况和稳态均匀风况,叶片/风轮旋转对风电机组机舱风速波动的影响最大。湍流风况会增加风电机组机舱风速的波动频率,增大波动的幅值,削弱风轮旋转对尾流和机舱风速的影响。湍流风况使得机舱周围的流动结构更复杂。稳态均匀风况与湍流风况下叶片吸力面叶根位置处都发生了分离流动,湍流强度增大了叶根位置处的流动分离。

基于风机式激光测风雷达的风机功率特性曲线测试方法

通过风机式激光测风雷达(NML)测试风机功率特性曲线(PPM),对比分析风机式NML和测风塔的结果差异,评估两种方法在发电量计算中的不确定性。结果表明,风机式NML与测风塔的风速测量一致,相关系数可达0.994,拟合的斜率和截距分别为0.979和0.084;风机式NML的测试数据在功率特性曲线的散点分布图中更集中;发电量评估结果表明,NML比测风塔高估发电量1.73%。不同风向扇区的研究结果表明,测风塔在不同风向下处于风机的不同方位,NML随风机机舱的偏航始终测量风机正前方风速,与风向保持一致,因此散点更为集中。风机式NML对PPM测试的不确定度更低,对风机叶轮上平均风速更具有代表性,具有一定的研究意义与实际应用价值。

内涵喷管关键几何参数对巡航工况超大涵道比短舱气动性能的影响研究

为降低燃油消耗、污染物排放和气动噪声,民用涡扇发动机朝着超大涵道比(Ultra-High Bypass Ratio,UHBPR)方向发展。发动机尺寸增大导致的短舱阻力和质量增大会减小甚至抵消涵道比增大带来的收益。为进一步提升UHBPR短舱的气动性能,建立了评价巡航工况进气道、外罩和排气系统整体气动性能的参数,基于数值模拟研究了内涵喷管关键几何参数对短舱气动性能的影响规律,并分析了影响机理。结果表明:核心后罩收缩比和内涵喷管长径比对发动机安装推力损失的影响较大,最大变化量分别为10.77%和13.40%。核心后罩收缩比取较小值,内涵喷管长径比取值在0.9附近有利于减小发动机的安装推力损失。流场分析表明:核心后罩收缩比、内涵喷管长径比和出口角变化会影响外涵喷管出口下游的激波前马赫数、激波位置、强度以及其与附面层的相互干扰,也会影响尾锥附近的压力分布,还会影响内涵喷管出口马赫数,从而显著影响核心后罩推力、尾锥推力和内涵喷管推力。巡航工况下外涵喷管超临界而内涵喷管亚临界,内涵喷管几何参数变化几乎不会影响外涵喷管的性能,但会显著影响内涵喷管的流量和推力。内涵喷管流通能力的变化会影响发动机的流量,进而影响冲压阻力、附加阻力和外罩阻力。

涡桨发动机舱引射通风冷却数值研究

以涡轮螺旋桨飞机的排气系统/短舱为研究对象,构建了机翼/机身/螺旋桨一体的发动机短舱仿真物理模型,采用多参考坐标系(MRF)法对螺旋桨滑流进行了模拟,并探究了不同排气管长度下发动机舱内的流动和换热情况。结果表明:在研究参数范围内,随排气管混合管段长度增加,在无滑流状态下,排气管中间环缝的引射流量上升18.3%,排气管末端环缝引射流量上升0.27 kg/s;在有滑流状态下,中间环缝引射流量保持在0.174 kg/s左右基本不变,末端环缝引射流量相对增加了35.8%,混合管段长度变化对末端环缝引射影响较大。排气管外管温度分布具有不对称性,滑流引入后,表面平均温度下降15 K,降幅4%;混合管段壁面温度受引射出口回流区和高温排气影响略有升高。

先进树脂基复合材料在商用航空发动机中的应用

为研究先进树脂基复合材料在商用航空发动机中的应用情况和发展趋势,分析国外航空发动机中先进树脂基复合材料的应用进展,重点介绍风扇段和短舱上复合材料的应用部件、材料体系及成型工艺。结果表明,应用先进树脂基复合材料制造航空发动机部件,可显著减轻发动机重量、提高推重比、降低燃油损耗、减少噪声,带来突出的性能优势和经济效益。说明通过开展材料体系研发、结构优化设计及低成本、自动化成型技术研究,提高复合材料应用水平,是商用航空发动机中先进复合材料的发展趋势。

Effect of Incoming Vortex on Secondary Flows in Turbine Cascades with Planar and Non-Axisymmetric Endwall

Non-Axisymmetric Endwall Profiling(NAEP) is commonly utilized in turbines to eliminate secondary flows.Nevertheless,most of the NAEP methods consider a single-blade row environment without incorporating the effect of the stage environment.This paper aims to investigate the influence mechanism of the incoming vortex on the endwall secondary flow structures of NAEP in a highly loaded turbine cascade.To model the incoming vortex in a stage environment,this study considers a half-delta wing as the vortex generator at the upstream of the turbine cascade.The NAEP is then carried out for a highly loaded turbine cascade with an in-house numerical optimization design platform subject to no incoming vortex.Numerical simulation is also carried out under the influence of the incoming vortex for the turbine cascades with both planar and non-axisymmetric endwall.This paper furthers investigated the pitchwise effect of the incoming vortex on the near endwall secondary flow.The results indicate that the NAEP effectively improves the endwall secondary flow of the turbine cascade,where the total pressure loss coefficient and the secondary kinetic energy(SKE) are reduced by 7.3%,and 45.7%,respectively.It is further seen that with the incoming vortex,the NAEP achieves a considerable control effect on the endwall secondary flow of the turbine cascade.With incoming vortex,the NAEP can still achieve considerable control effect on the endwall secondary flow of the turbine cascade;the averaged reductions of loss coefficient and SKE are 7.8% and 14.2%,respectively.Under some pitchwise locations,incoming vortex can suppress the convection of cross-passage flow toward the suction corner greatly and reduce the loss coefficient of the baseline cascade.The incoming vortex at 4/7 pitch impinged right at the blade leading edge,leading to the generation of low-momentum fluid,which increased the size and the strength of the horseshoe vortex.Under all the pitchwise locations,NAEP can suppress the secondary vortices,e.g.,the passage vortex and the counter vortex,considerably.

Approximate contact solutions for non-axisymmetric homogeneous and power-law graded elastic bodies:A practical tool for design engineers and tribologists

In two recent papers,approximate solutions for compact non-axisymmetric contact problems of homogeneous and power-law graded elastic bodies have been suggested,which provide explicit analytical relations for the force–approach relation,the size and the shape of the contact area,as well as for the pressure distribution therein.These solutions were derived for profiles,which only slightly deviate from the axisymmetric shape.In the present paper,they undergo an extensive testing and validation by comparison of solutions with a great variety of profile shapes with numerical solutions obtained by the fast Fourier transform(FFT)-assisted boundary element method(BEM).Examples are given with quite significant deviations from axial symmetry and show surprisingly good agreement with numerical solutions.

短舱管路接头耐火试验数值仿真预测

防耐火性能是航空发动机零部件满足适航要求的基本指标之一,在短舱火区内输送可燃液体的管路是其中的关键考核部件。为预测短舱管路耐火试验结果,评价管路接头火焰耐受性能,提出了开展标准火焰燃烧仿真获取第三类边界条件,通过管路流热耦合换热获取传热稳定后的流体域及固体域温度场,作为热边界条件进行结构变形分析考察管路接头接触状态的数值分析方法。通过直管火焰冲击试验及管路接头耐火试验对相关结果进行了验证。结果表明:出口管路温度预测结果误差小于3%,管路接头泄漏预测结果与试验结果一致。