(1. 沈陽航空航天大學(xué) 航空制造工藝數(shù)字化國防重點(diǎn)學(xué)科實(shí)驗(yàn)室，沈陽 110136; 2. 中國航發(fā)沈陽黎明航空發(fā)動(dòng)機(jī)有限責(zé)任公司，沈陽 110043)
摘 要: 結(jié)合GH4169高溫合金表面損傷的修復(fù)需求，研究基體預(yù)熱對不同基體厚度的激光沉積修復(fù)GH4169高溫合金試樣殘余應(yīng)力、顯微組織、拉伸性能的影響規(guī)律。結(jié)果表明：與未預(yù)熱修復(fù)試樣相比，基體預(yù)熱300 ℃的GH4169合金激光沉積修復(fù)試樣的殘余應(yīng)力σx、σy均明顯降低，修復(fù)區(qū)枝晶間析出的Laves相變得粗壯并呈現(xiàn)顆粒狀的碎化趨勢，抗拉強(qiáng)度略微降低，但斷后伸長率提高60%以上，達(dá)到鍛件標(biāo)準(zhǔn)。基體厚度越大，修復(fù)體厚度越小，修復(fù)試樣的殘余應(yīng)力減小，枝晶間析出的Laves相減少，抗拉強(qiáng)度與斷后伸長率均略有增加。
關(guān)鍵字: GH4169合金；激光沉積修復(fù)；預(yù)熱；殘余應(yīng)力；顯微組織；拉伸性能
（1. Key Laboratory of Fundamental Science for National Defence of Aeronautical Digital Manufacturing Process, Shenyang Aerospace University, Shenyang 110136, China; 2. Welding Laboratory, Shenyang Liming Aero-Engine (Group) Corporation LTD, Shenyang 110043, China）
Abstract:Combining with the repairing demand of GH4169 alloy surface damage, the effect of substrate preheating process on the residual stress, microstructure and tensile property of laser deposition repair (LDR) GH4169 alloy specimen with different substrate thickness were investigated. The results show that, in contrast to repaired specimen without preheating, laser deposition repair GH4169 alloy after the substrate is preheated to 300 ℃, both σx and σy of residual stress are reduced obviously. The Laves phase of the interdendritic in deposition becomes thick, and it presents a granular fragmentation phenomenon. The tensile strength is reduced slightly, but the elongation rate increases above 60%.These indicate that the standard of forging is reached. With the bigger substrate thickness and the smaller deposition thickness, the residual stress and Laves phase of the interdendritic of repaired specimen are decreased, the tensile strength and elongation are improved slightly.
Key words: GH4169 alloy; laser deposition repair; preheat; residual stress; microstructure; tensile property
