A method for measuring the rotating radius of an aircraft auxiliary power unit turbine blade based on mass deviation and imbalance decoupling

Abstract

The application is a kind of aircraft auxiliary power device turbine blade rotating radius measurement method based on mass deviation and unbalance decoupling. The application relates to the field of mechanical measurement technology, the application uses a dynamic balancing machine to measure a turbine rotor assembled with two blades, and reversely deduces and calculates the rotating radius of the turbine blades according to the measured unbalance error, the blade mass and the unbalance parameters of the blade disc. The application first offsets the unbalance of the blade disc by using the method of counterweight, then weighs the blades, selects two blades with a large mass difference for assembly, measures the unbalance of the whole rotor, and finally deduces the blade rotating radius calculation method of the rotor with an odd number of blades and the rotor with an even number of blades. The application does not need to use other equipment for measurement or scanning, which saves the economic cost; and the application has no requirements on the shape of the blades and is suitable for various shapes of blades.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of mechanical measurement, and is a method for measuring the rotating radius of a turbine blade of an auxiliary power unit of an airplane based on decoupling of mass deviation and imbalance. BACKGROUND

[0002] The rotating radius of a blade refers to the distance from the center of gravity of the blade to the center of the rotating shaft, and can be used to describe the characteristic size and position of the blade installed on a rotating part. In the field of mechanical engineering, it is very important to measure the rotating radius of a blade, because the rotating radius of the blade will affect the imbalance error control of the whole part, and further affect the safe operation of the rotating mechanical part. Especially in turbine machinery, wind turbines, impeller pumps and other equipment. Accurate measurement of the rotating radius of the blade is crucial to the design, manufacture and maintenance of the performance of these devices. In the process of assembling the turbine rotor of the auxiliary power unit of the airplane, accurate measurement of the rotating radius parameter of the turbine blade is conducive to ensuring the matching degree of the blade and the assembly accuracy of the blade, and reducing abnormal imbalance errors caused by differences in the rotating radius. Therefore, it is of great practical engineering significance to study a high-precision and high-efficiency method for measuring the rotating radius of the turbine rotor blade of the auxiliary power unit of the airplane.

[0003] At present, the main methods for measuring the rotating radius of the blade are as follows: (1) optical measurement method. Advanced instruments are used to scan the surface of the turbine blade, and the geometric shape and micro details of the surface of the blade are captured. Through the collected turbine disc and blade surface data, the software of the optical measurement system is used for data processing and analysis, and the rotating radius of the blade is obtained. This method usually has high precision, but the cost is also high; (2) mechanical measurement method. The surface of the blade is directly measured by a contact measurement tool, and then calculated, which is simple but the precision is limited. This method is relatively low in cost and is suitable for simple geometric shape measurement, but the measurement effect may not be good for blades with complex free curved surfaces or small curvature, and the measurement precision of this method is difficult to meet the measurement of the rotating radius of high-end turbine blades; (3) mathematical modeling method. Based on the design parameters and geometric shape of the blade, the rotating radius of the turbine blade is inversely deduced by using a mathematical theoretical model. This method depends on the accurate mathematical model that has been established, but it is difficult to accurately obtain the design model of the turbine blade to be measured in practice, and the inaccuracy of the model will lead to a large error in the measurement result. SUMMARY

[0004] In view of the deficiencies of the prior art, the application provides a method for measuring the rotating radius of a turbine blade of an auxiliary power unit of an airplane based on decoupling of mass deviation and imbalance. The application uses a dynamic balancing machine to measure a turbine rotor assembled with two blades, and inversely deduces and calculates the rotating radius of the turbine blade according to the measured imbalance error, the blade mass and the imbalance parameter of the disc. The application provides the following technical scheme:

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

[0006] Step 1: measuring the imbalance and imbalance angle of the turbine disk, and adding a counterweight in the opposite direction of the imbalance angle after the measurement to offset the imbalance of the disk;

[0007] Step 2: measuring the mass of all blades, and selecting two blades with a large mass difference, and establishing a mass-radius product model to determine the rotating radius of the blades.

[0008] Preferably, the step 2 further comprises:

[0009] After adding the counterweight, the imbalance and imbalance angle of the turbine disk are measured again, and the counterweight is added or reduced according to the measurement results, and the above process is repeated until the imbalance of the disk is negligible.

[0010] Preferably, when the number of turbine blades is even, two opposite 180-degree mortise and tenon positions are selected, two blades are installed on the two mortise and tenon positions respectively, and the angle of one mortise and tenon position is set to 0°.

[0011] Preferably, the mass of the blade is set as m, and the rotating radius vector is Theoretical mass-radius product which is expressed by the following formula:

[0012]

[0013] When the masses of the two blades are m1 and m2 respectively, and the rotating radius vectors are and The mass-radius product vectors of the two blades are expressed by the following formula:

[0014]

[0015] wherein, is the overall imbalance of the turbine rotor system measured;

[0016] The rotating radius of blades of the same type is the same, and when the installation angles of the two blades are different by 180 degrees, formula (2) is obtained according to formula (2):

[0017]

[0018] According to the mathematical relationship, formula (4) is obtained:

[0019] M = |m1-m2| x r (4)

[0020] Wherein, M is the size of the turbine rotor system imbalance, r is the radius of the blade rotation, further calculated formula (5):

[0021]

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

[0023] Preferably, for the turbine rotor with an odd number of blades, two opposite farthest mortise positions are selected; set the number of blades as n, the distance between two blades is 180°-180° / n.

[0024] Preferably, set the mass of two blades as m1 and m2, and the radius of rotation vector as r1 and r2, wherein the m1 mass blade is assembled at 0° angle, and the measured imbalance after assembly is It is expressed by the following formula:

[0025]

[0026] For the same type of blade, the radius of rotation is the same, and when the measured imbalance angle is θ, the following can be obtained:

[0027]

[0028] Simplified to the following formula:

[0029]

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

[0031] A kind of aircraft auxiliary power device turbine blade radius of rotation measurement system based on mass deviation and imbalance decoupling, the system includes:

[0032] The mass measurement module measures the mass of all blades of the same type of turbine blade disc, and selects two turbine blades with the largest mass difference;

[0033] The angle measurement module measures the imbalance and imbalance angle of the turbine blade disc, and after measurement, the counterweight is added in the opposite direction of the imbalance angle to offset the imbalance of the blade disc;

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

[0035] A computer readable storage medium, having stored thereon a computer program, the program being executed by a processor to implement a method for measuring a rotating radius of a turbine blade of an auxiliary power unit of an airplane based on decoupling of mass deviation and imbalance.

[0036] A computer device, comprising a memory and a processor, the memory storing a computer program, and the processor implementing a method for measuring a rotating radius of a turbine blade of an auxiliary power unit of an airplane based on decoupling of mass deviation and imbalance when executing the computer program.

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

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

[0039] The present application first offsets the imbalance of the bladed disc by using a counterweight, then weighs the blades, selects two blades with a large mass difference for assembly, measures the overall imbalance of the rotor, and finally derives the blade rotating radius calculation method of the rotor with an odd number of blades and the rotor with an even number of blades.

[0040] The present application does not need to use additional equipment for measurement or scanning, saving economic cost; and the present application has no requirements for the shape of the blades and is suitable for blades of various shapes. BRIEF DESCRIPTION OF DRAWINGS

[0041] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the following will briefly introduce the drawings needed to be used in the specific embodiments or prior art description. Obviously, the drawings in the following description are some embodiments of the present application, and those skilled in the art can obtain other drawings according to these drawings without creative labor.

[0042] Figure 1 A schematic diagram of measuring imbalance of two blades of a rotor is shown when the number of turbine blades of the present application is even;

[0043] Figure 2 A schematic diagram of measuring imbalance of two blades is shown when the number of turbine blades of the present application is odd;

[0044] Figure 3 A measuring process of a rotating radius of a turbine blade of an auxiliary power unit of an airplane based on decoupling of mass deviation and imbalance of the present application is shown. DETAILED DESCRIPTION

[0045] The present application is described in detail below in combination with specific embodiments. Embodiment One

[0047] According to Figures 1 to 3As shown, the specific optimization technical scheme adopted by the application to solve the above technical problems is: the application relates to a kind of aircraft auxiliary power device turbine blade rotating radius measurement method based on mass deviation and decoupling of unbalance.

[0048] A kind of aircraft auxiliary power device turbine blade rotating radius measurement method based on mass deviation and decoupling of unbalance, the method comprises the following steps:

[0049] Step 1: measure the unbalance amount and unbalance angle of the turbine blade disc, after measurement, increase the counterweight in the opposite direction of the unbalance angle, and use the counterweight to offset the unbalance amount of the blade disc;

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

[0051] Firstly, the application adopts counterweight to offset the unbalance amount of the blade disc. Then, the blades are weighed, and two blades with large mass difference are selected for assembly. Subsequently, the unbalance amount of the rotor is measured. Finally, the blade rotating radius calculation method for the rotor with odd number of blades and the rotor with even number of blades is derived, so as to accurately determine the rotating radius of the rotor blades, and provide reliable data support and technical guarantee for subsequent related processes or equipment operation.

[0052] The application does not need to use additional equipment for measurement or scanning, which saves economic cost;And the application has no requirement for the shape of the blade, and is suitable for blades of various shapes. Specific embodiment two:

[0054] The difference between the embodiment two and the embodiment one of the application is only that:

[0055] The step 1 further comprises:

[0056] After increasing the counterweight, the unbalance amount and unbalance angle of the turbine blade disc are measured again, and the counterweight is increased or decreased according to the measurement result, and the above process is repeated until the unbalance amount of the blade disc is negligible. Specific embodiment three:

[0058] The difference between the embodiment three and the embodiment two of the application is only that:

[0059] When the number of turbine blades is even, select two opposite 180-degree mortise and tenon groove positions, and mount two blades on the two mortise and tenon grooves respectively, and set the angle of one mortise and tenon groove to 0°. Specific embodiment four:

[0061] The difference between the embodiment four and the embodiment three of the application is only that:

[0062] Let the mass of the blade be m, and the rotating radius vector be Theoretical mass-diameter product It is expressed by the following formula:

[0063]

[0064] When the masses of the two blades are m1 and m2, and the rotating radius vectors are r1 and r2, respectively, and The mass-diameter product vector sum of the two blades is expressed by the following formula:

[0065]

[0066] Wherein, That is, the overall imbalance of the turbine rotor system measured;

[0067] For blades of the same type, the rotating radius is the same, and when the installation angles of the two blades differ by 180 degrees, according to formula (2), we have:

[0068]

[0069] According to the mathematical relationship, formula (4) is obtained:

[0070] M = |m1-m2| x r (4)

[0071] Wherein, M is the size of the overall imbalance of the turbine rotor system, and r is the rotating radius of the blade, and further calculation is obtained as formula (5):

[0072]

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

[0075] The difference between the embodiment five and the embodiment four is only that:

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

[0078] The difference between the embodiment six and the embodiment five is only that:

[0079] Let the masses of the two blades be m1 and m2, and the rotating radius vectors be r1 and r2, respectively, wherein the m1 mass blade is assembled at an angle of 0°, and the imbalance measured after assembly is It is expressed by the following formula:

[0080]

[0081] The same type of blade, the radius of rotation is the same, when the measured unbalance angle is θ, then:

[0082]

[0083] Simplify to get the following formula:

[0084] Specific embodiment seven:

[0086] The difference between the embodiment seven and the embodiment six is only:

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

[0089] The difference between the embodiment eight and the embodiment seven is only:

[0090] The application provides a kind of aircraft auxiliary power device turbine blade rotating radius measurement system based on mass deviation and unbalance decoupling, the system comprises:

[0091] The quality measurement module measures the quality of all blades of the same type turbine blade disc, and selects two turbine blades with the largest quality difference;

[0092] The angle measurement module measures the unbalance and unbalance angle of the turbine blade disc, and increases the counterweight in the opposite direction of the unbalance angle after measurement, to offset the unbalance of the blade disc with the counterweight;

[0093] The calculation module measures the quality of all blades, selects two blades with large quality difference, establishes the mass radius product model of the blades, and determines the rotating radius of the blades.

[0094] The application first offsets the unbalance of the blade disc by using the counterweight. Then the blades are weighed, and two blades with large quality difference are selected for assembly. Then the unbalance of the rotor is measured. Finally, the blade rotating radius calculation method for the rotor with an odd number of blades and the rotor with an even number of blades is derived, to realize accurate determination of the rotating radius of the rotor blades, and provide reliable data support and technical support for subsequent related processes or equipment operation. Specific embodiment nine:

[0096] The difference between the embodiment nine and the embodiment eight is only:

[0097] The application provides a computer readable storage medium, which stores a computer program, and the program is executed by a processor to realize a method for measuring a rotating radius of a turbine blade of an auxiliary power unit of an airplane based on decoupling of mass deviation and imbalance.

[0098] The method comprises the following steps:

[0099] Step 1: measuring an imbalance amount and an imbalance angle of a turbine blade disc, adding a counterweight in an opposite direction of the imbalance amount angle after the measurement is completed, and offsetting the imbalance amount of the blade disc by using the counterweight;

[0100] Step 2: measuring the mass of all blades, selecting two blades with a relatively large mass difference, and establishing a mass-diameter product model of the blades to determine the rotating radius of the blades.

[0101] Firstly, the imbalance amount of the blade disc is offset by using the counterweight, then the blades are weighed, two blades with a relatively large mass difference are selected to be assembled, the imbalance amount of the rotor is measured, and finally the calculation methods of the rotating radius of the blades of the rotor with an odd number of blades and the rotor with an even number of blades are derived. Specific embodiment ten:

[0103] The difference between the embodiment ten and the embodiment nine is only that:

[0104] The application provides a computer device, which comprises a memory and a processor, the memory stores a computer program, and the processor realizes a method for measuring a rotating radius of a turbine blade of an auxiliary power unit of an airplane based on decoupling of mass deviation and imbalance when the computer program is executed.

[0105] The method comprises the following steps:

[0106] Step 1: measuring an imbalance amount and an imbalance angle of a turbine blade disc, adding a counterweight in an opposite direction of the imbalance amount angle after the measurement is completed, and offsetting the imbalance amount of the blade disc by using the counterweight;

[0107] Step 2: measuring the mass of all blades, selecting two blades with a relatively large mass difference, and establishing a mass-diameter product model of the blades to determine the rotating radius of the blades.

[0108] Firstly, the imbalance amount of the blade disc is offset by using the counterweight, then the blades are weighed, two blades with a relatively large mass difference are selected to be assembled, the imbalance amount of the rotor is measured, and finally the calculation methods of the rotating radius of the blades of the rotor with an odd number of blades and the rotor with an even number of blades are derived. Embodiment eleven:

[0110] The difference between embodiment eleven and embodiment ten is only that:

[0111] The blade rotation radius is the distance from the center of the rotation axis to the center of gravity of the blade. In mechanical engineering, it is important and can affect the unbalance error of the component, determine the safe operation of the rotating component, and affect the equipment such as turbomachinery. When assembling the turbine rotor of the auxiliary power unit of the aircraft, measuring the blade rotation radius can ensure the matching and assembly precision of the blade and reduce the unbalance error. Therefore, it is of practical engineering significance to study a high-precision and high-efficiency measurement method.

[0112] In view of the problems existing in the prior art, the present application provides a blade rotation radius measurement method based on decoupling of blade mass deviation and unbalance. The method uses a dynamic balancing machine to measure a turbine rotor assembled with two blades, and reversely deduces and calculates the rotation radius of the turbine blade according to the measured unbalance error, the blade mass and the unbalance amount parameters of the blade disc.

[0113] The specific implementation method of the aircraft auxiliary power unit turbine blade rotation radius measurement method based on decoupling of mass deviation and unbalance is as follows:

[0114] Step two, measure the unbalance amount and unbalance angle of the blade disc. After the measurement is completed, add a counterweight in the opposite direction of the unbalance amount angle, and use the counterweight to offset the unbalance amount of the blade disc. After adding, the unbalance amount and unbalance angle of the blade disc are measured again, and the counterweight is added or reduced according to the measurement result. Repeat the above process until the unbalance amount of the blade disc can be ignored.

[0115] First, a blade mass-radius product model is established. The blade affects the rotor unbalance through its mass-radius product. The calculation method of the blade mass-radius product is to multiply the mass of the blade by the distance from the center of mass to the rotation center, that is, the rotation radius. Assuming that the mass of the blade is m, and the rotation radius vector is Theoretical mass-radius product As shown in formula 1:

[0116]

[0117] For a turbine rotor with an even number of turbine blades, select two opposite mortise and tenon groove positions, and assemble two blades on the two mortise and tenon grooves, and assume that the mortise and tenon groove angle of one of them is 0°, as shown in Figure 1 .

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

[0119]

[0120] Since the unbalance of the blade disc is compensated, the formula is The whole unbalance of the turbine rotor system is measured. Since the direction of the mortise and tenon is opposite, the direction of the rotating radius vector is also opposite, and the rotating radius of different blades is equal. The formula (2) can be simplified as:

[0121]

[0122] According to the mathematical relationship, the formula (4) is obtained:

[0123] M = |m1-m2| x r (4)

[0124] In the formula, M is the size of the whole unbalance of the turbine rotor system, and r is the rotating radius of the blade. Further, the formula (5) is obtained:

[0125]

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

[0127] For the turbine rotor with an odd number of blades, the positions of two opposite mortises and tenons are selected. Assuming that the number of blades is n, the distance between two blades is 180°-180° / n, as shown in Figure 2 .

[0128] Assuming that the masses of the two blades are m1 and m2, and the rotating radius vectors are r1 and r2, respectively, wherein the m1 mass blade is assembled at 0° angle. The measured unbalance after assembly is The formula (6) is obtained:

[0129]

[0130] The rotating radius of the same type of blade is the same in the theoretical design. Assuming that the measured unbalance angle is θ, the formula (7) is obtained:

[0131]

[0132] Further simplification obtains the formula (8):

[0133]

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

[0136] Embodiment twelve of the present application differs from embodiment eleven only in that:

[0137] There is a single stage rotor of an aircraft auxiliary power unit rotor system, which has 40 blades. The rotating radius of the blades is now measured:

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

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

[0140] Step 3: Assemble the blades at 0 degrees and 180 degrees, measure the rotor unbalance amount, and calculate the rotating radius of the rotor blades according to equation (5).

[0141] First, a mass-radius product model of the blades is established. The blades affect the rotor unbalance through their mass-radius product. The calculation method of the mass-radius product of the blades is to multiply the mass of the blades by the distance from the center of mass to the center of rotation, i.e. the rotating radius. Assuming the mass of the blades is m, and the rotating radius vector is Theoretical mass-radius product As shown in equation 1:

[0142]

[0143] For a turbine rotor with an even number of turbine blades, two opposite mortise and tenon positions are selected, and two blades are assembled into the two mortise and tenon positions, with one of the mortise and tenon positions being 0°, as shown in Figure 1 .

[0144] If the masses of the two blades are m1 and m2, and the rotating radius vectors are and The mass-radius product vector sum of the two blades is shown in equation (2):

[0145]

[0146] Since the unbalance amount of the disk is compensated, M in the equation is the overall unbalance amount of the turbine rotor system measured. Since the positions of the mortise and tenon are opposite, the directions of the rotating radius vectors are also opposite, and since the structures of different blades are the same, the values of the rotating radius are equal. Equation (2) can be simplified as:

[0147]

[0148] According to the mathematical relationship, equation (4) can be obtained:

[0149] M = |m1-m2| x r (4)

[0150] Where M is the magnitude of the overall imbalance 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 merely a preferred embodiment of a method for measuring the rotation radius of aircraft auxiliary power unit turbine blades based on mass deviation and imbalance decoupling. The scope of protection for a method for measuring the rotation radius of aircraft auxiliary power unit turbine blades based on mass deviation and imbalance decoupling is not limited to the above embodiment; all technical solutions based on this concept fall within the scope of protection of the present invention. It should be noted that improvements and variations that do not depart from the principles of the present invention, as known to those skilled in the art, should also be considered within the scope of protection of the present invention.

Claims

1. A method for measuring the rotating radius of an aircraft auxiliary power unit turbine blade based on decoupling of mass bias and imbalance, characterized in that: The method comprises the following steps: Step 1: measuring the unbalance and the unbalance angle of the turbine disc, and adding the counterweight in the opposite direction of the unbalance angle after the measurement to offset the unbalance of the disc; Step 2: measuring the mass of all the blades, and selecting two blades with the largest mass difference, and establishing a mass-radius product model to determine the rotating radius of the blades.

2. The method of claim 1, wherein: The step 1 further comprises: After adding the counterweight, the unbalance and the unbalance angle of the turbine disc are measured again, and the counterweight is added or reduced according to the measurement results, and the above process is repeated until the unbalance of the disc is negligible.

3. The method according to claim 2, characterized in that: for the turbine rotor with an even number of turbine blades, two mortise and tenon joints with an angle of 180 degrees are selected, and two blades are installed in the two mortise and tenon joints respectively, and the angle of one mortise and tenon joint is set to 0 degrees.

4. The method according to claim 3, characterized in that: The mass of the blade is set as m, and the radius vector of rotation is Theoretical mass diameter product This is expressed by the following equation: When the masses of the two blades are m1 and m2, and the radius vectors of rotation are and the mass-radius product vectors of the two blades are expressed by the following equation: wherein, i.e. the overall imbalance of the turbine rotor system as measured; for the same type of blades, the rotating radius is the same, and when the installation angles of the two blades are different by 180 degrees, formula (2) is obtained according to the formula (2): According to the mathematical relationship, formula (4) is obtained: M = |m1-m2| x r (4) wherein M is the size of the overall unbalance of the turbine rotor system, and r is the rotating radius of the blades, and formula (5) is further calculated: for the turbine rotor with an even number of turbine blades, the rotating radius r can be calculated according to the rotor unbalance error and the mass difference of the blades.

5. The method according to claim 2, characterized in that: for the turbine rotor with an odd number of turbine blades, two mortise and tenon joints with the farthest distance are selected; and the number of blades is n, and the distance between the two blades is 180 degrees-180 degrees / n.

6. The method according to claim 5, characterized in that: Let the mass of the two blades be m1 and m2, and the radius vectors of rotation be r1 and r2, respectively, where the blade of mass m1 is assembled at an angle of 0°, and the measured unbalance after assembly is This is expressed by the following equation: for the same type of blades, the rotating radius is the same, and when the measured unbalance angle is θ, the following formula is obtained: and the following formula is obtained by simplifying:

7. The method according to claim 5, characterized in that: for the rotor with an odd number of turbine blades, the rotating radius r can be calculated according to the rotor unbalance, the unbalance angle, the mass difference of the blades and the number of blades.

8. An aircraft auxiliary power unit turbine blade rotational radius measurement system based on mass bias and imbalance decoupling, characterized by: The system comprises: a mass measurement module, which measures the mass of all the blades of the same type of turbine disc, and selects two turbine blades with the largest mass difference; an angle measurement module, which measures the unbalance and the unbalance angle of the turbine disc, and adds the counterweight in the opposite direction of the unbalance angle after the measurement to offset the unbalance of the disc; a calculation module, which measures the mass of all the blades, selects two blades with the largest mass difference, and establishes a mass-radius product model to determine the rotating radius of the blades.

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

10. A computer device comprising a memory and a processor, the memory storing a computer program, characterized in that: The processor executes the computer program to implement the method of claims 1-7.

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