Aero-engine directional solidification blade structure integrity auxiliary detection device

Abstract

The utility model discloses an aero-engine directional solidification blade structure integrity auxiliary detection device, and belongs to the technical field of blade detection. The aero-engine directional solidification blade structure integrity auxiliary detection device comprises a blade profile mold and a lineation sample plate, the blade profile mold comprises a blade basin, a blade back and a blade root, an airflow channel is arranged in the blade basin, and the lineation sample plate is fixedly attached to the blade basin, the blade back and the blade root. In order to solve the problems that a geometric included angle between a grain boundary and a Z axis is difficult to accurately calculate under a visual condition, an inspector usually judges according to subjective experience, and mass escape is possibly caused, after a plurality of lineation sample plates are fixed, scribed lines parallel to the Z axis are marked near the position where the grain boundary included angle needs to be measured, and finally, a protractor is used for measuring the grain boundary included angle. And measuring the grain boundary of which the included angle needs to be measured, reading the numerical value alpha of the included angle of the grain boundary according to the scribed line of the protractor, and recording the numerical value alpha, wherein the scribed line parallel to the Z axis corresponds to the zero position of the protractor.

Description

Technical Field

[0001] This utility model relates to the field of blade inspection technology, specifically an auxiliary inspection device for the integrity of the structure of aero-engine directionally solidified blades. Background Technology

[0002] Compared to equiaxed blades, oriented stranded blades for aero-engines have only a few grain boundaries in a direction approximately parallel to the blade's working axis (i.e., the Z-axis). Because transverse grain boundaries are eliminated, the service life and performance of oriented stranded blades are improved to some extent, leading to their widespread application in the aero-engine field. During the manufacturing of oriented stranded blades, acceptance standards require the inspection of the geometric angle between the grain boundaries on the blade surface and the blade's working axis (i.e., the Z-axis). Depending on the location of the grain boundaries, this geometric angle is typically required to be no more than 10–20°.

[0003] However, the shape of aero-engine blades is a three-dimensional curved surface structure, and their working Z-axis usually needs to be calibrated with the help of a coordinate measuring machine. It is difficult to accurately calculate the geometric angle between the grain boundary and the Z-axis under visual conditions. Inspectors usually make judgments based on subjective experience, which may cause quality loss. Utility Model Content

[0004] The purpose of this invention is to provide an auxiliary detection device for the integrity of the structure of directional solidified blades in aero-engines. After fixing multiple scribing templates, marking lines parallel to the Z-axis are made near the location where the grain boundary angle to be measured is to be measured. Finally, a protractor is used to measure the grain boundary angle. The lines parallel to the Z-axis correspond to the zero position of the protractor. The grain boundary angle value α is read from the lines on the protractor and recorded. This invention can solve the problems in the prior art.

[0005] To achieve the above objectives, this utility model provides the following technical solution: an auxiliary detection device for the integrity of the structure of aero-engine directional solidification blades, comprising a blade mold and a scribing template, wherein the blade mold comprises a blade basin, a blade back, and a blade root, the blade basin has an airflow channel inside, and the scribing template is respectively attached and fixed to the blade basin, the blade back, and the blade root;

[0006] Using the above method, after fixing multiple scribing templates, mark the vicinity of the grain boundary angle to be measured with scribing lines parallel to the Z-axis. Finally, use a protractor to measure the grain boundary angle. The scribing line parallel to the Z-axis corresponds to the zero position of the protractor. Read the grain boundary angle value α from the scribing line of the protractor and record it.

[0007] Furthermore, the internal design of the scribing template includes multiple long, narrow, hollowed-out gaps, with a gap width of 3-5m.

[0008] Furthermore, the scribing template is configured as a transparent structure.

[0009] Using the above method, the distribution of grain boundaries on the blade surface can be accurately observed when marking the lines.

[0010] Furthermore, one end of the blade mold is provided with an extension shaft, and the other end of the blade mold is provided with a front shaft, wherein the extension shaft and the front shaft are integrated with the blade mold.

[0011] Furthermore, the blade root is installed below the extension shaft, and the outer surface of the blade root is provided with a capsule groove structure.

[0012] Compared with the prior art, the beneficial effects of this utility model are:

[0013] 1. In this utility model, after fixing multiple scribing templates, marking lines parallel to the Z-axis are made near the location where the grain boundary angle to be measured is to be measured. Finally, a protractor is used to measure the grain boundary where the angle to be measured is to be measured. The lines parallel to the Z-axis correspond to the zero position of the protractor. The grain boundary angle value α is read from the lines of the protractor and recorded. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the leaf basin detection structure of this utility model;

[0015] Figure 2 This is a schematic diagram of the leaf back detection structure of this utility model;

[0016] Figure 3 This is a schematic diagram of the leaf root detection structure of this utility model.

[0017] In the diagram: 1. Leaf-shaped mold; 2. Marking template; 101. Leaf basin; 102. Leaf back; 103. Expansion shaft; 104. Front shaft; 105. Leaf root; 1011. Airflow channel. Detailed Implementation

[0018] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0019] To address the difficulty of accurately calculating the geometric angle between grain boundaries and the Z-axis under visual inspection, inspectors often rely on subjective experience, which can lead to quality slippage. Please refer to [link / reference needed]. Figure 1-3 The present invention provides the following solution:

[0020] Reference Figure 1-2 An auxiliary detection device for the integrity of the structure of aero-engine directional solidification blades is characterized by comprising a blade mold 1 and a scribing template 2. The blade mold 1 includes a blade basin 101, a blade back 102, and a blade root 105. An airflow channel 1011 is provided inside the blade basin 101. The scribing template 2 is attached and fixed to the blade basin 101, the blade back 102, and the blade root 105 respectively. The scribing template 2 is designed with multiple long strip-shaped hollow gaps with a gap width of 3-5m. The scribing template 2 is made of a transparent structure. An extension shaft 103 is provided at one end of the blade mold 1, and a front shaft 104 is provided at the other end of the blade mold 1. The extension shaft 103 and the front shaft 104 are integrated with the blade mold 1.

[0021] In this embodiment, the central axis between the front shaft 104 and the extension shaft 103 is used as the Z-axis. The blade scribing template is installed and fixed through the airflow channel surface, inlet edge, or exhaust edge contour of the blade basin 101 or blade back 102 to ensure better fit between the template and the blade mold 1. The transparent scribing template 2 allows for accurate observation of the grain boundary distribution on the surface of the blade mold 1 when marking the scribing. After fixing multiple scribing templates 2, scribing lines parallel to the Z-axis are marked near the location where the grain boundary angle needs to be measured. Finally, the grain boundary angle needs to be measured using a protractor. The scribing line parallel to the Z-axis corresponds to the zero position of the protractor. The grain boundary angle value α is read from the protractor's scribing line and recorded.

[0022] It should be noted that the error between the outline of the scribing template 2 and the Z-axis of the leaf mold 1 should not exceed 0.5°.

[0023] Reference Figure 1 and Figure 3 The blade root 105 is installed below the extension shaft 103, and the outer surface of the blade root 105 is provided with a capsule groove structure.

[0024] In this embodiment, a conformal template can be manufactured according to the structure of the blade root 105. The scribing template is installed and fixed at the blade root 105, and scribing lines parallel to the Z-axis are marked at the blade root 105. Finally, a protractor is used to measure the angles α, β, and γ between each grain boundary and the scribing lines, and the results are compared with the values ​​specified in the acceptance standard.

[0025] The working principle involves installing and fixing the blade-shaped scribing template through the airflow channel surface, inlet edge, or exhaust edge contour of the blade basin 101 or blade back 102 to ensure better fit between the template and the blade mold 1. The transparent scribing template 2 allows for accurate observation of the grain boundary distribution on the surface of the blade mold 1 during the marking process. After fixing multiple scribing templates 2, scribing lines parallel to the Z-axis are marked near the location where the grain boundary angle needs to be measured. Finally, a protractor is used to measure the grain boundary angle. The scribing line parallel to the Z-axis corresponds to the zero position of the protractor. The grain boundary angle value α is read from the protractor's scribing lines and recorded.

[0026] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0027] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An auxiliary detection device for the structural integrity of directional solidified blades of aero-engines, characterized in that, It includes a leaf-shaped mold (1) and a scribing template (2), wherein the leaf-shaped mold (1) includes a leaf base (101), a leaf back (102) and a leaf root (105), and an airflow channel (1011) is provided inside the leaf base (1011), and the scribing template (2) is attached and fixed to the leaf base (101), the leaf back (102) and the leaf root (105) respectively.

2. The auxiliary detection device for the structural integrity of aero-engine directionally solidified blades according to claim 1, characterized in that: The internal design of the marking template (2) includes multiple long strip-shaped hollow gaps with a gap width of 3-5m.

3. The auxiliary detection device for the structural integrity of aero-engine directionally solidified blades according to claim 1, characterized in that: The scribing template (2) is set to a transparent structure.

4. The auxiliary detection device for the structural integrity of aero-engine directionally solidified blades according to claim 1, characterized in that: One end of the blade mold (1) is provided with an extension shaft (103), and the other end of the blade mold (1) is provided with a front shaft (104). The extension shaft (103) and the front shaft (104) are integrated with the blade mold (1).

5. The auxiliary detection device for the structural integrity of aero-engine directionally solidified blades according to claim 4, characterized in that: The blade root (105) is installed below the extension shaft (103), and the outer surface of the blade root (105) is provided with a capsule groove structure.

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