阅读说明：本技术 一种航空发动机整体叶盘惯性摩擦焊接接头设计方法 (Design method for inertia friction welding joint of blisk of aircraft engine ) 是由 李晓光 刘佳涛 帅焱林 赵强 尚震 于 2021-09-15 设计创作，主要内容包括：本发明涉及一种航空发动机整体叶盘惯性摩擦焊接接头设计方法,首先对整体叶盘零件的尺寸进行分析,找出惯性摩擦焊缝位置；然后对零件进行拆分,对拆分后的两部分进行重构,在焊接接头部位两侧增加加工余量,且分别对两部分的焊接接头部分进行取直,使焊接接头与盘体轴线平行,完成焊接接头部分的尺寸重构后,检查是否存在干涉情况,能够满足惯性摩擦焊接要求后进行惯性摩擦焊接。本发明能够使压气机整体转子的制造精度得到提升,零件制造重复度高,提高了整体转子零件的产品合格率和生产效率,能够满足产品的研制生产需要,增加经济收入。(The invention relates to a design method of an inertia friction welding joint of a blisk of an aero-engine, which comprises the steps of firstly analyzing the size of a blisk part and finding out the position of an inertia friction welding seam; then the parts are split, the split two parts are reconstructed, machining allowance is added on two sides of the welding joint part, the welding joint parts of the two parts are straightened respectively to enable the welding joints to be parallel to the axis of the disc body, after the size reconstruction of the welding joint parts is completed, whether interference conditions exist is checked, and the inertia friction welding can be carried out after the requirement of the inertia friction welding is met. The invention can improve the manufacturing precision of the integral rotor of the gas compressor, has high part manufacturing repeatability, improves the product qualification rate and the production efficiency of the integral rotor part, can meet the requirement of product development and production, and increases the economic income.)

1. A design method for an inertia friction welding joint of a blisk of an aircraft engine is characterized by comprising the following steps:

the method comprises the following steps: analyzing the size of the blisk part, and finding out the position of an inertia friction welding line by using a blisk sectional view;

step two: splitting the part, and splitting the part by taking the position of the welding seam as a parting line;

step three: reconstructing the two split parts, respectively increasing machining allowance on two sides of the welding joint part, and respectively straightening the welding joint part to enable the welding joint to be parallel to the axis of the disc body;

step four: after the size reconstruction of the welding joint part is completed, whether the interference condition exists or not is checked, if the interference condition does not exist, the welding accessibility is good, the requirement of inertia friction welding can be met, and the inertia friction welding is carried out.

2. The design method of the inertia friction welding joint of the blisk of the aero-engine as set forth in claim 1, wherein: the position of the friction welding seam in the first step is required to meet the requirements that the area of the position is good in openness and free of interference, and welding and subsequent processing are easy.

3. The design method of the inertia friction welding joint of the blisk of the aero-engine as set forth in claim 1, wherein: the machining allowance in the third step is 1-4 mm.

Technical Field

The invention belongs to the technical field of welding, and particularly relates to a design method of an inertial friction welding joint of an aero-engine blisk.

Background

The manufacturing of the two-stage blisk of the compressor of the aircraft engine adopts an inertia friction welding technology, the inertia friction welding technology is a key technology for manufacturing parts such as blisk rotors of the compressor of the aircraft engine, and the traditional welding joint structure has large welding residual stress and poor dimensional accuracy, so that the axial dimensional repetition accuracy of the two-stage blisk rotors of the compressor is low.

Disclosure of Invention

Aiming at the defects in the prior art, the invention provides a design method of an inertia friction welding joint of a blisk of an aero-engine, which can improve the welding quality of a two-stage blisk rotor of the compressor, improve the machining precision of the whole rotor of the compressor after welding, further improve the production efficiency and the product percent of pass of rotor-type parts of the blisk of the compressor, and improve the manufacturing reliability of the parts.

A design method for an inertia friction welding joint of a blisk of an aircraft engine specifically comprises the following steps:

the method comprises the following steps: analyzing the size of the blisk part, and finding out the position of an inertia friction welding line by using a blisk sectional view;

step two: splitting the part, and splitting the part by taking the position of the welding seam as a parting line;

step three: reconstructing the two split parts, respectively increasing machining allowance on two sides of the welding joint part, and respectively straightening the welding joint part to enable the welding joint to be parallel to the axis of the disc body;

step four: after the size reconstruction of the welding joint part is completed, whether the interference condition exists or not is checked, if the interference condition does not exist, the welding accessibility is good, the requirement of inertia friction welding can be met, and the inertia friction welding is carried out.

The position of the friction welding seam in the first step is required to meet the requirements that the area of the position is good in openness and free of interference, and welding and subsequent processing are easy.

The machining allowance in the third step is 1-4 mm.

The invention has the beneficial effects that: the invention can improve the manufacturing precision of the integral rotor of the gas compressor, has high part manufacturing repeatability, improves the product qualification rate and the production efficiency of the integral rotor part, can meet the requirement of product development and production, and increases the economic income.

Drawings

FIG. 1 is a schematic view of a weld location of a blisk part provided in accordance with an embodiment of the present invention;

fig. 2 is a schematic diagram of a pre-welding shape of an inertia welding joint according to an embodiment of the present invention (in which fig. (a) is a 1 st disc, and fig. (b) is a 2 nd disc);

FIG. 3 is a schematic representation of a post-weld shape of an inertia weld joint provided in accordance with an embodiment of the present invention;

wherein the content of the first and second substances,

1-welding position, 2-machining allowance and 3-welding joint.

Detailed Description

For better understanding of the present invention, the technical solutions and effects of the present invention will be described in detail by the following embodiments with reference to the accompanying drawings.

A design method for an inertia friction welding joint of a blisk of an aircraft engine specifically comprises the following steps:

the method comprises the following steps: the size of the blisk part is analyzed, the blisk sectional view is utilized to find out the position of the inertia friction welding line, the area of the position is good in openness, interference does not exist, and welding and subsequent processing are easy.

As shown in fig. 1, taking an engine compressor as an example, the welding position 1 of the 1 st stage blisk of the engine compressor is located between two blades and 8mm away from the 1 st stage blisk, the welding position 1 avoids the wall teeth of the 2 nd stage blisk, and the area is good in openness and easy to weld and subsequently process.

Step two: and (3) splitting the part, wherein the part is split by taking the position of a welding seam at the position 8mm away from the 1 st-level disc as a dividing line.

Step three: reconstructing the two split parts, reconstructing the shape and size of a welded joint 3 of a 1 st-level disc and a 2 nd-level disc in the embodiment, respectively adding 2mm machining allowance 2 on two sides of the welded joint 3 part in the embodiment, and respectively straightening the welded joint 3 parts of the 1 st-level disc and the 2 nd-level disc to enable the welded joint 3 to be parallel to the axis of the disc body and utilize the conduction of welding force. As shown in fig. 2.

Step four: after the dimensional reconstruction of the welded joint 3 portion is completed, it is checked whether there is an interference situation. Through inspection, the joint structure effectively avoids a 2 nd-level disc wall tooth structure, the interference condition does not exist, the welding accessibility is good, and the requirement of inertia friction welding can be met. Inertia friction welding is then carried out, and the welded joint 3 is constructed as shown in fig. 3.

In the embodiment, the 1-2 stage blisk of the engine compressor has good welding quality, the flash is formed to be round and smooth, no crack is found after the flash is processed, and a welding test piece passes a mechanical test and meets the use requirement. Therefore, the design method provided by the invention meets the manufacturing requirements of all engine compressor two-stage blisk parts.