先进航空发动机用高温钛合金双性能整体叶盘的制造

Manufacturing of High Temperature Titanium Alloy Dual-Property Blisk Used for Advanced Aero-Engine

钛合金整体叶盘是先进航空发动机压气机系统的典型轻质高效结构。整体叶盘零件工作时,叶片和盘承受不同的热力条件,采用“双性能”代替传统的“均质”设计,是提高压气机转子减重效果及满足愈加严苛且多变的温度和载荷工作条件使用的有效措施。对比分析了两种“梯度热处理”工艺,即分区控温梯度热处理工艺和局部包覆控时梯度热处理工艺制备钛合金双性能整体叶盘的可行性,评估了叶片、盘及过渡区的显微组织控制能力。试验结果表明:两种工艺均能在钛合金整体叶盘的叶片与盘之间的过渡区形成稳定可控的温度梯度,得到双重组织,即叶片为双态组织,盘为细小的片层组织,过渡区位置和尺寸可控,显微组织呈渐变特征。可根据整体叶盘锻件的外形特点和组织性能要求,选用适合的制备工艺及相应的工艺参数。

Titanium alloy blisk is a typical lightweight and efficient part of advanced aero-engine compressor.While working,the blade and disk of blisk are subjected to quiet different thermal and loading condition,it is an effective mean to improve the weight reduction effect of compressor rotor and to meet more stringent and variable thermodynamic condition through dual-property design instead of the traditional uniform-property design.The feasibility of two gradient heat treat-ment processes(GHTP),that is,separated-region temperature-controlled GHTP and partial-packed time-controlled GHTP,for manufacturing titanium alloy dual-property blisk is compared,and the microstructural controllability of blade,disk and transition zone is evaluated.The results show that the two processes can form stable and controllable temperature gradient in the transition zone of blisk,and dual microstructure is formed,that is,blade with duplex structure,disk with fine lamellar structure,the area and size of the transition zone is controllable,and the microstructure is gradually changed as well.Ac-cording to the general contour characteristic,microstructure and performance requirements of the blisk forging,the suitable manufacturing process and corresponding process parameters are applied.