涡轮叶片持久寿命预测中气膜冷却孔的影响

从涡轮叶片典型部位取材并设计加工试件,进行持久寿命试验.通过观察比较试验结果,发现相同名义应力下气膜冷却孔将使试件的持久寿命大为降低.为了验证这一结论,采用有限元数值模拟的方法对该试件的持久拉伸过程进行模拟,同时考虑材料的正交各向异性以及高温条件下的蠕变规律,求得应力集中最大节点的应力值,进而算出其持久寿命,并与标准试件进行比较.     

涡轮叶片蠕变全过程的修正Graham模型的参数识别

针对定向凝固镍基合金制造的航空发动机涡轮叶片,从涡轮叶片典型部位取材并设计制造模拟试件,在980℃下不同应力水平下进行单轴蠕变试验。对试验数据进行了唯象学的数学描述,并对ANSYS有限元分析软件中Graham蠕变模型进行了修正,使修正后的模型能够比较精确地描述单轴蠕变的全过程。并应用修正Graham模型对试验过程进行数值模拟,研究表明ANSYS有限元模拟蠕变的结果和试验数据吻合较好。这说明了修正Graham模型模拟单轴蠕变过程的合理性,该模型在一定程度上为ANSYS在金属材料蠕变分析方面的二次开发提供了理论基础。     

短碳纤维局部增强混凝土疲劳性能实验研究

对局部增强短碳纤维混凝土进行三点弯曲疲劳试验,发现相同试件在不同应力水平下的疲劳寿命符合两参数威布尔分布,并由此建立考虑失效概率和高低应力比的局部增强短碳纤维混凝土双对数疲劳方程.在工程应用中可以根据实际情况确定失效概率,运用线性插值得到相应回归系数,求得双对数疲劳方程.通过比较相同应力水平下短碳纤维局部增强试件和素混凝土试件的试验结果,发现仅对混凝土进行低掺量的局部增强就可以成倍地提高混凝土的疲劳寿命.上述结果对混凝土路面工程或一些有特殊要求工程的设计有参考意义.     

单向双筋板结构件共振疲劳试验及分析

航空航天领域广泛存在着振动疲劳问题,严重危及飞行器结构的安全可靠性。本文首先设计了激振器直接作用于试件的力激励振动疲劳试验系统,并提出了跟踪结构共振频率的频带激励共振疲劳寿命测试方法;而后利用试件进行了频带激励下的定应变共振或定载荷共振结构振动疲劳试验;最后针对试验结果分析与讨论了可能影响结构振动疲劳寿命的各种因素。结论表明,试验结构件的边界条件、初始条件以及结构动力学特性等都可能是影响振动疲劳寿命的关键因素。频带激励共振疲劳试验方法为振动疲劳寿命曲线的测试积累了经验。     

浅析光弹性法在增压器叶片强度分析上的应用

为了研究某型号涡轮增压器的涡轮叶片工作时受载荷情况,采用模型技术制造的环氧树脂叶片来取代真实叶片,并安装到涡轮上.采用合适的加载方式,使得叶片能模拟工作时的状态.环氧树脂的特性是可以将载荷以条纹的形式固化在其中.当载荷卸去后,获得的光弹性模型可切片以进行光弹性应力分析,获得模型内部应力,从而可方便的对涡轮叶片的强度进行全面研究.     

局部应变法在机翼主梁试件疲劳寿命估算中的应用

本文用有限元法对歼击机机翼主梁试件进行了弹塑性分析,并用局部应变法对主梁试件的裂纹形成寿命进行了估算.在估算中比较了不同的损伤计算方法,考虑了缺口表面双轴应力和平均应力的影响.寿命估算结果和25级程序加载及6级程序加载的试验进行了比较.结果是吻合的,计算寿命与试验寿命相差在系数为3数的分散带内.     

层合板结构元件动态S-N曲线的测定方法

在确定了飞机壁板结构的动力学特性后,为预计其声疲劳寿命,传统的方法必须采用飞机壁板结构的典型结构件并通过高声强行波管试验获得这种结构的声疲劳S-N曲线.为减少试验时间和费用,利用振动台获取典型层合复合材料结构元件的振动S-N曲线以代替声疲劳S-N曲线.根据典型复合材料的飞机蒙皮壁板结构形式,利用加筋复合材料层合板设计了用于振动试验的两种结构形式的梁元件.为获得准确的试验结果,试件模拟了实际的连接形式,并用于得到εrms-N振动试验中.所有试件的试验采用相同的振动激励谱形,并在不同的随机振动量级进行试验,利用最小二乘法拟合得到的εrms-N数据.这种测试方法可用于飞机结构抗声疲劳设计的实践中.     

利用红外热像技术快速预测材料的S-N曲线

研究材料疲劳一般采用试验的方法,但试验周期长, 所需试验试件和费用多,一直以来都是材料疲劳试验难以克服的困难,人们一直在探寻能快速得到材料疲劳性能的方法.本文在前人研究的基础上,采用红外热像技术,确定了材料的疲劳极限,并在"同种试件疲劳破坏消耗的塑性功不变"的假设下,通过建立塑性温升、热耗散、塑性功之间的关系给出了试件疲劳寿命的计算公式.由此经过简单的试验,理论上用一根试件,试验几个小时就可以快速确定材料的疲劳寿命,给出材料的S-N曲线.     

军机DFR方法在钛合金电子束横焊缝结构上的应用验证

为在飞机结构设计阶段进行钛合金焊接件的疲劳强度评估,采用军机DFR方法进行了TC4-DT钛合金电子束横焊缝试件的疲劳分析,并对其进行了试验验证。首先,进行了TC4-DT钛合金电子束横焊缝试件的DFR基准值测试,得到DFR基准值为470MPa;其次,为了验证军机DFR方法分析结果的可靠性,进行了TC4-DT钛合金电子束横焊缝试件在随机谱下的成组疲劳试验,采用断口判读技术确定裂纹萌生寿命,得到了随机谱下的试验中值寿命;最后,利用测得的DFR基准值,采用军机DFR方法评估得到随机谱下成组试验的试验件中值寿命以及对应试验中值寿命的应力水平。对比分析结果表明:分析寿命比试验寿命低10%,分析的应力水平比试验应力水平低3%。此结果表明军机DFR方法略偏保守,与DFR方法计算结果偏保守的特征一致,也验证了军机DFR方法在TC4-DT钛合金电子束焊接件上应用的可行性。     

TC4钛合金超高周次轴向振动疲劳试验

应用基于压电超声疲劳试验技术开发的20kHz轴向振动疲劳试验系统,完成了室温下TC4钛合金超高周疲劳试验,获得了TC4合金在107～109周次范围内的轴向振动疲劳寿命曲线(S-N曲线);运用C.Paris推导公式预测了TC4合金材料的寿命,得到各应力水平下破坏率为50％、95％、99％的安全寿命.结果表明:在疲劳循环大于107周次时,试件仍会发生疲劳断裂,疲劳强度随循环次数的增加而下降,并不存在明显的疲劳极限.TC4合金的S-N曲线在107～109周次的范围内呈连续下降型.在轴向振动超高周疲劳试验中,试件的裂纹扩展寿命只占其在50％破坏率下疲劳安全寿命的一小部分,其疲劳寿命主要由试件的裂纹萌生寿命决定.     

基于仿生设计的风力发电机叶片力学性能的实验研究

根据风力机的基本理论和相似理论设计了一个翼型为SG6050，半径为1m的小型风力机叶片。运用结构仿生学原理，对所设计的风力机叶片进行了仿生物中轴铺层设计。通过模态实验与应变实验，比较了传统设计与仿生设计两种不同风力机叶片的力学性能。模态实验结果表明，基于仿生设计的叶片的前六阶固有频率比传统叶片的前六阶固有频率减少约8％；两种叶片的固有频率均满足设计要求；仿生设计的叶片几乎不会改变叶片的动态特性。而应变实验表明，仿生设计的叶片在各种工况下的应变均大于传统的叶片约10％～20％。新设计的叶片具有较好的柔性，有效减小了叶片的应力，提高了叶片的疲劳寿命。     

透平转子的可靠性设计

介绍透平转子的可靠性设计方法。该方法以传统的转子强度和振动的设计方法为基础,把透平转子的静应力、材料静强度、应力幅、尺寸系数、表面加工系数、应力集中系数、材料疲劳极限、热疲劳累积损伤程度、材料低周疲劳程度、蠕变寿命、固有频率、激振力频率、不平衡响应等处理为随机变量,使用机械概率设计法确定转子设计的可靠度。文中给出了透平转子静强度、疲劳强度、热疲劳、蠕变寿命、避开弯曲共振、避开扭转共振和限制不平稳响     

Application of bamboo laminates in large-scale wind turbine blade design

From the viewpoint of material and structure in the design of bamboo blades of large-scale wind turbine, a series of mechanical property tests of bamboo laminates as the major enhancement materials for blades are presented. The basic mechanical characteristics needed in the design of bamboo blades are briefly introduced. Based on these data, the aerodynamic-structural integrated design of a 1.5 MW wind turbine bamboo blade relying on a conventional platform of upwind, variable speed, variable pitch, and doubly-fed generator is carried out. The process of the structural layer design of bamboo blades is documented in detail. The structural strength and fatigue life of the designed wind turbine blades are certified. The technical issues raised from the design are discussed. Key problems and direction of the future study are also summarized.     

基于近似技术的涡轮叶片气动优化设计

根据五次多项式方法进行三维涡轮叶片的参数化建模,采用N-S方程和湍流模型进行三维流场分析计算,以K-S函数法作为优化方法,利用近似技术加速循环优化速度,建立了一种基于近似技术的涡轮叶片的气动优化方法。将气动效率和总压比作为目标函数,对涡轮叶片进行多目标气动优化、形状优化。算例表明本文提出的涡轮叶片优化设计方法是有效的。     

接触状态对叶根轮槽应力分布影响的研究

汽轮机叶片叶根、轮槽连接区域常因加工误差及磨损等原因导致接触状态的改变,从而改变整个区域应力分布并大大降低汽轮机的使用寿命。本文运用数字光弹性技术实验测试了长叶片叶根、轮槽在不同接触状态下的应力分布情况,同时结合有限元进行了仿真计算。结果表明,叶根、轮槽对称接触时,全部齿同时接触的应力集中系数最小且分布较均匀;而当部分接触齿产生间隙时,接触状态发生显著变化,应力集中系数明显增大;尤其是当左右齿非对称接触时,最大应力集中系数明显增大且应力分布不均匀。本文研究可为叶根、轮槽的优化设计、加工以及叶片的装配、维护提供实验依据。     

Supercritical and subcritical dynamic flow-induced instabilities of a small-scale wind turbine blade placed in uniform flow

There is a growing interest in extracting more power per turbine by increasing the rotor size in offshore wind turbines. As a result, the turbine blades will become longer and therefore more flexible, and a flexible blade is susceptible to flow-induced instabilities. In order to design and build stable large wind turbine blades, the onset of possible flow-induced instabilities should be considered in the design process. Currently, there is a lack of experimental work on flow-induced instabilities of wind turbine blades. In the present study, a series of experiments were conducted and flow-induced instabilities were observed in wind turbine blades. A small-scale flexible blade based on the NREL 5 MW reference wind turbine blade was built using three-dimensional printing technique. The blade was placed in the test section of a wind tunnel and was subjected to uniform oncoming flow, representing the case of a parked wind turbine blade. The blade׳s tip displacement was measured using a non-contacting displacement measurement device as the oncoming wind speed was increased. At a critical wind speed, the blade became unstable and experienced limit cycle oscillations. The amplitude of these oscillations increased with increasing wind speed. Both supercritical and subcritical dynamic instabilities were observed. The instabilities were observed at different angles of attack and for blades both with and without a geometric twist. It was found that the blade twist had a significant influence on the observed instability: a blade without a twist experienced a strong subcritical instability.     

Design optimization of axial flow hydraulic turbine runner: Part I—an improved Q3D inverse method

With the aim of constructing a comprehensive design optimization procedure of axial flow hydraulic turbine, an improved quasi‐three‐dimensional inverse method has been proposed from the viewpoint of system and a set of rotational flow governing equations as well as a blade geometry design equation has been derived. The computation domain is firstly taken from the inlet of guide vane to the far outlet of runner blade in the inverse method and flows in different regions are solved simultaneously. So the influence of wicket gate parameters on the runner blade design can be considered and the difficulty to define the flow condition at the runner blade inlet is surmounted. As a pre‐computation of initial blade design on S2m surface is newly adopted, the iteration of S1 and S2m surfaces has been reduced greatly and the convergence of inverse computation has been improved. The present model has been applied to the inverse computation of a Kaplan turbine runner. Experimental results and the direct flow analysis have proved the validation of inverse computation. Numerical investigations show that a proper enlargement of guide vane distribution diameter is advantageous to improve the performance of axial hydraulic turbine runner. Copyright © 2002 John Wiley & Sons, Ltd.     

Creep,plasticity, and fatigue of single crystal superalloy

Single crystal components in gas turbine engines are subject to such extreme temperatures and stresses that life prediction becomes highly inaccurate resulting in components that can only be shown to meet their requirements through experience. Reliable life prediction methodologies are required both for design and life management. In order to address this issue we have developed a thermo-viscoplastic constitutive model for single crystal materials. Our incremental large strain formulation additively decomposes the inelastic strain rate into components along the octahedral and cubic slip planes. We have developed a crystallographic-based creep constitutive model able to predict sigmoidal creep behavior of Ni base superalloys. Inelastic shear rate along each slip system is expressed as a sum of a time dependent creep component and a rate independent plastic component. We develop a new robust, computationally efficient rate-independent crystal plasticity approach and combined it with creep flow rule calibrated for Ni-based superalloys. The transient variation of each of the inelastic components includes a back stress for kinematic hardening and latent hardening parameters to account for the stress evolution with inelastic strain as well as the evolution for dislocation densities. The complete formulation accurately predicts both monotonic and cyclic tests at different crystallographic orientations for constant and variable temperature conditions (low cycle fatigue (LCF) and thermo-mechanical fatigue (TMF) tests). Based on the test and modeling results we formulate a new life prediction criterion suitable for both LCF and TMF conditions.     

基于Schmitz理论的风叶气动设计研究

应用Schmitz理论进行叶片气动设计,考虑了风力机叶片的气动损失,用Schmitz理论推导出风力机叶片的基本设计参数的计算公式,并考虑了风力机在启动和空载时风力机的实际工作点偏离了设计点,对叶片的气动性能参数进行了修正。通过对200kW风力机的算例表明:随着叶片半径的增大,入流角逐渐减小;叶片弦长先增大后减小,修正后得到的风力机在非设计点处的推力、驱动力矩、功率与实际风力机的特性规律相符。     

Modeling Creep and Continuous Fracture Process Zones in Spatial Prismatic Bodies

The semianalytic finite-element method is used to develop a method for solving problems of creep and continuous fracture of complex spatial bodies. The method allows modeling the variation of the stress-strain state during creep, accompanying accumulation of dispersed microdamages, and development of macroscopic effects—continuous fracture process zones. The growth of a continuous fracture process zone is modeled. A criterion is formulated for determination of the applicability limits of continuum damage mechanics. The method is exemplified by the problem of deformation and continuous fracture of a gas turbine blade __________ Translated from Prikladnaya Mekhanika, Vol. 41, No. 9, pp. 70–86, September 2005.