CN218460738U

CN218460738U - Tool for precisely rolling large-scale aviation high-temperature alloy casing

Info

Publication number: CN218460738U
Application number: CN202222438135.9U
Authority: CN
Inventors: 刘其源; 何方有; 刘智; 巩芳源; 艾志斌
Original assignee: Wuxi Paike New Material Technology Co ltd
Current assignee: Wuxi Paike New Material Technology Co ltd
Priority date: 2022-09-14
Filing date: 2022-09-14
Publication date: 2023-02-10
Anticipated expiration: 2032-09-14

Abstract

The utility model discloses a be used for accurate rolling frock of large-scale aeronautical superalloy machine casket, including main roll and core roller, wherein, the laminating of the outside streamline of the inner wall of main roll and finished product machine casket, the outer wall of core roller is equipped with a plurality of annular convex surfaces, the main roll is joined in marriage with the core roller and is carried out special-shaped and roll the ring shaping. The utility model discloses a design to the frock mould to reduce raw and other materials cost and machining cost, make the surplus of product obtain optimizing, improve raw and other materials utilization ratio, solved large-scale superalloy casing raw and other materials cost big, material utilization ratio low and the too big problem of machining surplus.

Description

Tool for precisely rolling large-scale aviation high-temperature alloy casing

Technical Field

The utility model relates to a forge technical field, specifically be a frock that is used for large-scale aviation to use high temperature alloy cartridge receiver precision rolling.

Background

With the rapid development of the aerospace industry at home and abroad, the demand of large high-temperature alloy forgings for aerospace is more and more vigorous. In the traditional forging production process, due to process limitation, a segmented forming method is generally used and then welding is used. Although the design and production difficulty is small, a special die and a special tool are not needed, the material utilization rate is low, and the overall performance of a welding part is poor. Therefore, the high-temperature alloy casing forged piece for aviation is directly rolled into a forged piece with a shape close to a product shape by adopting a special-shaped ring rolling forming method so as to achieve the purpose of reducing the cost. But at present forging special-shaped rolling ring blanking in-process, the mould frock of adoption is mostly the design with the laminating of finished product forging appearance, has improved the mechanical properties of material, but is lower to the utilization ratio of material when rolling the ring, still can not solve large-scale superalloy casing raw and other materials cost big, material utilization is low and the too big problem of machining allowance.

Disclosure of Invention

The utility model aims at providing a frock that is used for large-scale aviation to use high temperature alloy cartridge receiver precision rolling through the design to the tooling mold to reduce raw and other materials cost and machining cost, make the surplus of product obtain optimizing, improve raw and other materials utilization ratio.

The utility model discloses the technical scheme who mainly adopts among does:

the utility model provides a frock that is used for accurate rolling of large-scale aviation high temperature alloy machine casket, includes main roll and core roller, wherein, the inner wall of main roll and the laminating of the outside streamline of finished product machine casket, the outer wall of core roller is equipped with a plurality of annular convexities, the main roll is joined in marriage with the core roller and is carried out special-shaped rolling ring shaping.

Preferably, the inner wall of the main roller is sequentially provided with a straight wall section, a first inclined wall section, a second inclined wall section, a third inclined wall section and a step which are arranged in the circumferential direction from top to bottom, and the sections are connected through a transition circular arc.

Preferably, the radius of the transition circular arc between the third inclined wall section and the step is R30-R50mm.

Preferably, the radius of the transition arc between the straight wall section and the first inclined wall section is R50-R100mm, and the radius of the transition arc between the first inclined wall section and the second inclined wall section and between the second inclined wall section and the third inclined wall section is R100-R105mm.

Preferably, a plurality of the annular convex surfaces on the outer wall of the core roller are continuously connected or connected at intervals, wherein a plurality of the annular convex surfaces are continuously connected by transition arcs.

Preferably, the annular convex surface is a circular arc convex surface arranged annularly.

Preferably, the outer wall of the core roller is provided with five sections of continuously arranged arc-shaped convex surfaces, including a first arc-shaped convex surface, a second arc-shaped convex surface, a third arc-shaped convex surface, a fourth arc-shaped convex surface and a fifth arc-shaped convex surface.

Preferably, the arc radiuses of the first arc-shaped convex surface, the second arc-shaped convex surface, the third arc-shaped convex surface and the fifth arc-shaped convex surface are all R50-80mm, and the arc radius of the fourth arc-shaped convex surface is R70-110mm.

Has the advantages that: the utility model provides a frock that is used for large-scale aeronautical superalloy cartridge receiver precision rolling through the design to the frock mould, on the basis that does not influence cartridge receiver appearance and mechanical properties for cartridge receiver inner wall grinds the ring and forms the ring channel, can make the finish forging product compare in the present product weight of having practiced thrift 20% -30%, fully improves the material utilization of product, has reduced the manufacturing cost of product.

Drawings

FIG. 1 is a schematic view of the structure of example 1 before finish rolling;

FIG. 2 is a schematic view of the structure after finish rolling in example 1;

in the figure: the roller comprises a main roller 1, a straight wall section 1-1, a first inclined wall section 1-2, a second inclined wall section 1-3, a third inclined wall section 1-4, a step 1-5, a core roller 2, a first arc-shaped convex surface 2-1, a second arc-shaped convex surface 2-2, a third arc-shaped convex surface 2-3, a fourth arc-shaped convex surface 2-4, a fifth arc-shaped convex surface 2-5 and a blank 3.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. The following description of the embodiments is merely exemplary in nature and is in no way intended to limit the invention, its application, or uses.

It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present. In contrast, when an element is referred to as being "directly on" another element, there are no intervening elements present. In contrast, when an element is referred to as being "directly connected to" another element, there are no intervening elements present. The terms "vertical," "horizontal," "left," "right," and the like are used herein for purposes of illustration only.

In the description of the present invention, it is to be understood that the terms "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are merely for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, are not to be construed as limiting the present invention.

Example 1

A tool for precisely rolling a large-scale aeronautical high-temperature alloy casing comprises a main roller 1 and a core roller 2, wherein the inner wall of the main roller 1 is attached to an external streamline of a finished casing, the inner wall of the main roller 1 is sequentially provided with a straight wall section 1-1, a first inclined wall section 1-2, a second inclined wall section 1-3, a third inclined wall section 1-4 and a step 1-5 which are annularly arranged from top to bottom, the sections are connected by adopting transition arcs, the radius of the transition arcs between the straight wall section 1-1 and the first inclined wall section 1-2 is R50mm, the radius of the transition arcs between the first inclined wall section 1-2 and the second inclined wall section 1-3 and the radius of the transition arcs between the second inclined wall section 1-3 and the third inclined wall section 1-4 are R150mm, and the radius of the transition arcs between the third inclined wall section 1-4 and the step 1-5 are R45mm;

the outer wall of the core roller 2 is provided with five sections of annularly arranged arc-shaped convex surfaces which are continuously connected by adopting transition arcs and comprise a first arc-shaped convex surface 2-1, a second arc-shaped convex surface 2-2, a third arc-shaped convex surface 2-3, a fourth arc-shaped convex surface 2-4 and a fifth arc-shaped convex surface 2-5, wherein the arc radiuses of the first arc-shaped convex surface 2-1, the second arc-shaped convex surface 2-2, the third arc-shaped convex surface 2-3 and the fifth arc-shaped convex surface 2-5 are all R75mm, and the arc radius of the fourth arc-shaped convex surface 2-4 is R105mm.

The concrete steps of rolling the ring blank in the process of preparing the low-pressure turbine special-shaped casing in the embodiment 1 are as follows:

s1, heating a blank: feeding 2.5T high-temperature alloy bars into a furnace at the temperature of less than or equal to 500 ℃, heating to 950 ℃, preserving heat for 8 hours, heating to 1020 ℃, preserving heat for 6 hours, and discharging;

s2, cake upsetting and punching: adopting a press machine to sequentially perform cake upsetting and punching processing on the heated blank so as to obtain a perforated annular blank with a preset size;

s3, trestle reaming: heating the annular blank with the holes to 1100-1130 ℃, preserving heat for 2-3h, and then taking out of the furnace to perform trestle reaming to reach the corresponding size;

s4, rolling a ring with a straight wall: heating the blank 3 after the hole expansion of the trestle to 1100-1130 ℃, keeping the temperature for 2-3h, discharging, and then adopting a straight wall die to perform straight wall ring rolling;

s5, special-shaped ring rolling: heating the blank 3 after the ring rolling on the straight wall to 1050-1100 ℃, keeping the temperature for 2-3h, discharging, and performing special-shaped ring rolling;

s6, blank making of a fetal membrane: inversely heating the blank subjected to the special-shaped ring rolling to 1030-1080 ℃, preserving heat for 2-3h, discharging, and performing special-shaped blank making by using a press through matching of a forming die and a punch to finish final blank making;

s7, final rolling forming: and heating the blank subjected to final blank making to 1000-1050 ℃, preserving heat for 2-3h, discharging, and performing final special-shaped ring rolling forming by using the rolling tool recorded in the embodiment 1 to obtain the finished special-shaped casing shown in the figure 2.

The utility model provides a structure of annular convex surface can design according to actual conditions.

It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

Furthermore, it should be understood that although the present specification describes embodiments, not every embodiment includes only a single embodiment, and such description is for clarity purposes only, and it is to be understood that all embodiments may be combined as appropriate by one of ordinary skill in the art to form other embodiments as will be apparent to those of skill in the art from the description herein.

Claims

1. The utility model provides a frock that is used for accurate rolling of large-scale aviation superalloy cartridge receiver which characterized in that, includes main roll and core roller, wherein, the inner wall of main roll and the laminating of the outside streamline of finished product cartridge receiver, the outer wall of core roller is equipped with a plurality of annular convex surfaces, main roll and core roller are joined in marriage and are carried out special-shaped rolling ring shaping.

2. The tool for precisely rolling the large-scale aeronautical high-temperature alloy casing according to claim 1, wherein the inner wall of the main roller is sequentially provided with a straight wall section, a first inclined wall section, a second inclined wall section, a third inclined wall section and a step which are arranged annularly from top to bottom, and the sections are connected by adopting a transition arc.

3. The tooling for precisely rolling the large-scale aeronautical superalloy casing according to claim 2, wherein the radius of the transition arc between the third inclined wall section and the step is R30-R50mm.

4. The tooling for precisely rolling the large-size aeronautical superalloy casings according to claim 3, wherein the radius of a transition arc between the straight wall section and the first inclined wall section is R50-R100mm, and the radius of a transition arc between the first inclined wall section and the second inclined wall section and between the second inclined wall section and the third inclined wall section is R100-R105mm.

5. The tool for precisely rolling the large-scale aviation high-temperature alloy casing according to claim 1, wherein the annular convex surfaces on the outer wall of the core roller are continuously or alternately connected, and transition arcs are adopted among the annular convex surfaces to realize continuous connection.

6. The tool for precisely rolling the large-scale aviation high-temperature alloy case according to claim 5, wherein the annular convex surface is a circular arc-shaped convex surface which is annularly arranged.

7. The tool for precisely rolling the large-size aeronautical high-temperature alloy casing according to claim 6, wherein five continuously arranged circular arc-shaped convex surfaces are arranged on the outer wall of the core roller, and the five continuously arranged circular arc-shaped convex surfaces comprise a first circular arc-shaped convex surface, a second circular arc-shaped convex surface, a third circular arc-shaped convex surface, a fourth circular arc-shaped convex surface and a fifth circular arc-shaped convex surface.

8. The tool for precisely rolling the large-scale aeronautical high-temperature alloy casing according to claim 7, wherein the arc radiuses of the first arc-shaped convex surface, the second arc-shaped convex surface, the third arc-shaped convex surface and the fifth arc-shaped convex surface are all R50-80mm, and the arc radius of the fourth arc-shaped convex surface is R70-110mm.