The profile accuracy and surface integrity of blades directly restrict the performance and service life of the aero-engine. Because of the characteristics of thin-wall deformation and difficult material processing and flexible contact, it is difficult to achieve a precision grinding. Therefore, a self-adaptive abrasive belt grinding method based on the integration of defection and machining was proposed. Firstly, according to the characteristics of the blade structure, the edge grinding and round angle grinding devices were designed, which were used to grinding the blade surface and LTE(the leading and the trailing edges), the damping table and the root corner. Secondly, self-adaptive software was developed based on geometric error of model reconstruction. Finally, the blade grinding test was carried out through the double position integrated seven axis CNC grinding center. The results show that the surface roughness of the blade is less than 0.4μm, the machining error is kept within the range of 0.05mm, and the grinding period is only 3.5h, which satisfies the processing requirements of the blade. Therefore, the self-adaptive abrasive belt grinding technology is an effective method for precision grinding of blades.

      It remains challenges to machine advanced aero-engine powder metallurgy turbine disk with structure integration. Low cutting efficiency, poor surface quality and distortion are the major obstacles. Therefore, researchers in the world have proposed many ways to process turbine disk. This paper reviews the structures of powder metallurgy turbine disks and their cutting properties, discussing the key issues in machining along with existing methodology, as well as surface integration after machining. Finally, the article summarizes some of the tool selecting principles available. It is believed combining wire electrical discharge machining (WEDM) and the super-hard abrasive grinding may be an effective and economic process for final finish of powder metallurgy turbine disks.

      The stator blade segments of aero-engine only process complex surface without double-ended platform, which are welded with other components subsequently. A typical stator blade segment high-temperature alloy GH4169 is featured with abrupt change in curvature, bowed & twisted surface, and obvious change in leading & trailing edge radius. A machining approach for the workpiece using the technique of precision rolling, CNC abrasive belt grinding and non-contact detection was proposed. The detailed process mainly includes the flat slab of rolling blank, the design-manufacture-detection of rolling die, the CNC abrasive blet grinding of leading & trailing edge, ang white-light interference measurement of blade surface. The blades produced by this process can meet the requirements of geometric accuracy and have excellent microstructure and properties.

      Nickel-base superalloy fine-casting blades are difficult to guarantee their machining accuracy during machining due to their large margin and no reference to positioning. In this paper, aero-engine fine-casting blades with nickelbase superalloy are grinded by using robotic belt grinding method combined with adaptive processing technology. Through a 6-point iterative approach, the paper determines the position of the blade relative to the fixture. Then in order to ensure the grinding position and orientation and the grinding parameters, the article plans the trajectory of the model and extracts the position and orientation information of points, and builds fourth order homogeneous matrix to solve the robot trajectory. Finally, based on the information of blade profile, the adaptive processing method was adopted to quantitatively remove the material from the fine-casting blades to ensure its machining accuracy.

      Aiming at the size and shape accuracy of edges of superalloy complex curved blades, an experimental study on precision electrolytic machining (PECM) was conducted. The results show that the use of vibration feed ECM machine tools and optimization of cathode design methods can improve the size of the leading and trailing edges accuracy by PECM processing. Using conductivity of 85- 90mS/cm and 25℃ electrolyte of NaNO3, amplitude of 0.4mm and vibration frequency of 40Hz process the shape of leading edges of the center profile meet the design requirements, and trailing edges is close to the design requirements. On this basis, as a supplementary means of PECM, exploring to solve the problems of the shape control of blade edges by combining with vibration lighting process.

      Because of the complicated shape, the slight profile dimension and the bad formability of superalloy, defects such as folds, cracks and surface damages are usually existed during precision forging process. Thermal parameters compromised of stress field, strain field and temperature field could be obtained using Deform software, the trial production time can be shortened exactly by optimized FEA results. It has been found that Deform could guide the precision forging design and actual production process for airfoils.

      In view of the development status of numerical control machining technology of aero-engine compressor blade, development and the application of several new processes, new equipments in blade NC machining field are expounded in recent years. The integration manufacturing, quick-change fixture, adaptive machining, NC polishing are introduced, analyzed and discussed. Through continuous monitoring and tracking the development process of NC machining technology of aero-engine compressor blade, breaking the limitation of technology development, adjusting research direction, widening ideas of development and innovation, speeding up the development of aero-engine blade manufacturing technology can be realized.

      In order to speed up the steps of intelligent manufacturing technology of aircraft engine manufacturing enterprises, meet the needs of a new generation of aviation engine development, and combine with service characteristics of aircraft engine manufacturing enterprises, firstly, it systematically analyzes the intelligent manufacturing requirements of the enterprise based on the architecture design method. Secondly, it puts forward the informatization application architecture of the intelligent factory aircraft engine manufacturing enterprises in this paper. Finally, it expounds the main construction content, implementation method, and briefly describes the key technology of intelligent factory construction yet to be conquered and the solving suggestion, which is a mirror for aircraft engine manufacturing enterprises and intelligent factory of the equipment manufacturing industry.

      Aiming at the problem of long production cycle of cooling holes in the aero-engine blades with EDM method and the poor processing quality of the ND:YAG laser drilling, one step EDM of cooling holes was proposed based on assisting method. Due to significant difference in gap discharge state between ceramic coatings and superalloys, current EDM control systems were able to achieve a stable and accurate control, which cannot make a compromise on processing efficiency and quality. Therefore, Key techniques for EDM of cooling holes were studied, including discharge state identification method of thermal barrier coated-superalloy, pulse power supply and servo control strategy based on fuzzy control. Based on the above technology, the EDM control system for drilling thermal barrier coated-superalloys was developed. The comparison experiments show that compared with the conventional EDM control system, the self-developed system can improve processing efficiency by 110%, and can obtain better machining quality.

      Aiming at the film cooling holes machining of nickel-based single crystal material by picosecond ultrashort pulsed laser, physical depth of field microscope is used to determine the geometry of the film cooling holes, meanwhile the cavity lumen surface of the membrane pore is observed by optical microscopy. Performances of porous film samples prepared by two processes of picosecond ultrashort pulsed laser and electric discharge using high temperature and low cycle fatigue equipment are compared, and specimen fracture is analyzed by scanning electron microscope (SEM) to evaluate the performance. The results show that the entering and exiting holes surface can avoid ablation by picosecond ultrashort pulsed laser processing step by step and effective control of energy density. While the geometric accuracy can meet the design specifications, also there is no remelting layer, intermittent beads,arcing and micro-cracks and other defects in the cavity. Besides, the surface integrity of the film holes after processing could be effectively improved. The comparative tests of high temperature low cycle fatigue performance of picosecond ultrashort pulsed and EDM film show that the cycle number of sample perforated by picosecond ultrashort pulsed laser is as many as three times that of EDM. SEM of high temperature low cycle fatigue fracture shows that the two kinds of processing specimens are cleavage fracture, without metallurgical defect, the remelting layer formed by EDM drilling may contribute to the fracture, and there is no obvious remelting layer in ultrashort pulsed laser drilling.

      Aero-engine blades have a great influence on the overall performance of the engine. Therefore, inspection of the blade surfaces in a rapid and accurate manner has become a key segment to improve the manufacturing quality of blades, as well as the performance and lifetime of the engine. In order to measure the geometrical shapes and dimensions of those workpieces with complex surfaces such as blades in a way of high accuracy and efficiency, the study on application of an optical scanning system in measuring of section parameters of a blade is carried on in the paper. Taking the traditional coordinate measuring machine (CMM) as the system platform, the optical scanning system is equipped with a new laser scanning probe, which is based on the measuring principle of circumferention triangulation. Also, combining with the special data processing software, the system can be used to inspect and evaluate the geometrical parameters of the specified sections of a blade, which could serve as an advanced solution for the shape inspection and quality control of blades. For verifying the application effect of the optical scanning system in the measurement of blade surfaces, a twisted fan blade is selected as the target. In the measuring procedure, 5 sections of the blade are scanned and measured by the system. After the model matching, the errors of profile, centroid position and chord angle on every section are derived, which fully manifests the effectiveness and practicality of the measuring system.

      The NC machining is the most important processing method for the blisk of aero-engine. The NC machining process is an important step to ensure that the geometric precision of the blisk meets the design requirements. According to the design of three-dimension digital model, the shape of the blade after finish milling can meet the dimensional tolerance of the drawing, but the flow-up blade surface finishing and strengthening process have different degrees of infullence on the character of the blade shape of the blisk, resulting in final geometric dimensions of the blade shape beyond design requirements. By analyzing the surface finishing and strengthening process such as polishing process,  vibratory finishing process, shot peening process, the paper determine its influence law and magnitude on the blade shape parameter, then according to the pre-deformed control technology, revise the machining model and program of the finishing process, allowing the blade to obtain the shape and position opposite to the deformation law of the subsequent surface finishing and strengthening process after finishing milling. At last, eliminate these pre-deformations in subsequent processing to achieve the goal of obtaining a qualified blisk in the delivery state.