Computing method for two-dimensional strength of moving blade of gas compressor

Abstract

The invention discloses a gas compressor moving blade two-dimensional strength calculation method which comprises the following steps: S1, fitting section coordinate point data of a gas compressor moving blade in a segmented manner, and fitting a function f (x); s2, encrypting each arc section according to the fitting function f (x); s3, calculating a cross section area Aea, a minimum main inertia moment (Ix0), a maximum main inertia moment (Iy0), a cross section centroid C coordinate Gx and a cross section centroid C coordinate Gy according to the encrypted array; s4, calculating the vector of each coordinate point of the cross section relative to the centroid C of the cross section # imgabs0 #, calculating the force arms A and B of each coordinate point of the cross section relative to the maximum and minimum main inertia axes, and calculating the coordinates xE and yE of the centrifugal force of the blade profile above the cross section at the projection point E of the cross section; calculating the vector of the projection point E relative to the section centroid C; 1. Calculating the force arms P and Q of the projection point E relative to the minimum main inertia axis and the maximum main inertia axis; and S5, calculating section centrifugal tensile stress sigma t, airflow bending stress sigma s and centrifugal bending stress sigma c. The method has the advantages of no need of manual intervention, high calculation efficiency and high calculation accuracy.

Description

Technical Field

[0001] The invention belongs to the field of gas turbine compressor moving blade strength calculation, in particular to a two-dimensional strength calculation method for compressor moving blades. Background Art

[0002] Compressor blades are a key component of gas turbines. Their function is to accelerate, pressurize, and heat the air, subjecting them to loads such as centrifugal forces, airflow forces, and cyclic excitation forces. The operating environment of compressor blades is complex, and their reliability directly impacts the safe operation of the gas turbine. Because compressor blades are subjected to high-frequency loads over long periods of time, they are susceptible to fatigue fracture. Therefore, accurate calculation of blade forces and a safety margin must be incorporated into the initial design phase of the compressor blades.

[0003] Fast and accurate strength calculation is the key to reducing the design cycle of compressor rotor blades. Traditional calculation methods have the following problems:

[0004] First, traditional calculation methods can only process one section of data at a time; it is impossible to achieve batch parallel calculation of multiple sections, resulting in long calculation cycles and low calculation efficiency.

[0005] Furthermore, the calculation of cross-sectional area, centroid, moment of inertia, and lever arm based on existing cross-sectional coordinate points results in large errors and requires the use of different specialized transfer components. Cross-sectional parameters (area, centroid, moment of inertia, etc.) must be calculated step by step using different specialized software, resulting in low system integration and complex data exchange.

[0006] Furthermore, the degree of manual intervention is high, and the sign of the data requires manual judgment. This subjective judgment based on experience can easily lead to incorrect moment polarity. The lack of standardization in manual operation procedures introduces random errors, resulting in poor repeatability of the calculation results.

[0007] Therefore, the traditional method for calculating the strength of compressor rotor blades is inefficient and prone to errors.

[0008] In view of the above shortcomings, it is necessary to provide a calculation method based on a programming language that can process multiple cross-sectional data simultaneously, use fitting functions to segmentally fit and encrypt the cross-sectional data to obtain coordinate point data that approximates the true curve, so that the calculation of cross-sectional area, centroid, moment of inertia and lever arm is fast and accurate without manual intervention, and the positive and negative signs of each data can be correctly judged through vector calculation. Summary of the Invention

[0009] The purpose of the present invention is to provide a two-dimensional strength calculation method for compressor rotor blades which does not require manual intervention and has high calculation efficiency and high calculation accuracy in order to address the deficiencies of the existing technology.

[0010] The technical objectives of the present invention are achieved through the following technical solutions:

[0011] A method for calculating the two-dimensional strength of a compressor rotor blade comprises the following steps:

[0012] S1, segmented fitting of compressor rotor blade cross-section coordinate data, fitting function f(x);

[0013] S2, encrypt each arc segment according to the fitting function f(x) to obtain the coordinate point data that approximates the true curve;

[0014] S3, calculate the cross-sectional area Aea and the minimum principal moment of inertia I according to the encrypted array x0 , maximum principal moment of inertia I y0 And the coordinates of the cross-section centroid C G x and G y ;

[0015] S4, calculate the vector of each coordinate point of the cross section relative to the cross section centroid C Calculate the force arm A of the section coordinate point relative to the maximum principal inertia axis, calculate the force arm B of the section coordinate point relative to the minimum principal inertia axis, and calculate the coordinate x of the centrifugal force of the blade above the section at the section projection point E. E and y E , calculate the vector of the projection point E relative to the cross-section centroid C Calculate the moment arms P and Q of the projection point E relative to the minimum and maximum principal inertia axes;

[0016] S41, Calculate airflow force Bending moments M1 and M2 generated about the minimum and maximum principal axes of inertia of the cross section;

[0017] S42, calculate the bending moments M3 and M4 generated by the centrifugal force C of the blade above the section relative to the minimum and maximum principal inertia axes of the section;

[0018] S5, calculate the centrifugal tensile stress σ at different cross-section positions based on the centrifugal force, principal moment of inertia, lever arm and bending moment of the blade t , airflow bending stress σ s and centrifugal bending stress σ c .

[0019] Furthermore, the calculation formula of the fitting function f(x) in step S1 is as follows:

[0020] y(i)=aerx(i)

[0021] or

[0022]

[0023] Where a and r are the coefficients of the fitting function.

[0024] Furthermore, in step S2, each arc segment is encrypted using uniform encryption.

[0025] Furthermore, the vector of the cross-section coordinate point P relative to the cross-section centroid C in step S4 is The calculation formula is as follows:

[0026]

[0027] Among them, G x is the X coordinate of the cross-section centroid C, G y is the y coordinate of the centroid C of the cross section.

[0028] Furthermore, the calculation formulas for calculating the moment arm A and the moment arm B of the cross-section coordinate point P relative to the minimum principal inertia axis and the maximum principal inertia axis in step S4 are as follows:

[0029]

[0030] in, is the unit vector in the positive direction of the minimum principal inertia axis, is the unit vector in the positive direction of the maximum principal inertia axis, and a0 is the rotation angle of the minimum principal inertia axis relative to the x-axis.

[0031] Furthermore, in step S4, the centrifugal force C of the blade profile above the cross section is calculated using the following formula for the coordinate of the cross section projection point E:

[0032]

[0033] Among them, b is the blade installation value, R c R is the distance between the analysis section and the axis of rotation; b is the distance from the center of gravity of the blade above the cross section to the axis of rotation; yb is the y coordinate of the center of gravity of the blade above the cross section.

[0034] Furthermore, in step S4, the centrifugal force C of the blade above the cross section is calculated at the cross section projection point E relative to the cross section centroid C. The formulas for calculating the moment arms P and Q of the projection point E relative to the minimum and maximum principal inertia axes of the cross section are as follows:

[0035]

[0036] Among them, x E is the x coordinate of point E, y E is the y coordinate of point E.

[0037] Furthermore, the airflow force in step S41 The calculation formulas for the bending moments M1 and M2 relative to the minimum and maximum principal inertia axes of the cross section are as follows:

[0038]

[0039] in, is the blade airflow force vector, F x F is the airflow force x axial force, y is the y-axial component of the airflow force.

[0040] Furthermore, the calculation formulas for the centrifugal force C of the blade above the cross section calculated in step S42 are as follows:

[0041] M3=C×P=C×(-(xE-Gx)sin(a0)+(yE-Gy)cos(a0))

[0042] M4=C×Q=C×((xE-Gx)cos(a0)+(yE-Gy)sin(a0)).

[0043] Furthermore, in step S5, the cross-sectional centrifugal tensile stress σ is calculated. t , airflow bending stress σ s and centrifugal bending stress σ c The calculation formula is as follows:

[0044]

[0045] Compared with the prior art, the present invention has the following beneficial effects:

[0046] The present invention is based on a programming language that can simultaneously process multiple cross-sectional data. It uses a fitting function to segmentally fit and encrypt the cross-sectional data to obtain coordinate point data that approximates the true curve. This allows for rapid and accurate calculation of cross-sectional area, centroid, moment of inertia, and lever arm without manual intervention. Furthermore, the positive and negative signs of each data can be correctly determined through vector calculation. The present invention has the advantages of requiring no manual intervention, high computational efficiency, and high computational accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] Figure 1 It is a schematic flow diagram of the present invention;

[0048] Figure 2 It is the calculation diagram of the airflow bending stress of the airflow force in the analysis section;

[0049] Figure 3 is the relationship between the blade profile installation value and the centrifugal force at the projection point of the analysis section;

[0050] Figure 4 It is the calculation diagram of the force arm of the centrifugal force at the projection point of the analysis section; DETAILED DESCRIPTION

[0051] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings herein can be arranged and designed in various different configurations.

[0052] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention as claimed, but rather merely represents selected embodiments of the present invention. All other embodiments derived by persons of ordinary skill in the art based on the embodiments of the present invention without creative effort shall fall within the scope of protection of the present invention.

[0053] It should be noted that similar reference numerals and letters represent similar items in the following drawings. Therefore, once an item is defined in one drawing, it does not need to be further defined or explained in subsequent drawings. In addition, the terms "first," "second," etc. are used only to distinguish the descriptions and are not to be understood as indicating or implying relative importance.

[0054] Any feature disclosed in this specification, unless otherwise stated, may be replaced by other equivalent or similar alternative features, that is, unless otherwise stated, each feature is just an example of a series of equivalent or similar features.

[0055] like Figure 1 — Figure 4 As shown, a two-dimensional strength calculation method for compressor rotor blades is implemented by the following steps:

[0056] S1, input the mass and center of gravity coordinates above the cross section, and segmentally fit the blade profile coordinates. In the specific implementation, segmentally fit the compressor rotor blade cross section coordinate point data, and fit the function f(x);

[0057] S2, encrypting the cross-sectional blade profile data according to the fitting function. In specific implementation, each arc segment is encrypted according to the fitting function f(x) to obtain coordinate point data that approximates the true curve;

[0058] S3, then calculate the cross-sectional area, moment of inertia, principal moment of inertia, product of inertia and cross-sectional centroid coordinates. In the specific implementation, the cross-sectional area Aea, the minimum principal moment of inertia I are calculated based on the encrypted array. x0 , maximum principal moment of inertia I y0 And the coordinates of the cross-section centroid C G x and G y ;

[0059] S4, then input the initial blade installation value, calculate the vector of the cross-section coordinate point relative to the cross-section centroid, and calculate the force arm of the cross-section coordinate point relative to the main inertia axis. In the specific implementation, calculate the vector of each cross-section coordinate point relative to the cross-section centroid C. Calculate the force arm A of the section coordinate point relative to the maximum principal inertia axis; calculate the force arm B of the section coordinate point relative to the minimum principal inertia axis; calculate the coordinate x of the centrifugal force of the blade above the section at the section projection point E E and y E , calculate the vector of the projection point E relative to the cross-section centroid C Calculate the moment arms P and Q of the projection point E relative to the minimum and maximum principal inertia axes;

[0060] S41, Calculate airflow force Bending moments M1 and M2 generated about the minimum and maximum principal axes of inertia of the cross section;

[0061] S42, calculate the bending moments M3 and M4 generated by the centrifugal force C of the blade above the section relative to the minimum and maximum principal inertia axes of the section;

[0062] S5, finally calculate the centrifugal tensile stress, centrifugal bending stress, airflow bending stress and the optimal blade installation value. In the specific implementation, the centrifugal tensile stress σ at different cross-section positions is calculated based on the centrifugal force, principal moment of inertia, force arm and bending moment of the blade. t , airflow bending stress σ s and centrifugal bending stress σ c .

[0063] This calculation method, based on a programming language, can simultaneously process multiple cross-sectional data. It uses a fitting function to segment and encrypt the cross-sectional data to obtain coordinate point data that approximates the true curve. This allows for rapid and accurate calculation of cross-sectional area, centroid, moment of inertia, and moment arm without manual intervention. Furthermore, the positive and negative signs of each data point can be correctly determined through vector calculation. This calculation method has the advantages of requiring no manual intervention, high computational efficiency, and high accuracy.

[0064] In the above specific design, the specific design of relevant parameters is as follows:

[0065] In step S1, the calculation formula of the fitting function f(x) is as follows:

[0066] y(i)=aerx(i)

[0067] or

[0068]

[0069] Where a and r are the coefficients of the fitting function, and the exponential fitting function is the preferred option.

[0070] The discrete cross-sectional coordinate points are segmented and fitted with continuous functions (exponential or fractional functions) to eliminate the discrete errors of the original data. This technical measure can eliminate discrete errors; by fitting discrete coordinate points with continuous functions, geometric shape distortion caused by the sparse original data is reduced, and the geometric accuracy of subsequent calculations is improved. It can flexibly adapt to complex cross-sections; exponential functions are suitable for smooth contours (such as the blade root area), and fractional functions are suitable for areas with high curvature (such as the blade tip), enhancing adaptability to different blade cross-sections. It can also be processed automatically; the program automatically selects the optimal fitting function, avoiding fitting deviations caused by manual intervention.

[0071] Furthermore, in step S2, uniform encryption is preferably used for the encryption of each arc segment. High-density coordinate points are uniformly generated on the fitting curve. After encryption, the data points are closer to the true curve, and the calculation errors of parameters such as the moment of inertia and the centroid can be reduced to less than 0.5%. The uniform encryption rules are unified, eliminating the randomness of manually selecting encryption points and ensuring the repeatability of the results. It is suitable for simultaneous encryption of multiple sections and significantly shortens the preprocessing time. The adoption of this technical measure has the advantages of improving accuracy and significantly improving efficiency.

[0072] Furthermore, in step S3, the calculation formulas for the moment of inertia, product of inertia, and cross-sectional area are as follows:

[0073]

[0074] Among them, m is the total number of points after cross-section coordinate points are encrypted, I x is the moment of inertia relative to the x-axis, I y is the moment of inertia relative to the y-axis, I xy is the product of inertia, x (i) x-coordinate, y-coordinate of the section point (i) The y-coordinate of the cross-section point, Aear is the cross-section area.

[0075] The moment of inertia (I x , I y ) and product of inertia (I xy The accuracy of moment of inertia calculations is significantly improved (error <1%) based on piecewise integration of encrypted data. The program directly processes multi-section data in batches, eliminating the need for manual formula input. This technology effectively improves calculation accuracy and efficiency.

[0076] Furthermore, in step S3, the angle between the minimum inertia axis and the x-axis and the principal moment of inertia are calculated as follows:

[0077]

[0078] Where a0 is the angle between the minimum principal inertia axis and the x-axis.

[0079] By determining the direction of the principal inertia axes through eigenvalue decomposition, manual judgment errors are eliminated; bending moments and stresses are calculated directly based on the principal moments of inertia, avoiding complex coordinate system transformations; and the proposed method has good anti-interference and strong robustness. This technical measure can further improve computational efficiency and accuracy.

[0080] Further, such as Figure 2 As shown, in step S4, the vector of the cross-section coordinate point P relative to the cross-section centroid C is The calculation formula is as follows:

[0081]

[0082] Among them, G x is the x-coordinate of the cross-section centroid C, G y is the y coordinate of the centroid C of the cross section.

[0083] like Figure 2 As shown, in step S4, the cross-sectional coordinate point P is calculated relative to the minimum principal inertia axis and the maximum principal inertia axis.

[0084] The calculation formulas for the shaft's lever arm A and lever arm B are as follows:

[0085]

[0086] in, is the unit vector in the positive direction of the minimum principal inertia axis, is the unit vector in the positive direction of the maximum principal inertia axis, and a0 is the rotation angle of the minimum principal inertia axis relative to the x-axis.

[0087] Step S4 automatically determines the direction (sign) of the moment arm through vector dot products, avoiding manual misjudgment. This method is applicable to arbitrary cross-sectional shapes (such as twisted blades) and supports complex geometric analysis. It can simultaneously calculate moment arms for multiple loads, including centrifugal and airflow forces. This technical approach can further improve computational accuracy and efficiency.

[0088] Further, such as Figure 3 As shown, in step S4, the centrifugal force C of the blade above the cross section is calculated at the coordinate of the cross section projection point E as follows:

[0089]

[0090] b is the blade installation value, R c R is the distance between the analysis section and the axis of rotation. b y is the distance from the center of gravity of the blade above the cross section to the axis of rotation. b is the y-coordinate of the centroid of the blade above the cross section.

[0091] This calculation formula can accurately calculate the position of the centrifugal force at the cross-sectional projection point, which is crucial for the design and analysis of blade profiles. Accurate calculation results help engineers understand the performance of the blade profile more accurately, thereby making more reasonable designs. In engineering design, the ability to quickly and accurately calculate the centrifugal force position greatly simplifies the design process. Engineers can optimize the blade profile design based on these precise calculation results to improve work efficiency. By calculating and analyzing the centrifugal force distribution of the blade profile, the blade profile design can be further optimized, thereby improving the overall performance and efficiency of the equipment. At the same time, understanding the centrifugal force distribution of the blade profile at different positions also helps to ensure the safety of the equipment during operation and avoid damage caused by excessive centrifugal force. The adoption of this technical measure has important application value in engineering design and analysis. It not only improves the accuracy and efficiency of the calculation, but also helps to optimize equipment design and enhance equipment safety.

[0092] Further, such as Figure 4 As shown, in step S4, the centrifugal force C of the blade above the cross section is calculated at the cross section projection point E relative to the cross section centroid C. The formulas for calculating the moment arms P and Q of the projection point E relative to the minimum and maximum principal inertia axes of the cross section are as follows:

[0093]

[0094] Among them, x E is the x coordinate of point E, y E is the y coordinate of point E.

[0095] The position of the centrifugal force is projected onto the principal inertia axis through P and Q, respectively reflecting the contribution of the centrifugal force to the bending moment in the direction of the strongest bending stiffness of the section (maximum principal inertia axis) and the direction of the weakest bending stiffness (minimum principal inertia axis).

[0096] By vector Accurately describe the geometric relationship between the centrifugal force application point and the centroid, avoiding deviations in bending moment calculations caused by coordinate conversion errors in traditional methods. Decomposing the moment arms P and Q along the principal inertia axes directly reflects the actual bending capacity of the section, ensuring the physical meaning of the bending moment calculation is clear and reducing numerical errors.

[0097] The direction (sign) of the lever arm is automatically determined through vector dot products, eliminating manual errors (such as misjudging tensile stress as compressive stress). All parameters are derived through formula chains, eliminating reliance on multiple software or manual intervention, and improving the standardization and repeatability of the calculation process.

[0098] P and Q quantify the bending moment components of the centrifugal force in the maximum and minimum bending directions, respectively. These components can be superimposed with the airflow bending moment to enable comprehensive stress analysis under multiple combined loads. This method is suitable for complex scenarios such as high-speed rotation, variable operating conditions (such as start-stop and load fluctuations), and accurately assesses the impact of centrifugal force on blade dynamic stability.

[0099] By comparing the values of P and Q, the weak direction of the cross-section bending stiffness (such as the direction of the minimum principal inertia axis) can be identified, guiding local structural strengthening (such as increasing material thickness or adjusting the geometric shape).

[0100] By combining different blade installation values (such as the position of projection point E), the optimal centrifugal force distribution is calculated to balance safety and lightweight requirements.

[0101] By adopting this technical measure, the accuracy, efficiency and reliability of blade strength calculations can be significantly improved through precise geometric modeling, automated symbol determination and refined load decomposition, providing key technical support for moving blade design.

[0102] Further, such as Figure 2 As shown, in step S41, the airflow force The calculation formulas for the bending moments M1 and M2 relative to the minimum and maximum principal inertia axes of the cross section are as follows:

[0103]

[0104] in, is the blade airflow force vector, F x F is the airflow force x axial force, y is the y-axial component of the airflow force.

[0105] like Figure 4 As shown, in step S42, the centrifugal force C of the blade above the cross section is calculated with respect to the bending moments M3 and M4 of the cross section's minimum principal inertia axis and maximum principal inertia axis as follows:

[0106] M3=C×P=C×(-(xE-Gx)sin(a0)+(yE-Gy)cos(a0))

[0107] M4=C×Q=C×((xE-Gx)cos(a0)+(yE-Gy)sin(a0));

[0108] Through the calculation formula of steps S41 and S42; the airflow force Decompose the centrifugal force C along the principal inertia axes to clearly identify the bending moment contributions in each direction. Calculate stresses using weighted principal moments of inertia to reflect the actual bending capacity of the cross-section. Independently analyze the bending moment distribution for different load conditions (e.g., startup, steady-state, transient).

[0109] Furthermore, in step S5, the cross-sectional centrifugal tensile stress σt, the airflow bending stress σs and the centrifugal bending stress σc are calculated using the following formulas:

[0110]

[0111] Different moving blade installation values correspond to different centrifugal tensile stress σt, airflow bending stress σs and centrifugal bending stress σc, and the optimal blade installation value can be obtained.

[0112] By calculating each stress component in real time, potential danger areas (such as high stress concentration areas) can be quickly identified. Combined with the stress comparison of different blade installation values b, the optimal blade geometry parameters can be determined.

[0113] The technical solutions provided by the embodiments of the present invention are introduced in detail above. Specific examples are used herein to illustrate the principles and implementation methods of the embodiments of the present invention. The description of the above embodiments is only applicable to help understand the principles of the embodiments of the present invention. At the same time, for those skilled in the art, according to the embodiments of the present invention, there may be changes in the specific implementation methods and application scopes. In summary, the contents of this specification should not be understood as limiting the present invention.

Claims

1. A method for calculating the two-dimensional strength of a compressor rotor blade, characterized in that: The following steps are involved: S1, segmented fitting of compressor rotor blade cross-section coordinate data, fitting function f(x); S2, encrypt each arc segment according to the fitting function f(x) to obtain the coordinate point data that approximates the true curve; S3, calculate the cross-sectional area Aea and the minimum principal moment of inertia I according to the encrypted array x0 , maximum principal moment of inertia I y0 And the coordinates of the cross-section centroid C G x and G y ; S4, calculate the vector of each coordinate point of the cross section relative to the cross section centroid C Calculate the force arm A of the section coordinate point relative to the maximum principal inertia axis, calculate the force arm B of the section coordinate point relative to the minimum principal inertia axis, and calculate the coordinate x of the centrifugal force of the blade above the section at the section projection point E. E and y E , calculate the vector of the projection point E relative to the cross-section centroid C Calculate the moment arms P and Q of the projection point E relative to the minimum and maximum principal inertia axes; S41, Calculate airflow force Bending moments M1 and M2 generated about the minimum and maximum principal axes of inertia of the cross section; S42, calculate the bending moments M3 and M4 generated by the centrifugal force C of the blade above the section relative to the minimum and maximum principal inertia axes of the section; S5, calculate the centrifugal tensile stress σ at different cross-section positions based on the centrifugal force, principal moment of inertia, lever arm and bending moment of the blade t , airflow bending stress σ s and centrifugal bending stress σ c .

2. The method for calculating the two-dimensional strength of a compressor rotor blade according to claim 1, wherein: The calculation formula of the fitting function f(x) in step S1 is as follows: or Where a and r are the coefficients of the fitting function.

3. The method for calculating the two-dimensional strength of a compressor rotor blade according to claim 1, wherein: In step S2, each arc segment is encrypted using uniform encryption.

4. The method for calculating the two-dimensional strength of a compressor rotor blade according to claim 1, wherein: The vector of the cross-sectional coordinate point P relative to the cross-sectional centroid C in step S4 The calculation formula is as follows: Among them, G x is the x-coordinate of the cross-section centroid C, G y is the y coordinate of the centroid C of the cross section.

5. The method for calculating the two-dimensional strength of a compressor rotor blade according to claim 1, wherein: The calculation formulas for calculating the moment arm A and the moment arm B of the cross-section coordinate point P relative to the minimum principal inertia axis and the maximum principal inertia axis in step S4 are as follows: in, is the unit vector in the positive direction of the minimum principal inertia axis, is the unit vector in the positive direction of the maximum principal inertia axis, and a0 is the rotation angle of the minimum principal inertia axis relative to the x-axis.

6. The method for calculating the two-dimensional strength of a compressor rotor blade according to claim 1, wherein: In step S4, the centrifugal force C of the blade profile above the cross section is calculated using the following formula at the cross section projection point E coordinate: Among them, b is the blade installation value, R c R is the distance between the analysis section and the axis of rotation; b is the distance from the center of gravity of the blade above the cross section to the axis of rotation; yb is the y coordinate of the center of gravity of the blade above the cross section.

7. The method for calculating the two-dimensional strength of a compressor rotor blade according to claim 1, wherein: In step S4, the centrifugal force C of the blade above the cross section is calculated at the cross section projection point E relative to the cross section centroid C. The formulas for calculating the moment arms P and Q of the projection point E relative to the minimum and maximum principal inertia axes of the cross section are as follows: Among them, x E is the x coordinate of point E, y E is the y coordinate of point E.

8. The method for calculating the two-dimensional strength of a compressor rotor blade according to claim 1, wherein: The airflow force in step S41 The calculation formulas for the bending moments M1 and M2 relative to the minimum and maximum principal inertia axes of the cross section are as follows: in, is the blade airflow force vector, F x F is the airflow force x axial force, y is the y-axial component of the airflow force.

9. The method for calculating the two-dimensional strength of a compressor rotor blade according to claim 1, wherein: The calculation formula for the centrifugal force C of the blade above the cross section in step S42 is as follows: M3=C×P=C×(-(xE-Gx)sin(a0)+(yE-Gy)cos(a0)) M4=C×Q=C×((xE-Gx)cos(a0)+(yE-Gy)sin(a0)).

10. The method for calculating the two-dimensional strength of a compressor rotor blade according to claim 1, wherein: In step S5, the cross-sectional centrifugal tensile stress σ is calculated. t , airflow bending stress σ s and centrifugal bending stress σ c The calculation formula is as follows:

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