A method for measuring and controlling the interference of vibration-damping bosses on compressor blades

Abstract

The present invention discloses a method for measuring and controlling the interference of a compressor blade vibration damping boss. A set measurement position is used to measure the blade boss before and after assembly. The boss torsion angle before and after assembly is calculated from the measurement results, and the interference of the blade after assembly is calculated from the torsion angle. The interference of each boss contact surface is calculated from the interference of each blade, and the order of blade installation is adjusted according to the interference of the contact surface to ensure that the boss interference meets the requirements. By measuring and calculating the blade boss, the interference value of each blade is confirmed, and according to the interference control method, the normal operation of the compressor blade boss is ensured. The compressor blade vibration damping boss interference measurement and control method can be widely used in the assembly process of aircraft engine compressor blades.

Description

Technical Field

[0001] The present invention relates to the field of structural design and application technology in the field of aero-engines, and in particular provides a method for measuring and controlling the interference of a vibration-damping boss of a compressor blade. Background Art

[0002] During aircraft engine design, to increase engine thrust, a larger diameter compressor can be used to increase engine flow. However, longer compressor blades are more susceptible to blade vibration, potentially leading to blade breakage. To prevent dangerous blade vibration, a shoulder structure is typically designed in the upper and middle portions of the blades. After blades with shoulders are installed in the compressor disk, the shoulders support each other, forming a circumferential ring structure that strengthens the blade. The contact surfaces between the shoulders are coated with a wear-resistant coating, which dampens blade vibration energy through friction between the shoulders. To protect the circumferential ring structure while ensuring adequate frictional damping between the shoulders, the shoulders are typically designed with an interference fit, meaning the total circumferential width of the shoulder is greater than the circumference of the shoulder ring. During assembly, the shoulder interference is typically measured for each blade shoulder and the total width is controlled. However, this method cannot guarantee interference at each shoulder contact surface. When shoulder widths differ significantly between the blade base and blade back, the interference at individual shoulder contact surfaces may be too small, leading to abnormal blade vibration and possible blade breakage.

[0003] People are eager to obtain a compressor blade vibration reduction shoulder interference measurement and control method that has excellent technical effects and can accurately control the interference on each shoulder contact surface to ensure the normal operation of the compressor blade shoulder. Summary of the Invention

[0004] The purpose of this invention is to provide a method for measuring and controlling the interference of compressor blade vibration damping bosses with excellent technical effects. The method accurately controls the interference of each boss contact surface, ensures the normal operation of the compressor blade bosses, and avoids situations where the interference of individual boss contact surfaces is too small.

[0005] The present invention provides a method for measuring and controlling the interference of a compressor blade vibration-damping shoulder. The method comprises the following steps:

[0006] Step 1: Using the standard blade tenon as a reference, calibrate the measuring head to 0 at a distance C from the center of the tenon using a standard blade;

[0007] Step 2: Using the tenon of the blade to be tested as a reference, measure the deviation δ1 between the blade to be tested and the standard blade at a distance C from the center of the tenon;

[0008] Step 3: Assemble the blade to be tested onto the compressor disk and measure the deviation δ2 between the blade to be tested and the standard blade at a distance C from the center of the tenon.

[0009] Step 4: Based on the deviation δ1 between the blade under test and the standard blade in the single-piece state and the deviation δ2 between the blade under test and the standard blade in the assembled state, calculate the shoulder torsion angle α = arctan[(δ1-δ2) / C] before and after assembly;

[0010] Step 5: First, measure the blade shoulder width and calculate the corresponding interference. After the blade is installed on the disk, the entire circle of shoulders contacts each other to form a ring. A theoretical circumference can be calculated based on the shoulder radius. Subtracting the actual shoulder width from the theoretical circumference gives the interference. Assemble the blade to the compressor disk and calculate the shoulder torsion angle α before and after assembly according to steps 1 to 4. Determine the relationship between the shoulder torsion angle α and the interference.

[0011] Step 6: Calculate the interference at the contact surface of adjacent blades to be measured. The interference at the contact surface of adjacent blades to be measured is the sum of the interferences of the two blades forming the contact surface. Calculate the interference at the contact surface of adjacent blades to be measured based on the interference of the shoulder of the adjacent blades to be measured.

[0012] Step 7: If the interference at the contact surface of adjacent blades to be tested exceeds the empirical value of 0.62 to 0.8 mm, the adjacent blades to be tested are replaced to complete the adjustment of the interference of the vibration-damping boss of the compressor blade.

[0013] The key technology of the present invention is to measure the blade boss before and after assembly at a set measurement position, calculate the torsion angle of the blade boss before and after assembly from the measurement results, and calculate the interference of the blade after assembly from the torsion angle. The interference of each boss contact surface is calculated from the interference of each blade, and the blade installation order is adjusted according to the interference of the contact surface to ensure that the boss interference meets the requirements. By measuring and calculating the blade boss, the interference value of each blade is confirmed, and according to the interference control method, the normal operation of the compressor blade boss is ensured. The compressor blade vibration damping boss interference measurement and control method can be widely used in the assembly process of aircraft engine compressor blades. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments:

[0015] Figure 1 Schematic diagram of the compressor blade structure with a shoulder structure;

[0016] Figure 2 Schematic diagram of the structure of installing compressor blades with a shoulder structure into a compressor disk;

[0017] Figure 3 Schematic diagram of compressor blade shoulder width;

[0018] Figure 4 This is a schematic diagram of the compressor blade after assembly;

[0019] Figure 5 This is a schematic diagram of the standard blade shoulder measurement calibration;

[0020] Figure 6 Schematic diagram of the deviation between the blade to be tested and the standard blade in the single-piece state;

[0021] Figure 7 Schematic diagram of the deviation between the blade to be tested and the standard blade in the assembled state;

[0022] Figure 8 Schematic diagram of the shoulder torsion angle before and after blade assembly. DETAILED DESCRIPTION

[0023] Example 1

[0024] In order to avoid dangerous blade vibration, a shoulder 2 structure is usually designed on the upper part of the compressor blade, see the attached Figure 1 After the blades with the shoulder 2 are installed in the compressor disk 3, the blade shoulders 2 support each other to form a circumferential ring structure, see the attached Figure 2 To ensure that the circumferential ring structure is not damaged and that the friction damping between the bosses 2 meets the requirements, the bosses 2 are generally designed as an interference structure, that is, the total circumferential width of the bosses 2 is greater than the circumference of the bosses 2. Figure 3 The width of the shoulder 2 is represented by D, the width of the blade back 12 is represented by A, and the width of the blade base 11 is represented by B. During the assembly process, the width of each blade shoulder 2 is generally measured and the total width is controlled to ensure the interference of the shoulder 2. When the width of the shoulder 3 differs greatly in the direction of the blade base 11 and the blade back 12, the interference of the contact surface of some shoulder 2 may be too small. See the attached Figure 4 , the A size of the middle blade 1 is smaller than the B size, and the A size of the upper and lower blades is larger than the B size. Then after assembly, the contact surface interference of the upper and middle blades will be insufficient, as shown at M in the figure, and the contact surface interference of the middle and lower blades will be larger, as shown at N in the figure.

[0025] The specific steps of the compressor blade vibration damping shoulder interference measurement and control method described in this embodiment are as follows:

[0026] Step 1: Using the standard blade tenon as a reference, calibrate the measuring head to 0 at a distance C from the center of the tenon using the standard blade. Figure 5 ;

[0027] Step 2: Taking the tenon of the blade to be tested 1 as a reference, measure the deviation δ1 between the blade to be tested 1 and the standard blade at a distance C from the center of the tenon;

[0028] Step 3: Assemble the blade 1 to be tested onto the compressor disk, and measure the deviation δ2 between the blade 1 to be tested and the standard blade at a distance C from the center of the tenon.

[0029] Step 4: Based on the deviation δ1 between the blade 1 to be tested and the standard blade in the single-piece state and the deviation δ2 between the blade 1 to be tested and the standard blade in the assembled state, calculate the torsion angle α of the shoulder 2 before and after assembly = arctan[(δ1-δ2) / C];

[0030] Step 5: First, measure the width of the blade shoulder 2 and calculate the corresponding interference. After the blade 1 to be measured is installed on the disk, the entire circle of shoulder 2 contacts each other to form a ring. A theoretical circumference can be calculated based on the radius of shoulder 2. Subtracting the actual shoulder width from the radius gives the interference. Assemble the blade onto the compressor disk 3 and calculate the torsion angle α of shoulder 2 before and after assembly according to steps 1 to 4. Determine the relationship between the torsion angle α and the interference.

[0031] Step 6: Calculate the interference at the contact surface of the adjacent blade to be measured 1. The interference at the contact surface of the adjacent blade to be measured 1 is the sum of the interferences of the two blades forming the contact surface. Calculate the interference at the contact surface of the adjacent blade to be measured based on the interference of the shoulder 2 of the adjacent blade to be measured 1. See the attached Figure 4 , calculate the interference at M based on the upper blade and the middle blade, and calculate the interference at N based on the middle blade and the lower blade.

[0032] Step 7: If the interference at the contact surface of the adjacent blades 1 to be tested exceeds the empirical value of 0.62 to 0.8 mm, the adjacent blades 1 to be tested are replaced to complete the adjustment of the interference of the compressor blade vibration reduction boss.

Claims

1. A method for measuring and controlling the interference of a compressor blade vibration damping shoulder, characterized in that: The specific steps of the compressor blade vibration damping shoulder interference measurement and control method are as follows: Step 1: Using the standard blade tenon as a reference, calibrate the measuring head to 0 at a distance C from the center of the tenon using a standard blade; Step 2: Taking the tenon of the blade to be tested as a reference, measure the deviation δ1 between the blade to be tested (1) in a single-piece state and the standard blade at a distance C from the center of the tenon; Step 3: Assemble the blade to be tested (1) onto the compressor disc (3), and measure the deviation δ2 between the blade to be tested (1) in the assembled state and the standard blade at a distance C from the center of the tenon; Step 4: Based on the deviation δ1 between the blade to be tested (1) in a single-piece state and the standard blade, and the deviation δ2 between the blade to be tested (1) in an assembled state and the standard blade, calculate the torsion angle α of the shoulder (2) before and after assembly = arctan[(δ1-δ2) / C]; Step 5: First measure the width of the blade shoulder (2) and calculate the corresponding interference; determine the relationship between the torsion angle α of the shoulder (2) before and after assembly and the interference; Step 6: Calculate the interference at the contact surface of the adjacent blades to be measured (1), where the interference at the contact surface of the adjacent blades to be measured (1) is the sum of the interferences of the two blades forming the contact surface; Step 7: If the interference at the contact surface of the adjacent blades to be measured (1) exceeds the empirical value of 0.62 to 0.8 mm, the adjacent blades to be measured (1) are replaced to complete the adjustment of the interference of the compressor blade vibration reduction boss (2).

Images