A forging method for 16Cr3NiWMoVNb biaxial aerospace gears

Abstract

This invention discloses a forging method for 16Cr3NiWMoVNb biaxial aerospace gears, comprising the following steps: (1) blanking; (2) first heating, heating temperature to 1050±10℃, extruding the blank with two hammers in the die; the two hammers in the first heating are 800±100T for the first hammer and 1000±100T for the second hammer. (3) second heating, the blank obtained in step (2) is further heated to 1050±10℃, forged in the same die, the two hammers in the second heating are 1000±100T for the third hammer and 6000±100T for the fourth hammer. The two hammers are then used for final forging; (4) sandblasting heat treatment. This invention rationally allocates the forging deformation amount and deformation distribution during biaxial gear forging, reduces the forging temperature rise, ensures that the deformation amount of the workpiece in a single heating is within 30%-80%, and solves the coarse grain problem of biaxial gears.

Description

TECHNICAL FIELD

[0001] The application discloses a forging method for 16Cr3NiWMoVNb double-shaft aviation gears and belongs to the field of forging of gear transmission parts of aviation engines. BACKGROUND

[0002] When the 16Cr3NiWMoVNb gear steel is forged, all grain sizes are required to meet grade 8 or finer, but coarse grain phenomenon is prone to occur in single-fire forging or multi-fire forging.

[0003] In the existing process for forging double-shaft aviation gears, as shown in the accompanying drawings, the double-shaft aviation gear is first formed at one end of the shaft neck part, and is forged to form the gear part, so that coarse grain is prone to occur in the first-formed part when the second fire is heated. Figure 1 SUMMARY

[0004] In order to overcome the above-mentioned defects, the present application reasonably distributes the forging deformation and deformation public during the forging of the double-shaft gear, reduces the forging temperature rise, and ensures that the single-fire deformation of the workpiece is between 30% and 80%, thereby solving the coarse grain problem of the double-shaft gear.

[0005] The technical scheme of the present application is as follows:

[0006] A forging method for 16Cr3NiWMoVNb double-shaft aviation gears, comprising the following steps:

[0007] (1) blanking

[0008] (2) first fire

[0009] The temperature of the blank is heated to 1050±10℃, and the blank is extruded by a die;

[0010] (3) second fire

[0011] The blank obtained in step (2) is continuously heated to a temperature of 1050±10℃, and is subjected to two-hammer final forging;

[0012] (4) sandblasting treatment.

[0013] Preferably, the two hammers of the first fire in step (2) are a first hammer with an energy of 800±100T and a second hammer with an energy of 1000±100T.

[0014] Preferably, the two hammers of the second fire in step (3) are a third hammer with an energy of 1000±100T and a fourth hammer with an energy of 6000±100T.

[0015] Preferably, the deformation of the workpiece in the second fire in step (3) is controlled to be between 30% and 80%, and the deformation is uniform, and the forging temperature rise is controlled to be within 20℃. ​

[0016] Preferably, the finish forging temperature in the above step (3) is > 900℃, and the transfer time is less than 30s.

[0017] The internal grain size grade of the 16Cr3NiWMoVNb double-shaft aviation gear after the above forging forming is > 8 grade.

[0018] The beneficial effects of the present application are:

[0019] 1. The forging scheme is improved, and the original step-by-step forging forming is improved to integral extrusion forming.

[0020] 2. The original finish forging one-hammer forming scheme is improved to a multi-hammer forming process.

[0021] 3. Through the improvement of the mold and the process route, the overall deformation of the workpiece is realized, the last heat workpiece deformation amount is controlled to be more than 30% and less than 80%, and the deformation is uniform, the forging temperature rise is controlled to be within 20℃. The workpiece has no risk of coarse grains, and the grain size of the workpiece is greater than 8 grade. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 is a schematic diagram of the forged aviation double-shaft gear of the present application;

[0023] Figure 2 is a microstructure morphology diagram of the forged part of Example 1;

[0024] Figure 3 is a microstructure morphology diagram of the forged part of Example 2;

[0025] Figure 4 is a microstructure morphology diagram of the forged part of Example 3. DETAILED DESCRIPTION

[0026] The present application will be further described below in conjunction with the drawings. The following examples are only used to more clearly illustrate the technical solutions of the present application, and cannot be used to limit the protection scope of the present application.

[0027] Example 1: A forging method of a 16Cr3NiWMoVNb double-shaft aviation gear, characterized in that it comprises the following steps:

[0028] (1) blanking

[0029] (2) first heat

[0030] The heating temperature is 1040℃, and the extrusion die is two-hammered to make the blank; the two hammers of the first heat are the first hammer 700T energy and the second hammer 900T energy hammering.

[0031] (3) second heat

[0032] The blank prepared in step (2) is continuously heated to 1040 ℃, and two-hammer finish forging is performed;

[0033] The two hammers of the second fire are respectively a third hammer 900T energy hammer and a fourth hammer 5900T energy hammer. The workpiece deformation of the second fire is controlled to be 30%, and the deformation is uniform. The forging temperature rise is controlled to be within 20 ℃. The finish forging temperature is greater than 900 ℃, and the transfer time is less than 30 s.

[0034] (4) Sandblasting treatment.

[0035] Example 2: A forging method of a 16Cr3NiWMoVNb dual-shaft aviation gear, characterized in that it comprises the following steps:

[0036] (1) blanking

[0037] (2) first fire

[0038] The blank is prepared by two-hammer extrusion die at a heating temperature of 1050 ℃. The two hammers of the first fire are respectively a first hammer 800T energy and a second hammer 1000T energy.

[0039] (3) second fire

[0040] The blank prepared in step (2) is continuously heated to 1050 ℃, and two-hammer finish forging is performed;

[0041] The two hammers of the second fire are respectively a third hammer 1000T energy hammer and a fourth hammer 6000T energy hammer. The workpiece deformation of the second fire is controlled to be 50%, and the deformation is uniform. The forging temperature rise is controlled to be within 20 ℃. The finish forging temperature is greater than 900 ℃, and the transfer time is less than 30 s.

[0042] (4) Sandblasting treatment.

[0043] Example 3: A forging method of a 16Cr3NiWMoVNb dual-shaft aviation gear, characterized in that it comprises the following steps:

[0044] (1) blanking

[0045] (2) first fire

[0046] The blank is prepared by two-hammer extrusion die at a heating temperature of 1050 ℃. The two hammers of the first fire are respectively a first hammer 900T energy and a second hammer 1100T energy.

[0047] (3) second fire

[0048] The blank prepared in step (2) is continuously heated to 1050 ℃, and two-hammer finish forging is performed;

[0049] The two hammers of the fire are the third hammer 1100T energy hammering and the fourth hammer 6100T energy hammering. The workpiece deformation of the two hammers is controlled within 80%, and the deformation is uniform, and the forging temperature rise is controlled within 20℃. The final forging temperature is greater than 900℃, and the transfer time is less than 30s.

[0050] (4) sandblasting treatment.

[0051] As Figures 2-4 The internal organization morphology diagram of the forgings can be obtained that the internal grain size grade of the 16Cr3NiWMoVNb double-shaft aviation gear forged by the above three embodiments is greater than 8 levels.

[0052] The above only describes the preferred embodiments of the present application, and it should be noted that for ordinary skilled in the art, without departing from the technical principles of the present application, a number of improvements and modifications can be made, and these improvements and modifications should be considered as the protection scope of the present application.

Claims

1. A method of forging a 16Cr3NiWMoVNb dual-shaft aircraft gear, characterized in that It comprises the following steps: (1) blanking (2) first fire The heating temperature is 1050±10℃, the billet is extruded by two hammers of the first fire, and the slow cooling treatment is performed; The two hammers of the first fire are respectively the first hammer 800±100T energy and the second hammer 1000±100T energy hammering; (3) second fire The billet prepared in step (2) is heated to 1050±10℃, two-hammer finish forging is performed, and slow cooling treatment is performed; The two hammers of the second fire are respectively the third hammer 1000±100T energy hammering and the fourth hammer 6000±100T energy hammering (4) sandblasting treatment.

2. The forging method of a 16Cr3NiWMoVNb dual-shaft aero gear according to claim 1, characterized in that: The workpiece deformation of the second fire of step (3) is controlled between 30%-80%, and the deformation is uniform, and the forging temperature rise is controlled within 20℃.

3. The method of claim 1, wherein the 16Cr3NiWMoVNb dual-shaft aircraft gear is forged by the steps of: The finish forging temperature in step (3) is >900℃, and the transfer time is less than 30s. ​ 4. The method of claim 1, wherein the 16Cr3NiWMoVNb dual-shaft aircraft gear is forged by the steps of: The internal grain size grade of the 16Cr3NiWMoVNb double-shaft aviation gear after forging forming is >8 grade. ​

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