CN-121972599-A - Aviation alloy shell cold heading forming device and forming process

CN121972599ACN 121972599 ACN121972599 ACN 121972599ACN-121972599-A

Abstract

The invention relates to the technical field of metal plastic processing, and provides a cold heading forming device and a forming process for an aviation alloy shell. The device comprises an annular multipoint distributed soaking component, a punch body internally provided with a plurality of independent mounting cavities, a plurality of telescopic micro-induction heating units, an inner heat insulation layer and an outer heat insulation sleeve. The annular soaking component is arranged on the periphery of the blank to realize integral preheating, and each heating unit in the punch head can independently and axially stretch and is provided with a heat insulation structure to avoid heat damage to the die. In the process, firstly, a blank is preheated through a peripheral multipoint soaking component, then a plurality of induction heating heads in a punch head are subjected to zone secondary heating, and after the heating is finished, the blank is retracted, and then upsetting is carried out. The invention eliminates local hot spot and temperature difference stress through inner and outer synergic gradient temperature equalization, obviously reduces part residual stress, protects the die, improves forming precision and assembly qualification rate, and is suitable for precise cold heading forming of aviation alloy shells such as TC4, GH4169 and the like.

Inventors

YANG YUE
HUANG ZHIBIN

Assignees

湖南中天云航科技有限公司

Dates

Publication Date: 20260505
Application Date: 20260403

Claims (8)

1. An aeronautical alloy casing cold heading forming device, characterized by comprising: The annular multipoint distributed soaking component is arranged on the periphery of the blank and is used for preheating the whole blank; a punch body having a plurality of independent mounting cavities therein; the telescopic micro induction heating units are arranged in the mounting cavities of the punch body in a one-to-one correspondence manner, and each heating unit comprises an induction heating head and a telescopic driving mechanism for driving the induction heating head to independently stretch along the axial direction of the punch; an internal heat insulation layer arranged between each telescopic micro induction heating unit and the inner wall of the corresponding punch mounting cavity, and And the outer heat insulation sleeve is sleeved on the periphery of the punch body.
2. The cold heading forming device for the aviation alloy shell according to claim 1, wherein the annular multipoint distributed soaking assembly comprises a plurality of micro heating units which are uniformly distributed along the circumferential direction, the number of the micro heating units is 6 to 12, and the plurality of induction heating heads are distributed in an array on the end face of a punch and respectively correspond to different areas of a blank surface to be formed.
3. The cold heading forming device of an aircraft alloy housing according to claim 1, wherein the telescopic micro-induction heating unit further comprises a guide insulating sleeve arranged between the induction heating head and the corresponding inner wall of the punch mounting cavity.
4. The cold heading forming device for an aero-alloy shell according to claim 1, wherein the inner heat insulation layer is a high-temperature heat insulation ceramic or aerogel composite layer.
5. The cold heading forming device for an aero-alloy shell according to claim 4, wherein one end of the mounting cavity is provided with a conical inner bottom, and the conical inner bottom is provided in a direction away from the telescopic driving mechanism.
6. The cold heading forming device for an aviation alloy shell according to claim 1, wherein the induction heating head is electrically induction heated, and the telescopic driving mechanism is driven by an electric cylinder.
7. The cold heading forming device for an aero-alloy shell according to claim 1, wherein the outer heat-insulating sleeve is made of high-temperature alloy.
8. A gradient uniform temperature process method for cold heading forming of an aviation alloy, which is applied to the cold heading forming device of an aviation alloy shell as claimed in any one of claims 1 to 7, and is characterized by comprising the following steps: Firstly, performing peripheral pre-soaking on a blank through an annular multipoint distributed soaking component, and integrally heating the blank to a first target temperature; step two, the preheated blank is sent into a die cavity, and a punch main body descends to enable an external heat-insulating pressing sleeve to contact the blank; driving the corresponding induction heating heads to extend out simultaneously by the telescopic driving mechanisms, and secondarily heating the blank to a second target temperature in different areas close to the blank surface to be formed; Step four, each induction heating head is retracted into the corresponding punch mounting cavity, and the punch main body continues to perform cold heading forming in a descending way; and fifthly, after forming is completed, returning the punch body and ejecting the part.

Description

Aviation alloy shell cold heading forming device and forming process Technical Field The invention relates to the technical field of metal plastic processing, in particular to a cold heading forming device and a forming process for an aviation alloy shell, which are particularly suitable for cold heading forming of aviation alloy fasteners such as titanium alloy and high-temperature alloy and shell parts. Background In cold heading forming of aviation fasteners and shell parts, TC4 titanium alloy, GH4169 superalloy and other aviation materials are poor in room temperature plasticity and large in deformation resistance, the traditional cold heading can enable the parts to generate large residual stress, uneven shrinkage occurs in subsequent storage or heat treatment, and assembly difficulty, size overfall and even scrapping are caused. In order to improve the forming performance, a local heating auxiliary cold heading technology is commonly adopted in the industry, and deformation resistance and residual stress are reduced by properly heating the blank. The existing heating auxiliary cold heading mostly adopts a single-point or local concentrated heating mode, but has obvious defects that firstly, a local high-temperature area is easily formed due to concentrated heat source, the temperature difference between the inside and the outside of a blank is obvious, extra temperature difference stress is introduced due to uneven thermal expansion, the problem of later shrinkage deformation is not eliminated from the source, secondly, the heat source directly acts on the blank and simultaneously continuously irradiates mold parts such as a punch, a female die and the like, so that the local overheating softening and the abrasion of the mold are accelerated, the precision of the cavity is reduced, the service life is obviously reduced, thirdly, the single-point heating heat conduction of a surface layer is delayed, the uneven phenomenon of surface heat and internal cooling is easily generated, the heating time is prolonged, the problems of thick surface layer tissues, oxidization and the like are also caused, and the performance of parts is influenced. The existing local heating cold heading technology is difficult to realize uniform heating of blanks, has obvious defects in controlling residual stress, protecting a die and stabilizing forming quality, and cannot meet the manufacturing requirements of high precision and high reliability of aviation precision parts. Therefore, we propose a cold heading forming device and a forming process for an aviation alloy shell, which can effectively solve the problems. Disclosure of Invention Aiming at the defects in the prior art, the invention provides an aviation alloy shell cold heading forming device and a forming process, which are used for solving the problems of large temperature difference stress, serious die thermal damage, insufficient heating depth and the like. The cold heading forming device for the aviation alloy shell comprises annular multipoint distributed soaking components, a punch body, a plurality of telescopic micro induction heating units, an inner heat insulation layer and an outer heat insulation sleeve, wherein the annular multipoint distributed soaking components are arranged on the periphery of a blank and used for integrally preheating the blank, the inside of the punch body is provided with a plurality of independent mounting cavities, the telescopic micro induction heating units are correspondingly arranged in the plurality of mounting cavities of the punch body one by one, each heating unit comprises an induction heating head and a telescopic driving mechanism for driving the induction heating head to independently stretch along the axial direction of the punch, and the inner heat insulation layer is arranged between each telescopic micro induction heating unit and the inner wall of the corresponding punch mounting cavity and sleeved on the periphery of the punch body. Further, the annular multipoint distributed soaking component comprises a plurality of micro heating units which are uniformly distributed along the circumferential direction, the number of the micro heating units is 6 to 12, and a plurality of induction heating heads are distributed in an array on the end face of the punch and respectively correspond to different areas of the blank surface to be formed. In practical application, the design can form a wrapped surface heat source, so that the temperature of the whole body of the blank is consistent, and the original temperature difference is eliminated. The plurality of heating units work simultaneously, so that the concentration of a single heat source is avoided. Thereby avoiding local hot spots caused by the concentration of a single heat source, thereby eliminating the stress concentration caused by uneven thermal expansion from a physical source and providing a uniform matrix temperature field for the subsequent forming. Furthe