含呼吸式裂纹的整体叶盘的固有特性

基于ANSYS软件创建了含呼吸式裂纹整体叶盘的有限元模型,在裂纹处通过创建接触对来模拟裂纹的呼吸效应;然后,对整体叶盘和含呼吸裂纹的整体叶盘进行了模态分析,得到了其固有频率及振型,并通过对完好的整体叶盘进行模态试验验证了有限元模型的有效性;最后,对比分析不同长度、不同位置的裂纹对整体叶盘静频、动频、频率转向及振型转换的影响,为避免共振和监测整体叶盘裂纹故障提供参考依据。

电解辅助磁力研磨整体叶盘试验研究

针对航空发动机整体叶盘结构复杂和材料难以加工的特性,在磁力研磨技术的基础上引入电解作用作为辅助手段。通过电解作用产生易于处理的钝化膜,然后再引入磁力研磨加工技术,加快了对叶盘表面纹理的去除,同时使表面加工质量更加均匀。通过3D超景深电镜观测叶盘表面形貌,结果显示:经复合研磨20 min,叶盘表面纹理基本去除,表面更加细密、均匀。表面粗糙度值R_(a)由1.5μm降至0.4μm。

砂布页轮柔性抛光表面微观形貌建模与预测

柔性抛光技术广泛应用于航空发动机整体叶盘叶片的精密加工。系统深入研究柔性抛光过程,了解抛光加工表面微观形貌生成的内涵,成为柔性抛光加工技术的重要研究内容之一。以砂布页轮为柔性磨具,通过空间几何坐标变换建立了砂布页轮表面磨粒的空间运动学模型及磨粒-工件几何学干涉模型,并研究了砂布页轮柔性变形对工件表面磨粒运动轨迹的影响。基于磨具表面形貌模型,利用MATLAB软件进行砂布页轮柔性抛光表面微观形貌生成过程仿真,并得到不同工艺参数下工件表面三维形貌及其影响规律,抛光实验结果验证了该仿真算法的正确性和有效性。

压气机整体叶盘修复再制造的研究进展

压气机整体叶盘的应用,是高性能发动机的典型技术之一,但整体叶盘接触包含各种固体物的高速气流,频繁出现多种不同形式的结构损伤和性能衰退,严重制约发动机高性能、高可靠和长寿命运行。基于深度维修的整体叶盘再制造技术,是解决上述难题的有效途径。本文针对压气机整体叶盘修复再制造过程中的共性基础问题,总结国内外整体叶盘修复再制造的历史沿革和技术发展,根据整体叶盘几何结构损伤形式和服役损伤形式,从损伤可修复评估与设计、熔焊修复技术、压力焊修复技术、钎焊及激光增材修复及技术、表面加工及优/强化技术等五个部分进行系统阐述,并探讨整体叶盘修复再制造中评估设计、技术发展和深度修复等重要问题,旨在推动整体叶盘再制造技术快速发展和应用。

面向全型面精加工的整体叶盘铣磨组合加工技术研究

整体叶盘由多个叶片呈圆周阵列布置在轮毂上,由于叶身型面为弱刚性零件,精加工时刀具磨损、颤振及让刀变形较为严重,影响了加工质量的进一步提高。提出一种面向全型面精加工的整体叶盘铣磨组合加工工艺,叶片型面采用磨削加工工艺,叶根、流道区域采用铣削加工工艺,通过控制磨削与铣削刀轨重叠区域的接刀误差实现叶盘全型面加工。试验结果表明,铣磨组合加工工艺表现出较好的加工质量,接刀误差控制在0.01 mm以内,轮廓误差小于0.04 mm,并通过加工试验验证了多主轴阵列加工的可行性,在保证加工质量的同时可大幅度提升加工效率。

基于反向分段加工的整体叶盘变形控制技术研究

针对航空发动机整体叶盘精加工过程中易产生颤振和加工变形的难题,开展了整体叶盘变形控制技术研究,设计出一种基于反向分段加工的光固化辅助支撑夹具。首先依据工件分段刚性化原则说明反向分段加工对于减少工件加工变形的有效性。其次设计了包括压紧块、仿形块、固定板在内的三段式叶盘加工辅助支撑夹具,通过光敏树脂填充仿形块与叶片之间的缝隙,为整体叶盘的加工提供良好支撑。并对夹具支撑性能进行了测试,验证了夹具的可靠性。最后,采用叶盘模拟件进行了反向分段加工验证试验,结果表明,所设计的夹具减小了叶盘截面线加工误差,最大让刀变形量由0.1 mm下降到了0.05 mm,验证了光固化辅助夹具对整体叶盘加工具有较好的变形控制作用。

复杂型腔电解加工成形规律分析及试验研究

电解加工适用于包含复杂型腔的难加工材料整体构件的高效加工,但复杂型腔电解加工时加工余量的分布需进一步深入研究。针对阴极曲面上各点法向与进给方向夹角不同时工件成形过程存在差异的问题,对阴极建立特定夹角处加工间隙的微分方程,模拟不同法向与进给方向夹角,并采用规则形状阴极开展直流电解加工和脉冲振动耦合电解加工工艺对比试验,以优选合适的微分方程模拟复杂型腔在上述加工模式下的成形过程。研究成果已应用于闭式整体叶盘叶间流道的电解加工。

斜向进给电解加工叶盘通道流场分析与试验

为使叶栅通道粗加工余量更加均匀,针对某型整体叶盘,采用阴极斜向进给的加工方式设计了电解液流动方案,建立阴极在不同进给量下的三维流场模型,采用COMSOL Multiphysics软件计算不同加工阶段下电解液流场的速度和压力,并进行电解加工工艺试验。结果表明:加工过程稳定,无火花、短路现象,叶盘轮毂表面光洁,表面粗糙度为Ra=0.278μm,验证了流场设计的合理性以及工装夹具的可靠性。

压气机叶片加工误差离散性控制研究进展综述

航空发动机压气机整体叶盘通常设计为旋转周期对称结构。然而,实际加工中同一级整体叶盘上不同叶片之间以及单个叶片自身存在的加工误差离散性会对流场参数产生不利影响。因此,提高整体叶盘叶片加工误差一致性成为普遍关注的难题。综述了近年来针对同级叶盘不同叶片加工误差离散性对气动性能影响规律的相关研究,以及加工过程强时变特性下误差离散度控制的相关成果。就误差离散性现象及产生原因、对性能影响规律及加工误差离散度控制方法这3个方面展开论述。最后展望了未来误差离散度加工控制方法发展趋势,为未来相关研究工作提供参考。

基于公差约束的叶片表面振纹修复技术

以某大型风扇钛合金整体叶盘叶片为载体,对其叶片在铣削加工时由刀具磨损、崩刃、振动带来的振纹问题开展基于公差约束的叶片表面振纹修复方法研究,在此基础上通过提取振纹边界,编制基于振纹位置的四重截面线检测程序、基于公差约束的在机测量截面线双向偏置、基于偏置曲线的振纹加工表面重构、振纹位置切削程序重新计算和补偿加工的方式,提出大型风扇钛合金整体叶盘叶片振纹的铣削加工修复解决方案,并进行加工验证。结果表明:在零件实际加工中,该技术在修复由崩刃导致的叶片加工振纹、避免由于加工振纹等导致叶盘报废的问题、保证零件的加工精度以及改善加工质量等方面有明显效果。

基于特征的整体叶盘加工参数优化及质量控制技术研究

针对航空发动机大型风扇钛合金整体叶盘零件加工过程中出现的让刀、振动、变形等加工问题,开展了基于特征的整体叶盘加工参数优化及质量控制方法研究。通过提取叶盘的叶片、流道、辐板等加工特征,结合叶盘轮廓铣、插铣等常用加工策略,提出针对特征弱刚性受力方向切削力控制的参数优化解决方案,并进行加工验证。结果表明,基于特征的整体叶盘加工参数优化及质量控制方法对缩短数控程序加工时间、降低最大切削力以及满足尺寸精度要求等方面有明显效果。

基于热流固的热障涂层整体叶盘振动特性研究

为了研究复杂载荷对整体叶盘振动特性的影响,基于热流固耦合方法对热障涂层整体叶盘振动特性进行研究。简化整体叶盘模型,对叶片表面涂敷热障涂层并建立整体叶盘的流场模型;在Fluent中采用热流固耦合方法对整体叶盘的表面进行气动载荷和温度载荷的模拟;最后,采用预应力模态分析法分别对不同工况下整体叶盘的振动特性进行分析。结果表明:考虑离心载荷对整体叶盘的固有频率影响最大,温度的影响最小;对比不同工况下,考虑温度载荷对整体叶盘的共振点个数无影响,气动载荷增加整体叶盘的共振点个数。

Machining the Integral Impeller and Blisk of Aero-Engines:A Review of Surface Finishing and Strengthening Technologies

The integral impeller and blisk of an aero-engine are high performance parts with complex structure and made of difficult-to-cut materials. The blade surfaces of the integral impeller and blisk are functional surfaces for power transmission, and their surface integrity has signif- icant effects on the aerodynamic efficiency and service life of an aero-engine. Thus, it is indispensable to finish and strengthen the blades before use. This paper presents a comprehensive literature review of studies on finishing and strengthening technologies for the impeller and blisk of aero-engines. The review includes independent and inte- grated finishing and strengthening technologies and dis- cusses advanced rotational abrasive flow machining with back-pressure used for finishing the integral impeller and blisk. A brief assessment of future research problems and directions is also presented.

Application of Improved Hybrid Interface Substructural Component Modal Synthesis Method in Vibration Characteristics of Mistuned Blisk

The large and complex structures are divided into hundreds of thousands or millions degrees of freedom（DOF） when they are calculated which will spend a lot of time and the efficiency will be extremely low. The classical component modal synthesis method （CMSM） are used extensively, but for many structures in the engineering of high-rise buildings, aerospace systemic engineerings, marine oil platforms etc, a large amount of calculation is still needed. An improved hybrid interface substructural component modal synthesis method（HISCMSM） is proposed. The parametric model of the mistuned blisk is built by the improved HISCMSM. The double coordinating conditions of the displacement and the force are introduced to ensure the computational accuracy. Compared with the overall structure finite element model method（FEMM）, the computational time is shortened by23.86%–31.56%and the modal deviation is 0.002%–0.157% which meets the requirement of the computational accuracy. It is faster 4.46%–10.57% than the classical HISCMSM. So the improved HISCMSM is better than the classical HISCMSM and the overall structure FEMM. Meanwhile, the frequency and the modal shape are researched, considering the factors including rotational speed, gas temperature and geometry size. The strong localization phenomenon of the modal shape’s the maximum displacement and the maximum stress is observed in the second frequency band and it is the most sensitive in the frequency veering. But the localization phenomenon is relatively weak in 1st and the 3d frequency band. The localization of the modal shape is more serious under the condition of the geometric dimensioning mistuned. An improved HISCMSM is proposed, the computational efficiency of the mistuned blisk can be increased observably by this method.

A special CAD/CAM software for electro-discharge machining of shrouded turbine blisks

In this paper, a special-purpose CAD/CAM software package, BliskCad/Cam, based on a commercial CAD/CAM software Unigraphics is developed to reduce difficulties in CNC-EDM of the shrouded turbine blisks. The software package consists of five modules such as electrode design, path searching, and machining simulation module. Functions of BliskCad/Cam include parametrical reconstruction of 3-D model of the blisk, intelligent design of complex shaped electrode, automatic generation of NC codes, search of interference-free tool path for multi-axis NC-EDM and machining simulation, etc. Experimental verification is conducted by using BliskCad/Cam and the results show that it satisfies the requirements, and can realize precision machining and reduce accessorial time remarkably.

3D FEM analysis of welding residual stress and deformation of aero-engine blisk

Aero-engine blisk welded by electron beam welding（EBW） method is a complicated structure. Fixtures were used to control the deformation of blisk during its manufacturing process. Finite element method was utilized to study the evolution of the welding residual stress and deformation of this structure. In which an attenuation function was applied to the double ellipsoid heat source model based on the characteristic of EBW, and the effects of fixtures on the welding residual stresses and deforamtion were also reserached. The simulation results showed that the temperature contour of weld cross section vertical to the weld centerline followed a ＇＂ V＂ shape. Moreover, large welding residual stress and distortion were found in the interface between blisk and fixtures. The stress concentration was reduced sufficiently in starting and end part of weldment as the fixtures were renmved after welding process, while the removing operation had almost no effects on the welding residual stress in the middle section of weld bead.

Development of an in-situ measuring system for blisk manufacturing

In order to solve the in-situ measurement problem of workpiece with complex structures,a cantilever coordinate measuring machine(CCMM)is proposed to adapt to the finite space constraints of the 5-axis computer numerical control(CNC)processing site.Structure design of dense ball bearing shafting is analyzed and optimized.Factors affecting measurement accuracy of CCMM are analyzed,and measurement accuracy is validated by experiments.Results show that the structure of CCMM is able to satisfy requirements of technical specification,and the in-situ measurement of blisk manufacturing is realized.The CCMM developed is of important significance for machining quantity improvement of blisk and development of large aircraft production.

Finite element analysis of welding residual stress of aero engine blisk by controlling heat input

In order to improve aero engine performance, it is necessary to reduce the welding residual stress of aero engine blisk. In this paper, finite element method was employed to simulate electron beam welding process of blisk, in accordance with the deducing formula（ p = kh ） , the heat input is changed with the weld depth to control welding residual stress of blisk. The calculation results show that welding residual stress of blisk can be controlled effectively by reducing the heat input on the conditions of meeting the demand of weld penetration and guaranteeing the welding quality, a new theoretical method and some numerical data are provided for controlling welding residual stress of blisk.

基于Hertz接触理论的整体叶盘百页轮抛光材料去除深度建模研究

为了揭示复杂曲面百页轮抛光的材料去除机理,假设磨粒凸出高度服从正态分布,通过Hertz接触理论得到了接触区的抛光压力分布模型,然后基于弹塑性接触理论进行单颗磨粒受力分析,结合百页轮表面磨粒凸出高度分布函数建立了磨粒切入深度模型。在此基础上,综合主轴转速、进给速度和磨粒切削沟槽形状等确定了单颗磨粒的材料去除体积,并通过沿抛光轨迹积分的方法建立了材料去除深度模型。实验结果表明,材料去除深度的预测值与实验值的最大偏差和平均偏差分别为4.85%和2.95%,验证了所建材料去除深度模型的正确性和有效性。

航空发动机整体叶盘叶片前倾抛光工序规划

通过增加前倾角的前倾抛光工艺可降低表面粗糙度。探究前倾角对抛光表面质量的影响规律对提高整体叶盘叶片的抛光效率具有重要意义。通过砂布页轮前倾抛光实验,获得P400~P1200粒度砂布页轮抛光TC4整体叶盘叶片时,用在不同抛光次数、前倾角度下的表面粗糙度。实验结果表明,抛光表面粗糙度随着前倾角的增加呈下降趋势。分析了前倾角变化对抛光表面质量的影响机制,并从多个角度进行探讨。通过量化抛光效率,研究了各粒度砂布页轮抛光效率随前倾角的变化规律,并得到了最佳前倾角度;此基础上进行抛光效率最优的抛光工序规划,并通过抛光实验进行验证。实验结果表明,优化后的抛光工序规划能在较少工序内获得合格的表面粗糙度,验证了抛光工序规划结果的可靠性。该研究为TC4整体叶盘叶片砂布页轮抛光工艺的优化提供了理论依据和实践指导。