军车发动机低压涡轮叶片裂纹失效检测系统设计

针对传统的军车发动机检测系统对于低压涡轮叶片裂纹失效检测的实时性和准确性较低的问题,设计了一款新的军车发动机低压涡轮叶片裂纹失效检测系统;该系统主要由叶片频率检测部分和叶片裂纹实验部分构成;硬件部分主要包括NI USB-9233、PCB加速度传感器、MA-600功放器、PYD-1型电涡流急诊疲劳试验器、以及PCB力锤等构成;软件部分主要针对叶片裂纹检测界面进行了设计,主要设计了检测系统的主界面、检测通道、检测信号模块和信号波形显示模块;最后进行实验,实验中对叶片上的20个测试点进行锤击,在进行通道参数设置的过程中,需要设置通道1作为力通道,通道2作为叶片裂纹信号响应通道;实验结果表明文中算法对叶片裂纹深度0.2 mm~2 mm的发动机低压涡轮叶片检测准确率达到98%,比传统算法提高32%,取得了令人满意的效果。     

进口温度不均匀对气冷涡轮叶片传热的影响

本文对带有复合冷却结构的航空燃机高压涡轮导向叶片进行了气热耦合数值模拟研究,分析了温度径向分布不均匀和存在"热斑"涡轮进口条件下对气冷涡轮叶片传热的影响,研究发现进口温度径向不均匀分布在涡轮叶片径向中上部形成相对集中的带状高温区域,并使下游气膜冷却效果降低,热斑的存在进一步加剧对叶片局部区域的热冲击,复合冷却结构能够比较有效地降低由于进口温度不均匀所形成叶片表面局部高热区域的热负荷。     

斜入射SH波厚壁管道内壁裂纹检测方法研究

厚壁管道常被用于军事装备及其他流程工业中，长期使用后内壁会产生较多微裂纹，成为影响构件安全运行的重大隐患。为此，本文针对厚壁管道内壁裂纹难以检测的问题，提出基于斜入射SH(Shear Horizontal)波的厚壁管道检测方法，对厚壁管道内壁不同深度的裂纹进行检测。本文首先对斜入射SH波的激励原理进行分析，建立声场模型优选激励频率，研究斜入射SH波与厚壁管道内壁裂纹径向深度的作用规律，并通过实验对仿真结果进行验证。研究结果表明，斜入射SH波对该型管道最佳检测频率为1MHz；随着裂纹径向深度增加，缺陷回波幅值呈现曲折型上升；斜入射SH波可有效对厚壁管道内壁轴向长8mm，径向深1mm和周向宽1mm的微裂纹进行检测，验证了斜入射SH波厚壁管道内壁裂纹检测方法的科学性和可行性。     

顶爆和拱腰侧爆同时作用下锚固洞室的动态响应

基于相似模型试验,采用显式非线性动力分析程序LS-DYNA3D研究了地下锚固洞室在拱顶和拱腰侧两处集中装药爆源同时爆炸作用下应力波传播规律、裂纹形成机理以及洞壁围岩位移分布特征。通过对比分析顶爆试验和计算模型的压应力时程曲线,发现模拟与试验结果吻合,且符合应力波的传播规律,表明数值模拟结果可靠。爆源爆炸后,应力波以圆形向周围岩体传播,两应力波相遇处压应力强度明显大于周围岩体;当应力波传到自由面时,会反射形成拉伸波,在地表下方和洞室上方发生“层裂”现象,在拱顶和拱腰侧爆源中间沿洞室径向有裂纹延伸,由于拉伸波的叠加,在爆源下方出现“八”字形的锥形裂纹面。锚杆能够起到加固岩体的作用,锚固洞室比毛洞裂纹分布少,毛洞迎爆侧裂纹主要为横向裂纹,而锚固洞室则为径向劈裂和横向裂纹。两爆源中点洞室径向处的洞壁围岩位移峰值最大,极易产生破坏。     

周界固定带裂纹薄圆板的振动基频

在将裂纹板挠度表示为正交多项式的基础上，用分区技术的瑞利一里兹方法求解了含不同长度径向裂纹和弧向裂纹的周界固定圆板的振动基频。实验上用小球撞击法测定了裂纹圆板的辐射声场频谱，并得出了谱的基频。此外用有限元法对裂纹板作了理论计算。三项结果基本符合。探究了裂纹长度对圆板基频的影响规律。     

掠动叶对微型轴流风扇气动-声学性能的影响研究

轴向掠是叶片的径向成型方法之一.本文基于Fluent软件分别对具有前10°、后掠10°和径向0°动叶的三种风扇模型进行了定常流场和非定常流场的数值模拟,然后基于FW-H积分完成了风扇流动噪声的远场辐射计算,研究动叶的轴向掠对小尺寸轴流风扇气动与声学性能的影响.结果表明,前掠叶片和后掠叶片使风扇的全压在大流量工作区域低于0°径向风扇,内效率也略有降低.在气动声学性能方面,研究结果表明前掠不利于本文所研究的微型轴流风扇气动噪声的抑制,但后掠动叶降低了风扇的噪声,相比径向风扇,后掠风扇的远场噪声总声压级约下降1. dB.     

汽轮机小长径比静叶片的优化径向积叠

应用粘性流动数值计算对叶轮机械叶片进行设计，能够使设计者对几种不同设计方案进行分析以满足设计要求，并获得最佳设计方案．本文采用三维N．S方程组和Baldwin-Lomax湍流模型，对一个小长径比的汽轮机导叶进行三维粘性流场数值模拟．计算结果表明，采用合适的周向弯曲（优化径向积叠）同样可以提高短叶片的效率．本计算方法可用来分析和研究叶片径向积叠形式对径向和周向流量平均绝热效率的影响，以获得较优的积叠形式．     

掠效应对高负荷跨音转子性能的影响

本文对一高负荷跨音转子采用掠技术进行了改型设计,并通过数值模拟对原型以及前、后掠转子分别进行了流场分析。结果发现掠叶片效率和压比与原型叶片相差不大,但是前掠叶型的失速裕度得到了大幅提高。同时前掠叶型的堵塞流量比原始叶型增大,而后掠叶型却明显减小。叶片采用掠之后一方面前缘位置变化所引起的径向压力输运改变了入口来流条件,另一方面气动掠还直接影响到了叶片吸力面附面层内低能流体的径向输运以及在叶尖区域的集聚,从而使流场内部的激波强度及相对位置明显变化,并最终导致叶片不同叶高载荷分布规律的改变。     

叶片的周向弯曲与弦向弯曲及其数值分析

六十年代提出的静叶片的倾斜或弯曲方法是以透平轴的平行线为转动轴将叶片转动（构成倾斜叶片）或沿叶高弯曲（构成弯曲叶片）。本文提出将转动轴在Ｓ１平面旋转到弦向，然后倾斜或弯曲叶片，称这种叶片为弦向倾斜或弯曲叶片。应用欧拉方程和高精度ＴＶＤ格式对不同弯曲方法的叶片的数值分析表明弦向弯曲叶片控制径向二次流的能力大于周向弯曲叶片。     

进口热斑径向作用位置对无导叶对转涡轮高压级温度场的影响

为了探究无导叶对转涡轮进口热斑径向作用位置的变化对其高压级温度场的影响,运用CFD方法对某无导叶对转涡轮模型级的流场进行了三维非定常多叶片排的数值模拟.结果表明,热斑流体在高压导叶中未发生周向和展向迁移;进口热斑径向作用位置的差异直接影响到热斑流体通过涡轮叶片时的温度耗散度;进口热斑径向作用位置的变化对高压动叶中控制热斑迁移的冷热气流掺混效应、通道二次流和浮力三种因素的作用效果产生了一定程度的影响.     

涡轮叶顶冷却布置对叶顶传热冷却性能的影响

本文采用数值模拟的方法,对比分析了1+1/2对转涡轮四种不同的叶顶冷却布置方案对叶顶传热、冷却性能以及气动特性的影响。四种布置方案分别是:靠近压力面垂直叶顶方向、靠近压力面且与叶顶有30°出射角、中弧线位置垂直叶顶方向、中弧线位置有30°出射角。研究表明,气膜孔沿压力面布置与气膜孔沿中弧线布置相比可以降低叶顶传热系数;由于气膜孔倾斜布置气膜射流动量降低,且削弱了肾形涡的影响,气膜的侧向覆盖范围增大。因此气膜孔靠近压力面布置可以提高气膜冷却效率;气膜孔靠近压力面且有30°出射角比垂直布置叶顶热负荷减少2.7%。另外,气膜孔靠近压力面布置可以降低主流的泄漏流量,有利于减小泄漏损失和提高涡轮效率。     

Application of local indentations for film cooling of gas turbine blade leading edge

The paper presents results of computer simulation of the film cooling on the turbine blade leading edge model where the air coolant is supplied through radial holes and row of cylindrical inclined holes placed inside hemispherical dimples or trench. The blowing factor was varied from 0.5 to 2.0. The model size and key initial parameters for simulation were taken as for a real blade of a high-pressure high-performance gas turbine. Simulation was performed using commercial software code ANSYS CFX. The simulation results were compared with reference variant (no dimples or trench) both for the leading edge area and for the flat plate downstream of the leading edge.     

弯扭静子叶片的环形叶栅试验

弯扭静子叶片的环形叶栅试验徐文远，于清，杨弘，王仲奇（哈尔滨工业大学动力工程系哈尔滨１５０００１）关键词：弯扭叶片，环形叶栅，试验随着弯扭叶片理论的发展，它在国内外叶轮机械中的应用日益广泛。在国外，弯扭叶片已应用于新一代航空发动机中，如Ｖ２５００、Ｐ...     

Three-dimensional analysis of blade force and sound generation for an annular cascade in distorted flows

An unsteady lifting-surface theory for a rotating subsonic annular cascade has been developed to predict the unsteady blade forces and the acoustic power generation caused by interaction of blades with inlet distortions or wakes. Disturbance pressure and velocity fields induced by the rotor blades with fluctuating blade force are expressed in terms of the blade force distribution and kernel functions. The spanwise distribution of the blade force is given as a sum of blade force modes, and the kernel functions are resolved into the corresponding modal components. The sound pressure and intensity are expressed as a sum of acoustic modes, the modal components of which are given in terms of the blade force mode components.Numerical computations have been conducted .for interaction with the external disturbance flows that are sinusoidal in the circumferential direction, but possess a phase skewing in the radial direction. Correlations among the acoustic modes, the blade force modes and the flow patterns of the external disturbance have been investigated. When the predominant acoustic mode is subresonant, the blade force amplitude is reduced by the three-dimensional effect, which is lessened as the frequency increases. At deeply superresonant states, however, the three-dimensional effect upon the spanwise average of the blade force amplitude is small. The generated sound power is effectively reduced by increasing the radial non-uniformity of the external disturbance.     

Computation of leading edge film cooling from a CONSOLE geometry (CONverging Slot hOLE)

The aim of this study is to investigate the effect of mass flow rate on film cooling effectiveness and heat transfer over a gas turbine rotor blade with three staggered rows of shower-head holes which are inclined at 30° to the spanwise direction, and are normal to the streamwise direction on the blade. To improve film cooling effectiveness, the standard cylindrical holes, located on the leading edge region, are replaced with the converging slot holes (console). The ANSYS CFX has been used for this computational simulation. The turbulence is approximated by a k-ε model. Detailed film effectiveness distributions are presented for different mass flow rate. The numerical results are compared with experimental data.     

Influence of blade compactness and segmentation strategy on tonal noise prediction of an automotive engine cooling fan

This paper discusses a blade segmentation strategy for tonal noise computation of automotive engine cooling fans. The noise sources are extracted from an Unsteady Reynolds-averaged Naviers Stocks simulation (URANS), and propagated into the far field using dipole noise equations derived from Ffowcs-Williams acoustic analogy. On the aerodynamic side, a mesh independence study is carried out. On the acoustic side, three levels of acoustic meshes are compared to evaluate the assumption of blade compactness and its influence on the final results. The blade is modeled with one dipole at the lowest level of the acoustic mesh: it is assumed acoustically compact regardless of the frequency. At the finest level, the blade is meshed with 26,726 dipoles which are the surface elements of the CFD mesh. An intermediate level of mesh is also studied where the blade is cut into three acoustically compact strips. A comparison is also established between two approaches for summing the contributions of the dipoles in the cases of the intermediate and fine meshes. The first approach is to neglect the axial, tangential and radial phase lags between the dipoles, and assume uncorrelated sources. The second approach takes into account the phase lags between the dipoles due to the blade’s geometry. It is based on the equations derived by Hanson Parzych [4]. The results are additionally compared to values extracted from experiments carried out in an anechoic chamber.     

Detection of cracks at rivet holes using guided waves

Guided Lamb waves can be used for a fast inspection of large areas, e.g. the detection of cracks at rivet holes in the fuselage of airplanes. When the guided wave hits a discontinuity like a hole, a typical scattered displacement field is obtained. A change of the scattered field indicates the development of a crack. In the experiments, the first anti-symmetric mode A0 of Lamb waves in plates is excited selectively by means of a piezoelectric transducer. The used frequency range is below the cut-off frequencies of higher wave modes. The scattered field around undamaged and damaged holes is measured on a grid around the hole with a heterodyne laser interferometer. Two types of damage are introduced: a notch cut with a very fine saw blade, and a fatigue grown crack. A significant change in the scattered field due to the defect is seen. Good agreement of the experimental results with theoretical calculations is obtained. The wave propagation is studied using Mindlin's theory of plates. The scattered field is calculated analytically and using finite difference methods (FDMs).     

Effect of a rough surface on the aerodynamic characteristics of a two-bladed wind-powered engine with cylindrical blades

We have reported the results of experiments on determining the drag coefficient and the thrust coefficient of a two-bladed wind-powered engine based on the Magnus effect with rotating rough cylinders in the range of air flow velocity of 4–10 m/s (Re = 26800–90000) for a constant rotation number of a cylindrical blade about its own axis. The results show that an increase in the Reynolds number reduces the drag coefficient and the thrust coefficient. The extent of the influence of the relative roughness on the aerodynamic characteristics of the two-bladed wind-powered engine has been experimentally established.     

发动机叶尖间隙影像测量系统的设计

 发动机转子叶片叶尖到开半机匣内壁径向距离是衡量发动机质量是否合格的一个重要指标,其值的大小对发动机的高效安全运行至关重要。利用立体视觉原理、自动聚焦技术和边缘检测算法,设计了一套发动机装配过程中叶尖间隙静态测量装置。该测量装置实现了对发动机叶尖间隙的非接触测量,且操作简单,测量精度高。实验结果表明该套装置测量精度达到20 μm。     

叶轮顶部间隙对向心透平总体性能影响的研究

对微型燃机向心透平叶轮顶部间隙流动在级环境下进行了全三维粘性数值模拟．研究结果表明:顶部间隙小于 2％时,间隙每增加1％,级效率降低1．5％,而级通流能力有所降低;径向与轴向间隙变化对级性能影响有很大差别, 径向间隙增加对级效率降低的影响是轴向间隙增加的8．3倍,径向间隙增加使通流能力增强的程度是轴向间隙增加使通流能力减弱的4．2倍。此外,将间隙流场与文献报道试验结果进行了比较,差别主要在工作轮顶部区域。