Time filter

Source Type

Zhao X.,Zhengzhou Institute of Aeronautics | Zhao H.,Guizhou ANDA Aviation Forging Co. | Zhang R.,Zhengzhou Institute of Aeronautics
Advanced Materials Research | Year: 2011

To improve the efficiency of process planning, an CAPP system is developed according to the complexity and particularity of process design for large forgings,. The feature functions of the system are analyzed. The key techniques are discussed. The application results show that the process plans of about 70% large forgings are designed by the system and the efficiency of process planning is improved 4-8 times. © 2011 Trans Tech Publications.


Yu X.-H.,Northwestern Polytechnical University | Li S.-Y.,Northwestern Polytechnical University | Wei Z.-J.,Guizhou Anda Aviation Forging Co. | Xiao Y.-X.,Guizhou Anda Aviation Forging Co.
Suxing Gongcheng Xuebao/Journal of Plasticity Engineering | Year: 2010

The key problem for a knowledge management system is the model of knowledge representation, which is the base stone of knowledge acquisition, sharing, reusing and deduction. The die forging knowledge was classified and summarized with the concept of domain ontology, and a die forging knowledge management model based on ontology meta-data model engine was proposed. Die forging knowledge domain ontology was set tentatively taking framework concept graph for representing the die forging knowledge. The application of the model based on ontology meta-data model engine and represented by framework concept graph knowledge in die forging knowledge management was proposed. A reasoning method fit for ontology meta-data model engine was proposed and applied to die forging process knowledge reasoning. The ontology meta-data model engine is featured in short time for knowledge forming, excellent interoperations and knowledge sharing.


Zhou L.,Guizhou University | Wei Z.,Guizhou Anda Aviation Forging Co. | Liang Y.,Guizhou University | Liang Y.,Xi'an Jiaotong University | And 2 more authors.
Jinshu Rechuli/Heat Treatment of Metals | Year: 2015

Relationship between microstructure and properties of Ti-6242 alloy air-cooled after heating at different temperatures was studied. The results show that when heated at below the phase transition point, the content of α phase is gradually reduced with the heating temperature rising, while higher than the phase transition point, the grain size becomes coarser with the heating temperature rising, the Widmannstatten microstructure is formed after air-cooling; as the heating temperature rising, the strength and ductility capacity of the alloy shows at the beginning increase and then decrease, and the impact toughness is gradually reduced. The strength and toughness variation of the alloy is dependent on the content, shape and grain size of α phase and β phase transition microstructure when the heating temperature is higher than the phase transition point. ©, 2015, Chinese Mechanical Engineering Society of Heat Treatment. All right reserved.


Xin X.,Northeastern University China | Xin X.,CAS Shenyang Institute of Metal Research | Sun W.,CAS Shenyang Institute of Metal Research | Duan Z.,Guizhou Anda Aviation Forging Co. | And 5 more authors.
Xiyou Jinshu Cailiao Yu Gongcheng/Rare Metal Materials and Engineering | Year: 2011

The effects of increasing Al and decreasing Nb on microstructure and mechanical properties of GH706 alloy were studied. With increasing Al from 0.35% to 1.26% and decreasing Nb from 2.88% to 1.98%, the precipitation of γ ″-Ni 3Nb phase is constrained, while the formation of γ'-Ni 3Al phase is promoted. As a result, the tensile strength at room temperature is decreased, but the impact energy is improved. However, such a modification of Al and Nb constrains the precipitation of intergranular η-Ni 3 (Ti, Nb) phase, and enhances the precipitation of Laves phase rich in Nb and Cr 2Nb phase rich in Nb and Cr, which decreases the grain boundary cohesion and deteriorates the stress rupture properties at 650°C and 690 MPa. © 2011, Northwest Institute for Nonferrous Metal Research. Published by Elsevier BV. All rights reserved.


Zhao X.,Zhengzhou Institute of Aeronautics | Zhao H.,Guizhou ANDA Aviation Forging Co. | Zhang R.,Zhengzhou Institute of Aeronautics
Advanced Materials Research | Year: 2012

The hot deformation behavior of TC18 titanium alloy was studied in alpha-beta phase region. The temperature range was 1023-1123K and strain rate range 1-0.001 -1s -1. The material constants of the alloy, including deformation activation energy ΔH as 364.823kJ / mol, stress-level coefficient α as 0.0086mm 2/ N, stress exponential n as 3.8442 and structural factor A as 1.2601×10 15s -1 were derived by Zener-Hollomon method from the interdependencies of flow stress, strain rate and temperature. © (2012) Trans Tech Publications, Switzerland.


Zhao X.,Zhengzhou Institute of Aeronautics | Zhao H.,Guizhou ANDA Aviation Forging Co. | Zhang R.,Zhengzhou Institute of Aeronautics
Advanced Materials Research | Year: 2012

The hot deformation characteristics of TC18 titanium alloy were studied in the temperature range 750-850° and strain rate range 0.001-1 s -1 by using hot compression tests. Processing maps for hot working are developed on the basis of the variations of efficiency of power dissipation with temperature and strain rate. The results reveal that the flow stress of TC18 is sensitive to strain rate. Processing map at stain of 0.6 reveals two domains: one is centered at 750° and 0.001s -1; another is centered at 850° and 0.001s -1. The maximum efficiency is more than 60%. According to the maps, the zone with the temperature range of 750-850° and strain rate range of 0.01-0.001s -1 may be suitable for hot working. © (2012) Trans Tech Publications, Switzerland.


Patent
Guizhou Anda Aviation Forging Co. | Date: 2014-05-23

A method for expanding a rectangular section ring to form a non-rectangular section ring. The method includes heating a rectangular section ring of an alloy to a temperature of between 1000 and 1020 C., preheating an expanding block to a temperature of between 260 and 320 C., nesting the inner circumferential surface of the rectangular section ring on the outer circumferential surface of the expanding block; enabling the expanding block to press the inner circumferential surface of the ring in the radial direction, expanding the inner and outer diameter of the rectangular section ring and decreasing the wall thickness thereof for deforming the rectangular section ring to yield a profiled ring billet, whereby finishing a first expanding; rotating the profiled ring billet for 45 along the central axis, whereby finishing a first rotation; and repeating the expanding process and the rotation to obtain a non-rectangular section ring.

Loading Guizhou ANDA Aviation Forging Co. collaborators
Loading Guizhou ANDA Aviation Forging Co. collaborators