一种改善大型GH4698涡轮盘锻件强度、塑性及冲击性能的方法
By pre-deforming the bar stock of GH4698 turbine disk forgings and using triaxial compressive stress die tooling before roughing and die forging, combined with multi-stage die forging and heat treatment, the problem of low performance of large GH4698 turbine disk forgings was solved, and a significant performance improvement was achieved.
CN115889645BActive Publication Date: 2026-07-17SHAANXI HONGYUAN AVIATION FORGING
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- SHAANXI HONGYUAN AVIATION FORGING
- Filing Date
- 2022-12-09
- Publication Date
- 2026-07-17
Abstract
本发明属于高温合金的热加工领域，涉及一种改善大型GH4698涡轮盘锻件强度、塑性及冲击性能的方法。包括：制荒、模锻前需对棒材增加额外的预变形，对一次碳化物进行充分破碎；对预变形后的坯料需采用三向压应力式模具工装进行制荒，得到荒形；对荒形进行多火次模锻得到涡轮盘锻件；对涡轮盘锻件进行热处理。有效解决了原始大规格棒材一次碳化物组织偏聚引起的抗拉强度、塑性及冲击性能低下的问题。
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