Method for measuring rotation radius of turbine blade of aircraft auxiliary power device based on mass deviation and unbalanced decoupling

Abstract

The invention relates to an aircraft auxiliary power device turbine blade rotation radius measuring method based on mass deviation and unbalanced decoupling. The invention relates to the technical field of mechanical measurement, a dynamic balancing machine is used for measuring a turbine rotor provided with two blades, and the rotating radius of the turbine blades is reversely deduced and calculated according to the measured unbalance error and the blade mass and blade disc unbalance parameters. According to the method, the unbalance amount of a blade disc is counteracted through a balance weight method, then the blades are weighed, the two blades with the large mass difference are selected to be assembled, the overall unbalance amount of the rotor is obtained through measurement, and finally, the blade rotation radius calculation method of the rotor with the odd number of blades and the blade rotation radius calculation method of the rotor with the even number of blades are deduced respectively. According to the invention, no extra equipment is needed for measurement or scanning, so that the economic cost is saved; and the method has no requirement on the shape of the blade, and is suitable for the blades with various shapes.

Description

Technical Field

[0001] The invention relates to the technical field of mechanical measurement, in particular to a method for measuring the rotation radius of a turbine blade of an aircraft auxiliary power device based on mass deviation and unbalance decoupling. Background Art

[0002] The blade rotation radius refers to the distance from the center of gravity of the blade itself to the center of the rotation axis, which can be used to describe the characteristic size and position of the blade installed on the rotating component. In the field of mechanical engineering, it is very important to measure the blade rotation radius, because the blade rotation radius will affect the overall unbalance error control of the component, and then affect the safe operation of the rotating mechanical component. Especially in turbomachinery, wind turbines, impeller pumps and other equipment. Accurate measurement of the blade rotation radius is crucial for the design, manufacture and maintenance of the performance of these equipment. In the process of stacking and assembling the turbine rotor of the aircraft auxiliary power unit, accurate measurement of the turbine blade rotation radius parameters is conducive to ensuring the matching degree and blade assembly accuracy of the blades, and reducing the abnormal unbalance error caused by the difference in rotation radius. Therefore, it is of great practical engineering significance to study a high-precision and high-efficiency method for measuring the rotation radius of the turbine rotor blades of the aircraft auxiliary power unit.

[0003] The main methods for measuring blade rotation radius are as follows: (1) Optical measurement method. Advanced instruments are used to scan the surface of turbine blades to capture the geometric shape and microscopic details of the blade surface. The collected turbine disk and blade surface data are processed and analyzed by the software of the optical measurement system to obtain the blade rotation radius. This method is usually more accurate, but the cost is also higher; (2) Mechanical measurement method. The blade surface is directly measured by contact measurement tools and then calculated. The method is simple but the accuracy is limited. This method is relatively low-cost and suitable for simple geometric shape measurement. The measurement effect may not be good for blades with complex free-form surfaces or blades with small curvature. The measurement accuracy of this method is difficult to meet the measurement of the rotation radius of high-end turbine blades; (3) Mathematical modeling method. Based on the design parameters and geometric shape of the blade, the rotation radius of the turbine blade is reversely deduced using a mathematical theoretical model. This method relies on an established accurate mathematical model, but in practice, the design model of the measured turbine blade is usually difficult to obtain accurately, and an inaccurate model will lead to large errors in the measurement results. Summary of the invention

[0004] In view of the shortcomings of the prior art, the present invention provides a method for measuring the rotation radius of turbine blades of an aircraft auxiliary power unit based on mass deviation and unbalance decoupling. The present invention uses a dynamic balancing machine to measure a turbine rotor equipped with two blades, and reversely deduce and calculate the rotation radius of the turbine blade based on the measured unbalance error and blade mass and blade disk unbalance parameters. The present invention provides the following technical solutions:

[0005] A method for measuring the rotation radius of a turbine blade of an aircraft auxiliary power unit based on mass deviation and imbalance decoupling, the method comprising the following steps:

[0006] Step 1: Measure the unbalance amount and unbalance angle of the turbine blade disk. After the measurement is completed, add a counterweight in the direction opposite to the unbalance angle to offset the unbalance amount of the blade disk;

[0007] Step 2: Measure the mass of all blades, select two blades with a large mass difference, and establish a mass-diameter product model of the blades to determine the rotation radius of the blades.

[0008] Preferably, the step 2 further comprises:

[0009] After adding the counterweight, re-measure the unbalance amount and unbalance angle of the turbine blade disk, and increase or decrease the counterweight according to the measurement results. Repeat the above process until the unbalance amount of the blade disk is negligible.

[0010] Preferably, when the turbine rotor has an even number of turbine blades, two mortise and tenon positions with a relative angle of 180 degrees are selected, the two blades are respectively mounted on the two mortise and tenons, and the angle of one of the mortise and tenons is set to 0°.

[0011] Preferably, the mass of the blade is set to m, and the rotation radius vector is Theoretical mass-diameter product It is expressed by the following formula:

[0012]

[0013] When the masses of the two blades are m1 and m2 respectively, the rotation radius vectors are and Then the mass-diameter product vector sum of the two blades is expressed by the following formula:

[0014]

[0015] in, That is, the measured overall unbalance of the turbine rotor system;

[0016] The same model of blades has the same rotation radius. When the installation angles of the two blades differ by 180 degrees, according to formula (2):

[0017]

[0018] According to the mathematical relationship, we can get formula (4):

[0019] M=|m1-m2|×r (4)

[0020] Where M is the magnitude of the overall unbalance of the turbine rotor system, and r is the rotation radius of the blade. Further calculation yields equation (5):

[0021]

[0022] For a turbine rotor with an even number of turbine blades, the rotation radius r can be derived and calculated from the rotor unbalance error and the blade mass difference.

[0023] Preferably, for a turbine rotor with an odd number of blades, two relatively farthest tenon groove positions are selected; the number of blades is set to n, and the distance between the two blades is 180°-180° / n.

[0024] Preferably, the masses of the two blades are set to be m1 and m2, and the rotation radius vectors are set to be r1 and r2, respectively. The m1 mass blade is assembled at an angle of 0°, and the unbalance measured after assembly is It is expressed by the following formula:

[0025]

[0026] The same model of blades has the same rotation radius. When the measured unbalance angle is θ, we can get:

[0027]

[0028] Simplify to get the following formula:

[0029]

[0030] Preferably, for a rotor with an odd number of turbine blades, the rotation radius r can be derived and calculated from the rotor imbalance, the imbalance angle, the blade mass difference and the number of blades.

[0031] A system for measuring the rotation radius of a turbine blade of an aircraft auxiliary power unit based on mass deviation and imbalance decoupling, the system comprising:

[0032] A quality measurement module, wherein the quality measurement module measures the quality of all blades of a turbine blade disk of the same model and selects two turbine blades with the largest quality difference;

[0033] An angle measurement module, wherein the angle measurement module measures the unbalance amount and unbalance angle of the turbine blade disk, and after the measurement is completed, a counterweight is added in the direction opposite to the unbalance angle to offset the unbalance amount of the blade disk with the counterweight;

[0034] A calculation module measures the mass of all blades, selects two blades with a large mass difference, establishes a mass-diameter product model of the blades, and determines the rotation radius of the blades.

[0035] A computer-readable storage medium stores a computer program, which is executed by a processor to implement a method for measuring the rotation radius of a turbine blade of an aircraft auxiliary power unit based on mass deviation and imbalance decoupling.

[0036] A computer device comprises a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, a method for measuring the rotation radius of a turbine blade of an aircraft auxiliary power unit based on mass deviation and imbalance decoupling is implemented.

[0037] The present invention has the following beneficial effects:

[0038] Compared with the prior art, the present invention has the following advantages:

[0039] The present invention firstly uses a counterweight method to offset the imbalance of the blade disk, then weighs the blades, selects two blades with a large mass difference for assembly, measures the imbalance of the rotor as a whole, and finally derives the blade rotation radius calculation methods for rotors with odd numbers of blades and rotors with even numbers of blades respectively.

[0040] The present invention does not require the use of other additional equipment for measurement or scanning, thus saving economic costs; and the present invention has no requirements on the shape of the blade, and is applicable to blades of various shapes. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0042] Figure 1 It is a schematic diagram showing the unbalance measurement of two rotor blades when the number of turbine blades is an even number according to the present invention;

[0043] Figure 2 It is a schematic diagram showing the unbalance measurement of two blades when the number of turbine blades is an odd number according to the present invention;

[0044] Figure 3 The present invention shows the measurement process of the turbine blade rotation radius of the aircraft auxiliary power unit based on the decoupling of mass deviation and imbalance. DETAILED DESCRIPTION

[0045] The present invention is described in detail below in conjunction with specific embodiments. Specific embodiment one:

[0047] according to Figures 1 to 3As shown, the specific optimization technical solution adopted by the present invention to solve the above technical problems is: the present invention relates to a method for measuring the rotation radius of turbine blades of an aircraft auxiliary power unit based on mass deviation and imbalance decoupling.

[0048] A method for measuring the rotation radius of a turbine blade of an aircraft auxiliary power unit based on mass deviation and imbalance decoupling, the method comprising the following steps:

[0049] Step 1: Measure the unbalance amount and unbalance angle of the turbine blade disk. After the measurement is completed, add a counterweight in the direction opposite to the unbalance angle to offset the unbalance amount of the blade disk;

[0050] Step 2: Measure the mass of all blades, select two blades with a large mass difference, and establish a mass-diameter product model of the blades to determine the rotation radius of the blades.

[0051] The present invention first uses a counterweight method to offset the imbalance of the blade disk. Then the blades are weighed and two blades with a large mass difference are selected for assembly. The overall imbalance of the rotor is then measured. Finally, the blade rotation radius calculation methods for rotors with odd blades and rotors with even blades are derived respectively, so as to achieve accurate determination of the rotor blade rotation radius and provide reliable data support and technical guarantee for subsequent related processes or equipment operations.

[0052] The present invention does not require the use of other additional equipment for measurement or scanning, thus saving economic costs; and the present invention has no requirements on the shape of the blade, and is applicable to blades of various shapes. Specific embodiment 2:

[0054] The difference between the second embodiment of the present application and the first embodiment is that:

[0055] The step 1 also includes:

[0056] After adding the counterweight, re-measure the unbalance amount and unbalance angle of the turbine blade disk, and increase or decrease the counterweight according to the measurement results. Repeat the above process until the unbalance amount of the blade disk is negligible. Specific embodiment three:

[0058] The difference between the third embodiment of the present application and the second embodiment is that:

[0059] When the turbine rotor has an even number of turbine blades, two mortise positions with an angle of 180 degrees relative to each other are selected, two blades are respectively installed on the two mortise angles, and the angle of one of the mortise angles is set to 0 degrees. Specific embodiment four:

[0061] The difference between the fourth embodiment of the present application and the third embodiment is that:

[0062] Assume the mass of the blade is m and the rotation radius vector is Theoretical mass-diameter product It is expressed by the following formula:

[0063]

[0064] When the masses of the two blades are m1 and m2 respectively, the rotation radius vectors are and Then the mass-diameter product vector sum of the two blades is expressed by the following formula:

[0065]

[0066] in, That is, the measured overall unbalance of the turbine rotor system;

[0067] The same model of blades has the same rotation radius. When the installation angles of the two blades differ by 180 degrees, according to formula (2):

[0068]

[0069] According to the mathematical relationship, we can get formula (4):

[0070] M=|m1-m2|×r (4)

[0071] Where M is the magnitude of the overall unbalance of the turbine rotor system, and r is the rotation radius of the blade. Further calculation yields equation (5):

[0072]

[0073] For a turbine rotor with an even number of turbine blades, the rotation radius r can be derived and calculated from the rotor unbalance error and the blade mass difference. Specific embodiment five:

[0075] The difference between the fifth embodiment of the present invention and the fourth embodiment is that:

[0076] For a turbine rotor with an odd number of blades, two relatively farthest tenon groove positions are selected; the number of blades is set to n, and the distance between the two blades is 180°-180° / n. Specific embodiment six:

[0078] The difference between the sixth embodiment of the present invention and the fifth embodiment is that:

[0079] Assume that the masses of the two blades are m1 and m2, and the rotation radius vectors are r1 and r2, respectively. The m1 mass blade is assembled at an angle of 0°. The unbalance measured after assembly is It is expressed by the following formula:

[0080]

[0081] The same model of blades has the same rotation radius. When the measured unbalance angle is θ, we can get:

[0082]

[0083] Simplify to get the following formula:

[0084] Specific embodiment seven:

[0086] The difference between the seventh embodiment of the present invention and the sixth embodiment is that:

[0087] For a rotor with an odd number of turbine blades, the radius of rotation r can be derived and calculated from the rotor imbalance, imbalance angle, blade mass difference and the number of blades. Specific embodiment eight:

[0089] The difference between the eighth embodiment of the present invention and the seventh embodiment is that:

[0090] The present invention provides a system for measuring the rotation radius of turbine blades of an aircraft auxiliary power unit based on mass deviation and imbalance decoupling, the system comprising:

[0091] A quality measurement module, wherein the quality measurement module measures the quality of all blades of a turbine blade disk of the same model and selects two turbine blades with the largest quality difference;

[0092] An angle measurement module, wherein the angle measurement module measures the unbalance amount and unbalance angle of the turbine blade disk, and after the measurement is completed, a counterweight is added in the direction opposite to the unbalance angle to offset the unbalance amount of the blade disk with the counterweight;

[0093] A calculation module measures the mass of all blades, selects two blades with a large mass difference, establishes a mass-diameter product model of the blades, and determines the rotation radius of the blades.

[0094] The present invention first uses a counterweight method to offset the imbalance of the blade disk. Then the blades are weighed and two blades with a large mass difference are selected for assembly. The overall imbalance of the rotor is then measured. Finally, the blade rotation radius calculation methods for rotors with odd blades and rotors with even blades are derived respectively, so as to achieve accurate determination of the rotor blade rotation radius and provide reliable data support and technical guarantee for subsequent related processes or equipment operations. Specific embodiment nine:

[0096] The difference between the ninth embodiment of the present invention and the eighth embodiment is that:

[0097] The present invention provides a computer-readable storage medium on which a computer program is stored. The program is executed by a processor to implement a method for measuring the rotation radius of a turbine blade of an aircraft auxiliary power unit based on mass deviation and imbalance decoupling.

[0098] The method comprises the following steps:

[0099] Step 1: Measure the unbalance amount and unbalance angle of the turbine blade disk. After the measurement is completed, add a counterweight in the direction opposite to the unbalance angle to offset the unbalance amount of the blade disk;

[0100] Step 2: Measure the mass of all blades, select two blades with a large mass difference, and establish a mass-diameter product model of the blades to determine the rotation radius of the blades.

[0101] The present invention first uses a counterweight method to offset the imbalance of the blade disk. Then the blades are weighed and two blades with a large mass difference are selected for assembly. The overall imbalance of the rotor is then measured. Finally, the blade rotation radius calculation methods for rotors with odd blades and rotors with even blades are derived respectively, so as to achieve accurate determination of the rotor blade rotation radius and provide reliable data support and technical guarantee for subsequent related processes or equipment operations. Specific embodiment ten:

[0103] The difference between the tenth embodiment of the present invention and the ninth embodiment is that:

[0104] The present invention provides a computer device, comprising a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, a method for measuring the rotation radius of a turbine blade of an aircraft auxiliary power unit based on mass deviation and imbalance decoupling is implemented.

[0105] The method comprises the following steps:

[0106] Step 1: Measure the unbalance amount and unbalance angle of the turbine blade disk. After the measurement is completed, add a counterweight in the direction opposite to the unbalance angle to offset the unbalance amount of the blade disk;

[0107] Step 2: Measure the mass of all blades, select two blades with a large mass difference, and establish a mass-diameter product model of the blades to determine the rotation radius of the blades.

[0108] The present invention firstly uses a counterweight method to offset the imbalance of the blade disk, then weighs the blades, selects two blades with a large mass difference for assembly, measures the imbalance of the rotor as a whole, and finally derives the blade rotation radius calculation methods for rotors with odd numbers of blades and rotors with even numbers of blades respectively. Specific embodiment eleven:

[0110] The difference between the eleventh embodiment of the present invention and the tenth embodiment is that:

[0111] The blade rotation radius is the distance from the center of gravity of the blade to the center of the rotation axis. In mechanical engineering, it is very important and will affect the unbalance error of the components and determine the safe operation of the rotating components. Equipment such as turbomachinery are affected by it. When assembling the turbine rotor of the aircraft auxiliary power unit, accurately measuring the blade rotation radius can ensure the blade matching and assembly accuracy and reduce the unbalance error. Therefore, studying high-precision and high-efficiency measurement methods is of practical engineering significance.

[0112] In response to the problems existing in the prior art, the present invention proposes a blade rotation radius measurement method based on the decoupling of blade mass deviation and imbalance. The method uses a dynamic balancing machine to measure a turbine rotor equipped with two blades, and reversely deduce and calculate the rotation radius of the turbine blade based on the measured imbalance error and blade mass and blade disk imbalance parameters.

[0113] The method for measuring the rotation radius of the turbine blade of an aircraft auxiliary power unit based on the decoupling of mass deviation and imbalance is specifically implemented as follows:

[0114] Step 2: Measure the unbalance amount and unbalance angle of the blade disk. After the measurement is completed, add a counterweight in the direction opposite to the unbalance angle to offset the unbalance amount of the blade disk. After the increase, re-measure the unbalance amount and unbalance angle of the blade disk, and increase or decrease the counterweight according to the measurement results. Repeat the above process until the unbalance amount of the blade disk can be ignored.

[0115] First, the blade mass-diameter product model is established. The blade affects the rotor imbalance through its mass-diameter product. The blade mass-diameter product is calculated by multiplying the mass of the blade by the distance from its center of mass to the center of rotation, that is, the rotation radius. Assume that the mass of the blade is m and the rotation radius vector is Theoretical mass-diameter product As shown in formula 1:

[0116]

[0117] For a turbine rotor with an even number of turbine blades, select two opposite tenon positions and install the two blades on the two tenons respectively, and assume that the angle of one of the tenons is 0°, such as Figure 1 shown.

[0118] If the masses of the two blades are m1 and m2 respectively, the rotation radius vectors are and Then the mass-diameter product vector sum of the two blades is as shown in formula (2):

[0119]

[0120] Since the unbalance of the blade disk is compensated, the formula This is the measured overall unbalance of the turbine rotor system. Since the positions of the tenon and the groove are in opposite directions, the directions of the rotation radius vectors are also opposite, and since different blades have the same structure, the rotation radius values ​​are equal. Formula (2) can be simplified as:

[0121]

[0122] According to the mathematical relationship, we can get formula (4):

[0123] M=|m1-m2|×r (4)

[0124] Where M is the magnitude of the overall unbalance of the turbine rotor system, and r is the rotation radius of the blade. Further, we can obtain formula (5):

[0125]

[0126] Therefore, for a turbine rotor with an even number of turbine blades, the rotation radius r can be derived and calculated from the rotor unbalance error and the blade mass difference.

[0127] For turbine rotors with an odd number of blades, select the two farthest relative groove positions. Assuming the number of blades is n, the distance between the two blades is 180°-180° / n, such as Figure 2 shown.

[0128] Assume that the masses of the two blades are m1 and m2, and the rotation radius vectors are r1 and r2, respectively, where the m1 mass blade is assembled at an angle of 0°. The unbalance measured after assembly is Then we can get formula (6):

[0129]

[0130] The theoretically designed rotation radius of blades of the same model is the same. Assuming that the measured unbalance angle is θ, we can get equation (7):

[0131]

[0132] Further simplifying formula (8):

[0133]

[0134] Therefore, for a rotor with an odd number of turbine blades, the radius of rotation r can be derived and calculated from the rotor imbalance, imbalance angle, blade mass difference and the number of blades. Specific embodiment twelve:

[0136] The difference between the twelfth embodiment of the present invention and the eleventh embodiment is that:

[0137] There is a single-stage rotor of an aircraft auxiliary power unit rotor system, which has 40 blades. Now measure the rotation radius of its blades:

[0138] Step 1: First, measure the mass of all blades and number them, then select two blades with a large mass difference. Then measure the unbalance amount and unbalance angle of the blade disk;

[0139] Step 2: Then measure the unbalance amount and unbalance angle of the blade disk, and balance the blade disk to offset the unbalance amount of the blade disk.

[0140] Step 3: Assemble the blades at angles of 0 and 180 degrees, measure the rotor imbalance, and calculate the rotation radius of the rotor blade according to formula (5).

[0141] First, the blade mass-diameter product model is established. The blade affects the rotor imbalance through its mass-diameter product. The blade mass-diameter product is calculated by multiplying the mass of the blade by the distance from its center of mass to the center of rotation, that is, the rotation radius. Assume that the mass of the blade is m and the rotation radius vector is Theoretical mass-diameter product As shown in formula 1:

[0142]

[0143] For a turbine rotor with an even number of turbine blades, select two opposite tenon positions and install the two blades on the two tenons respectively, and assume that the angle of one of the tenons is 0°, such as Figure 1 shown.

[0144] If the masses of the two blades are m1 and m2 respectively, the rotation radius vectors are and Then the mass-diameter product vector sum of the two blades is as shown in formula (2):

[0145]

[0146] Since the unbalance of the blade disk is compensated, M in the formula is the measured unbalance of the turbine rotor system as a whole. Since the positions of the tongue and groove are in opposite directions, the directions of the rotation radius vectors are also opposite, and different blades have the same structure, so the rotation radius values ​​are equal. Formula (2) can be simplified as:

[0147]

[0148] According to the mathematical relationship, we can get formula (4):

[0149] M=|m1-m2|×r (4)

[0150] Where M is the magnitude of the overall unbalance of the turbine rotor system, and r is the rotation radius of the blade. Further, we can obtain formula (5):

[0151]

[0152] Therefore, for a turbine rotor with an even number of turbine blades, the rotation radius r can be derived and calculated from the rotor unbalance error and the blade mass difference.

[0153] The above is only a preferred implementation of a method for measuring the rotation radius of a turbine blade of an aircraft auxiliary power unit based on mass deviation and unbalance decoupling. The protection scope of a method for measuring the rotation radius of a turbine blade of an aircraft auxiliary power unit based on mass deviation and unbalance decoupling is not limited to the above embodiments. All technical solutions under this idea belong to the protection scope of the present invention. It should be pointed out that for those skilled in the art, several improvements and changes without departing from the principle of the present invention should also be regarded as the protection scope of the present invention.

Claims

1. A method for measuring the rotation radius of turbine blades of an aircraft auxiliary power unit based on mass deviation and imbalance decoupling, characterized by: The method comprises the following steps: Step 1: Measure the unbalance amount and unbalance angle of the turbine blade disk. After the measurement is completed, add a counterweight in the direction opposite to the unbalance angle to offset the unbalance amount of the blade disk; Step 2: Measure the mass of all blades, select two blades with a large mass difference, and establish a mass-diameter product model of the blades to determine the rotation radius of the blades.

2. The method according to claim 1, characterized in that: The step 1 also includes: After adding the counterweight, re-measure the unbalance amount and unbalance angle of the turbine blade disk, and increase or decrease the counterweight according to the measurement results. Repeat the above process until the unbalance amount of the blade disk is negligible.

3. The method according to claim 2, characterized in that: When the turbine rotor has an even number of turbine blades, two mortise positions with an angle of 180 degrees relative to each other are selected, two blades are respectively installed on the two mortise angles, and the angle of one of the mortise angles is set to 0 degrees.

4. The method according to claim 3, characterized in that: Assume the mass of the blade is m and the rotation radius vector is Theoretical mass-diameter product It is expressed by the following formula: When the masses of the two blades are m1 and m2 respectively, the rotation radius vectors are and Then the mass-diameter product vector sum of the two blades is expressed by the following formula: in, That is, the measured overall unbalance of the turbine rotor system; The same model of blades has the same rotation radius. When the installation angles of the two blades differ by 180 degrees, according to formula (2): According to the mathematical relationship, we can get formula (4): M=|m1-m2|×r (4) Where M is the magnitude of the overall unbalance of the turbine rotor system, and r is the rotation radius of the blade. Further calculation yields equation (5): For a turbine rotor with an even number of turbine blades, the rotation radius r can be derived and calculated from the rotor unbalance error and the blade mass difference.

5. The method according to claim 2, characterized in that: For a turbine rotor with an odd number of blades, two relatively farthest tenon groove positions are selected; the number of blades is set to n, and the distance between the two blades is 180°-180° / n.

6. The method according to claim 5, characterized in that: Assume that the masses of the two blades are m1 and m2, and the rotation radius vectors are r1 and r2, respectively. The m1 mass blade is assembled at an angle of 0°. The unbalance measured after assembly is It is expressed by the following formula: The same model of blades has the same rotation radius. When the measured unbalance angle is θ, we can get: Simplify to get the following formula:

7. The method according to claim 5, characterized in that: For a rotor with an odd number of turbine blades, the radius of rotation r can be derived and calculated from the rotor imbalance, imbalance angle, blade mass difference and the number of blades.

8. A system for measuring the rotation radius of turbine blades of an aircraft auxiliary power unit based on mass deviation and imbalance decoupling, characterized by: The system comprises: A quality measurement module, wherein the quality measurement module measures the quality of all blades of a turbine blade disk of the same model and selects two turbine blades with the largest quality difference; An angle measurement module, wherein the angle measurement module measures the unbalance amount and unbalance angle of the turbine blade disk, and after the measurement is completed, a counterweight is added in the direction opposite to the unbalance angle to offset the unbalance amount of the blade disk with the counterweight; A calculation module measures the mass of all blades, selects two blades with a large mass difference, establishes a mass-diameter product model of the blades, and determines the rotation radius of the blades.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that: The program is executed by a processor to implement the method according to claims 1-7.

10. A computer device comprising a memory and a processor, wherein the memory stores a computer program, wherein: When the processor executes the computer program, the method of claims 1-7 is implemented.

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