航空发动机GH3230高温合金层板结构TLP扩散焊接制备及力学性能研究  

TLP Diffusion Welding and Joint Mechanical Property of GH3230 Superalloy Laminate Structure in Aero-Engine

作　　者：曲文卿[1] 张斯涵 吕彦龙 滕俊飞 汪淼 杨文静 庄鸿寿[1] QU Wenqing;ZHANG Sihan;LÜYanlong;TENG Junfei;WANG Miao;YANG Wenjing;ZHUANG Hongshou(Beihang University,Beijing 100191,China;AVIC Manufacturing Technology Institute,Beijing 100024,China)

机构地区：[1]北京航空航天大学,北京100191 [2]中国航空制造技术研究院,北京100024

出　　处：《航空制造技术》2024年第3期24-29,共6页Aeronautical Manufacturing Technology

基　　金：航空发动机及燃气轮机重大专项基础研究(J2019-VII-0012)。

摘　　要：随着更高推重比需求的不断提高,航空发动机热端部件不仅需要耐高温材料,更需要冷却效率更高的结构形式,本文采用自主研制的KNiCr–5中间层在1200℃保温4 h的工艺条件下TLP扩散焊接制备了GH3230高温合金多孔层板冷却结构,测试了层板结构模拟件的焊接质量和接头力学性能。超声检测结果表明,层板模拟件所有柱形结构(扰流柱)与底板(冲击板)焊接完好,未发现任何缺陷。焊缝形成了均匀的固溶体组织,无任何化合物相、裂纹和孔洞缺陷存在。室温/950℃高温拉伸测试结果表明,层板板柱结构模拟件和GH3230高温合金棒材对接结构全部断裂在GH3230高温合金基体,焊缝强度均明显高于GH3230高温合金。高温拉伸断裂试件的延伸率高达52%,薄板焊缝90°三点弯曲后无开裂,微观观察无裂纹等缺陷,表明了焊缝具有优异塑性。优异的焊接质量和性能保证了焊缝结构承受高温载荷时能达到GH3230高温合金基体的传热和承力性能,避免了焊缝成为整个层板结构薄弱环节。With the increasing demand for higher thrust-weight ratio,the aero-engine hot-end components not only need the superalloy used for high temperature,but also need the structural configuration with higher cooling efficiency.In this paper,the new GH3230 superalloy porous laminated structure for cooling was TLP diffusion welded at the temperature of 1200℃holding 4 h using the self-developed KNiCr–5 interlayer alloy.The welded quality and mechanical property of the laminated structure are tested.The results of ultrasonic testing show that,all the connection between the column structure and flat impingement plate of the laminated structure simulated sample is high quality and welded together,and no flaw is found.The homogeneous solid solution microstructure is formed in the welded seam zone,and no compound phase,crack and pore defect exist.The tension tests at room temperature and 950℃high temperature reveal that all fractures happened at GH3230 superalloy base metals,when the tension loads were applied on column-to-base connection of laminated structure simulated samples and GH3230 superalloy rod-rod butt joints.The room/high temperature strength of weld seam are obviously higher than those of GH3230 superalloy base metal.The sample elongation at high temperature tension is over 52%,no macrocrack and microcrack existed in the weld seam after the thin plate welded joint was applied three-point bend to 90°angle,indicating the good plasticity of the weld seam.The excellent welded quality and property can provide the weld seam with the same heat conductivity and mechanical property as GH3230 superalloy base metal when the weld seam endure,high temperature load,avoid it becoming the bottleneck in the whole laminated structure.

关 键 词：GH3230高温合金 多孔层板冷却结构 TLP扩散焊 微观组织 力学性能 室温/高温 

分 类 号：V263[航空宇航科学与技术—航空宇航制造工程]