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.