Purpose

This paper aims to optimize the single-point incremental forming process variables for realizing higher formability in Inconel 625 components and to plot the forming limit diagram for Inconel 625 aviation-grade superalloy.

Design/methodology/approach

The formability of Inconel 625 components has been measured in terms of major strain, minor strain and minimum sheet thickness. Response surface methodology with desirability function analysis has been used to achieve maximum formability. The finite element analysis has been conducted at optimal parametric setting.

Findings

The derived forming limit diagram proves that the maximum forming limit for Inconel 625 is 57.5° at the optimal parametric setting, achieved with desirability of 0.995. The outcomes of finite element analysis conducted at optimal parametric setting show excellent agreement with confirmation experiment results.

Practical implications

Inconel 625 superalloy is frequently used in aircraft and other high-performance applications for its superior strength.

Originality/value

It has been suggested that to enhance formability, higher tool rotation speed, minimum step-size, larger tooltip diameter and higher wall angle must be used. Wall angle is the governing parameter among all the parameters.

中文翻译：

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Inconel 625航空级高温合金SPIF成形极限图及工艺参数优化

目的

本文旨在优化单点渐进成形工艺变量，以实现 Inconel 625 部件的更高成形性能，并绘制 Inconel 625 航空级高温合金的成形极限图。

设计/方法论/途径

Inconel 625 部件的可成形性是根据主应变、次应变和最小板厚来测量的。响应面方法与期望函数分析已被用来实现最大的成形性。有限元分析是在最佳参数设置下进行的。

发现

导出的成形极限图证明，在最佳参数设置下，Inconel 625 的最大成形极限为 57.5°，理想度为 0.995。在最佳参数设置下进行的有限元分析结果与验证实验结果非常吻合。

实际影响

Inconel 625 高温合金因其卓越的强度而经常用于飞机和其他高性能应用。

原创性/价值

有人建议，为了提高成形性，必须使用更高的刀具旋转速度、最小的步长、更大的刀尖直径和更大的壁角。壁角是所有参数中的主导参数。