网站首页期刊简介编委会过刊目录投稿指南广告合作征订与发行联系我们English
TC6钛合金叶片形变热处理工艺
英文标题:Deformation heat treatment process of TC6 titanium alloy blades
作者:陆彦良 吴永斌 黄联杰 赵春燕 
单位:中国航发贵州黎阳航空动力有限公司 
关键词:TC6钛合金 形变 热处理 热校 叶片 
分类号:TG156.93
出版年,卷(期):页码:2024,49(11):169-174
摘要:

 针对TC6钛合金叶片在热处理后发生严重变形的问题,设计了不同的形变热处理工艺,对热处理前后叶片叶型关键尺寸变化以及热处理后试样的金相组织和力学性能进行检测,研究了通过形变热处理工艺控制TC6钛合金叶片热处理后变形的可行性。结果表明:采用“终锻+热处理(900~(Tβ-40) ℃,保温12~16 min,终锻,10 s内将锻件转移至空气中冷却至室温)低温退火(640 ℃,保温120~130 min0.1 MPa氩气冷却至60 ℃后空冷)”或“终锻(Tβ-40) ℃,保温12~16 min,终锻)热校+热处理(850~900 ℃,保温12~16min,热校,10 s内将锻件转移至空气中冷却至室温)低温退火(640 ℃,保温120~130 min0.1 MPa氩气冷却至60 ℃后空冷)”的形变热处理工艺,可降低60%以上的TC6钛合金叶片的热处理变形量;在终锻之后的热校正工序中进行形变热处理可获得预期的组织及性能,能够满足叶片锻件的技术要求;为满足强度与塑性双重性能指标对叶片锻件形变热处理后的预期组织的要求,可适当调整形变热处理时的保温温度或保温时间。

 For the problem of serious deformation of TC6 titanium alloy blades after heat treatment, different deformation heat treatment processes were designed.  The changes in key dimensions of blade profile before and after heat treatment and the metallographic structure and mechanical properties of samples after heat treatment were tested to study the feasibility of controlling the deformation of TC6 titanium alloy blades after heat treatment through deformation heat treatment process. The results show that adopting the deformation heat treatment process of “final forging + heat treatment (900-(Tβ-40)℃,holding for 12-16 min, final forging, and transferring the forgings to air and cooling to room temperature within 10 s) low temperature annealing (640 ℃,holding for 120-130 min, cooling to 60 ℃ with 0.1 MPa argon gas and then air cooling)” or “final forging ((Tβ-40)℃,holding for 12-16 min, final forging)  thermal correction + heat treatment (850-900 ℃,holding for 12-16 min, thermal correction, and transferring the forgings to air and cooling to room temperature within 10 s)  low temperature annealing (640 ℃,holding for 120-130 min, cooling to 60 ℃ with 0.1 MPa argon gas and then air cooling)” reduces the heat treatment deformation amount of TC6 titanium alloy blade by more than 60%. Deformation heat treatment in the thermal correction process after final forging obtains the expected microstructure and properties, which meets the technical requirements of blade forgings. Thus, in order to meet the requirements of dual performance indicators of strength and plasticity for the expected microstructure of blade forgings after deformation heat treatment, the holding temperature or time during deformation heat treatment can be appropriately adjusted.

基金项目:
贵州省专项基金资助项目(2018036)
作者简介:
作者简介:陆彦良(1988-),男,学士,高级工程师 E-mail:wugaoaliang@163.com
参考文献:

 [1]刘静安.钛合金的特性与用途[J].有色金属加工,2002,31(4):1-9,59.


Liu J A. Properties and applications of titanium alloy [J]. Nonferrous Metals Processing, 2002, 31 (4):1-9,59.

[2]王泽均,李明强,李长亮,等.航空发动机用BT3-1(TC6)钛合金棒材的试制[J].钛工业进展,2003(1):43-45.

Wang Z J, Li M Q, Li C L, et al. Trial-production of BT3-1(TC6)Ti alloy bars for aircraft engines [J]. Titanium Industry Progress, 2003 (1): 43-45.

[3]顾忠明,张起,乔恩利,等.热处理工艺对大规格Ti6246钛合金棒材组织与性能的影响[J].金属世界,2024(4):54-58.

Gu Z M, Zhang Q, Qiao E L, et al. Effect of heat treatment process on the microstructure and properties of large-size Ti6246 titanium alloy bar[J]. Metal World,2024(4):54-58.

[4]裴颖脱. 基于计算机模拟的安全阀阀体多向模锻精密成形工艺[J]. 锻压技术,2022,47(5):12-18.

Pei Y T. Multi-directional die forging precision forming process of safety valve body based on computer simulation[J]. Forging & Stamping Technology,2022,47(5):12-18.

[5]姚贵,张勇,王利歌,等.一种精锻叶片厚度塑性变形补偿方法[P].中国:CN103244195A,2013-08-14.

Yao G, Zhang Y, Wang L G, et al. A compensation method for plastic deformation of precision forged blade thickness [P]. China: CN103244195A,2013-08-14.

[6]陆彦良,陈玉珍,夏玥,等.一种用于航空发动机叶片装夹热处理的夹具优化方法[P].中国:CN112395742A,2021-02-23.

Lu Y L, Chen Y Z, Xia Y, et al. A fixture optimization method for heat treatment of aircraft engine blade clamping [P]. China: CN112395742A,2021-02-23.

[7]陆彦良,胡吉云,夏玥.一种用于航空发动机精锻叶片真空热处理的装夹装置[P].中国:CN112921168A,2021-06-08.

Lu Y L, Hu J Y, Xia Y. A clamping device for vacuum heat treatment of precision forged blades in aircraft engines [P]. China: CN112921168A,2021-06-08.

[8]王斌,王琪伟,宗影影,等. 5A06铝合金环形连接框等温模锻坯料设计及工艺验证[J]. 锻压技术,2023,48(1):29-45.

Wang B, Wang Q W, Zong Y Y, et al. Design on isothermal die forging billet for 5A06 aluminum alloy ring connecting frame and process validation [J]. Forging & Stamping Technology,2023,48(1): 29-45.

[9]陆彦良,曹敏,潘柳成,等.一种航空发动机TC6钛合金叶片锻件制备方法[P].中国:CN117531941A,2024-02-09.

Lu Y L, Cao M, Pan L C, et al. A method for preparing TC6 titanium alloy blade forgings for aircraft engines [P]. China: CN117531941A,2024-02-09.

[10]HB 5647—1998,叶片叶型的标注、公差与叶身表面粗糙度[S].

HB 5647—1998,Labeling, tolerances, and surface roughness of blade profiles[S].

[11]HB 7726—2002,航空发动机用钛合金叶片精锻件规范[S].

HB 7726—2002, Specification for precision forgings of titanium alloy blades for aeroengine[S].

[12]孙坤,徐媛,叶青,等.不同原始组织TC6钛合金高温变形微结构演化及其力学性能[J].稀有金属材料与工程,2012,41(3):406-412.

Sun K, Xu Y, Ye Q, et al. Microstructure evolution and mechanical properties of TC6 alloys with different original microstructures during high temperature deformation[J]. Rare Metal Materials and Engineering, 2012,41 (3): 406-412.

[13]黄帆,海敏娜,孙虎代,等.热处理对航空紧固件用TC16钛合金棒材组织性能的影响[J].金属世界,2022(5):46-50.

Huang F, Hai M N, Sun H D, et al. Effect of heat treatment on microstructure and properties of TC16 titanium alloy bar[J]. Metal World, 2022(5):46-50.

[14]Mustafi L.TC6 钛合金的相变与热变形行为[D].哈尔滨:哈尔滨工业大学,2016.

Mustafi L.Phase Transformation and Thermal Deformation Behavior of TC6 Titanium Alloy [D]. Harbin: Harbin Institute of Technology,2016.

 
服务与反馈:
文章下载】【加入收藏
《锻压技术》编辑部版权所有

中国机械工业联合会主管  中国机械总院集团北京机电研究所有限公司 中国机械工程学会主办
联系地址:北京市海淀区学清路18号 邮编:100083
电话:+86-010-82415085 传真:+86-010-62920652
E-mail: fst@263.net(稿件) dyjsjournal@163.com(广告)
京ICP备07007000号-9