An aero-engine blade vulnerable area division method, system, device and storage medium

Abstract

The application provides an aero-engine blade vulnerable area division method, system, device and storage medium. First, numerical models of various real aero-engine blades are established, modal analysis is performed by using finite element analysis software, the sizes of leading edge cross sections under the first three modes are compared, and a numerical model with a thinner cross section is selected and marked as a dangerous numerical model. Then, a dangerous mode of the dangerous numerical model is selected according to the dynamic stress test result, and the position of the corresponding maximum stress point under the dangerous mode is the vulnerable area of the corresponding real blade. The above division method can find the weak parts of the blade vulnerable to damage before the foreign object damage experiment, has good operability and good interpretability, accelerates the experimental process, and greatly reduces the cost of the experiment.

Description

Technical Field

[0001] This invention relates to the field of aero-engine blade technology, specifically to a method, system, device, and storage medium for dividing vulnerable areas of aero-engine blades. Background Technology

[0002] During flight, engines frequently encounter foreign object (FOD) impacts or intrusions, resulting in FOD damage. FOD can originate from various external objects such as birds, hail, debris, and dust, potentially damaging critical components like engine blades, turbines, and turbine blades, leading to decreased engine performance or even failure. FOD is a significant safety hazard for aircraft. High-speed aero engines often ingest hard objects; once inside, these objects can reach relative speeds of 100 m / s to 350 m / s with the compressor blades, causing severe impact damage, especially to the first few stages of the compressor blades and their leading edges. Current technology refers to damage caused by hard objects like metal and gravel impacting the engine as "Foreign Object Damage" (FOD).

[0003] Foreign object damage has a very serious impact on engines, potentially causing blade deformation, cracks, or even breakage. Once a blade breaks, it will fly off and cause serious damage to other blades or the casing. Since the location of the impact on the leading edge of the blade is random, it would be very time-consuming and expensive to investigate the effects of different foreign objects, impact locations, and impact angles on the fatigue limit of the blade using only the controlled variable method. If the weak areas on the blade that will be significantly affected by impact damage can be marked before the experiment, the experimental process will be greatly accelerated and resources will be saved. Summary of the Invention

[0004] Purpose of the invention: The first purpose of the invention is to provide a method for dividing vulnerable areas of aero-engine blades that is easy to operate and has good interpretability. The second purpose is to provide a system, device and storage medium corresponding to the above-mentioned method for dividing vulnerable areas of aero-engine blades.

[0005] Technical solution: A method for dividing vulnerable areas of aero-engine blades, comprising the following steps:

[0006] (1) Establish numerical models of several real blades to be tested, give test conditions, and calculate the corresponding blade modes for each numerical model;

[0007] (2) Extract the natural frequencies and stress distributions of the first ten modes of each numerical model from the calculation results of the blade modes, and record the location of the maximum stress point at the leading edge and the leading edge cross-sectional dimensions of each mode of each numerical model.

[0008] (3) Based on the leading edge cross-sectional dimension data of the first three modes of each numerical model, the numerical models whose leading edge cross-sectional dimension data is less than or equal to the set value are selected and marked as dangerous numerical models.

[0009] (4) Based on the dynamic stress measurement data of the real blade corresponding to the dangerous numerical model, the corresponding order with dynamic stress greater than or equal to the dangerous threshold is selected. The maximum stress point at the leading edge of the dangerous numerical model blade corresponding to this order is the vulnerable area of ​​the real blade corresponding to this dangerous numerical model.

[0010] Specifically, in step (1), a numerical model of the actual blade to be tested is established, imported into the finite element analysis software, the material parameters of each numerical model are set, the mesh type, boundary conditions and blade rotation speed are given, and the modes of each blade are calculated.

[0011] Specifically, material parameters include density, elastic modulus, and Poisson's ratio.

[0012] Specifically, in step (3), the front section dimension data is the front section radius value.

[0013] Specifically, in step (4), the danger threshold for dynamic stress is 50 MPa.

[0014] The present invention also provides a system for classifying vulnerable areas of aero-engine blades, comprising:

[0015] Modal calculation module: used to establish numerical models of several real blades to be tested, given test conditions, and calculate the corresponding blade modes for each numerical model;

[0016] Data extraction and recording module: used to extract the natural frequencies and stress distributions of the first ten modes of each numerical model from the calculation results of blade modes, and record the location of the maximum stress point at the leading edge and the leading edge cross-sectional dimensions of each mode of each numerical model;

[0017] Hazardous blade screening module: This module is used to screen numerical models whose leading edge cross-section size data is less than or equal to a set value based on the leading edge cross-section size data of the first three modes of each numerical model, and then mark them as hazardous numerical models.

[0018] Vulnerable Area Marking Module: Based on the dynamic stress measurement data of the actual blade corresponding to the dangerous numerical model, this module filters out the corresponding order where the dynamic stress is greater than or equal to the dangerous threshold. The maximum stress point at the leading edge of the dangerous numerical model blade corresponding to this order is the vulnerable area of ​​the actual blade corresponding to the dangerous numerical model.

[0019] Specifically, the modal calculation module includes: establishing a numerical model of the actual blade to be tested, importing it into the finite element analysis software, setting the material parameters of each numerical model, giving the mesh type, boundary conditions and blade rotation speed, and calculating the modes of each blade.

[0020] Specifically, in the hazardous blade screening module, the leading edge section size data is the value of the leading edge section radius.

[0021] The present invention also provides an apparatus, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the steps of the above-described method for dividing vulnerable areas of aero-engine blades.

[0022] The present invention also provides a computer-readable storage medium storing a computer program thereon, which, when executed by a processor, implements the steps of the above-described method for dividing vulnerable areas of aero-engine blades.

[0023] Beneficial effects: Compared with the prior art, the significant effect of the present invention is that: the present invention performs modal analysis on numerical models of various real blades, compares the leading edge cross-sectional dimensions under the first three modes, selects the thinner blades as critical blades, selects the critical modes of the critical blades based on the dynamic stress test results, and the location of the corresponding maximum stress point under the critical mode is the vulnerable area of ​​the blade. This method can identify the weak parts of the blade that are easily damaged before conducting external object damage experiments, and has good operability and interpretability. While speeding up the experimental process, it can greatly reduce the cost of the experiment. Attached Figure Description

[0024] Figure 1 This is a flowchart of the method for dividing vulnerable areas of aero-engine blades according to the present invention.

[0025] Figure 2 This is a diagram showing the first-order leading edge cross-sectional dimensions of each blade in this invention.

[0026] Figure 3 This is a diagram showing the dimensions of the second-order leading edge cross-section of each blade in this invention.

[0027] Figure 4 This is a diagram showing the dimensional dimensions of the leading edge cross-section of each blade in this invention. Detailed Implementation

[0028] The present invention will now be described in further detail with reference to the accompanying drawings.

[0029] Please see Figure 1 As shown, this invention discloses a method for dividing vulnerable areas of aero-engine blades, comprising the following steps:

[0030] (1) Use UG or other engineering modeling software to establish numerical models of various real aero-engine blades, and import them into Workbench or other finite element analysis software. Set the material parameters such as density, elastic modulus, and Poisson's ratio of each blade corresponding to the numerical model, and set the mesh type, boundary conditions and rotational speed. After setting, calculate the mode of each blade.

[0031] (2) Extract the natural frequencies and stress distributions of the first ten modes of the numerical model corresponding to each blade from the calculation results of the blade modes, and record the location of the maximum stress point at the leading edge and the leading edge cross-sectional dimensions of each mode of the numerical model.

[0032] In this embodiment, five different types of aero-engine blades were selected as examples for testing.

[0033] Please refer to Table 1 below, which records the natural frequencies of the first ten modes of each blade.

[0034] Table 1

[0035]

[0036] (3) Based on the leading edge cross-sectional dimension data of the first three modes of each numerical model, select the numerical models whose leading edge cross-sectional dimension data is less than the set value and mark them as dangerous numerical models.

[0037] Please see Figure 2-4 The figures show the leading-edge cross-sectional dimensions for the five blades in their first to third modes. Using the leading-edge cross-sectional radius as a reference, and considering the data from all three modes, blade 8111 has the smallest leading-edge cross-sectional radius. Therefore, under the aforementioned operating conditions, blade 8111 is more susceptible to stress and more easily damaged by external objects compared to other blades. Thus, in this embodiment, the numerical model corresponding to blade 8111 is a hazardous numerical model. In practical applications, a numerical threshold for the leading-edge cross-sectional radius can also be set based on expert experience to filter out hazardous blades with a leading-edge cross-sectional radius less than or equal to the threshold.

[0038] (4) Perform dynamic stress tests on the actual blades corresponding to the hazardous numerical model, or obtain dynamic stress measurement data directly from the blade manufacturer. Based on the dynamic stress measurement data of blade No. 8111, select the corresponding order where the dynamic stress is greater than or equal to the hazardous threshold. The maximum stress point at the leading edge of the numerical model corresponding to this order is the vulnerable area of ​​the actual blade corresponding to the hazardous numerical model. Table 2 below shows the dynamic stress measurement data of blade No. 8111.

[0039] Table 2

[0040]

[0041] In this embodiment, dynamic stress exceeding 50 MPa is considered a dangerous threshold. According to the dynamic stress measurement data, the dynamic stress at strain gauge 2 (243 Hz), strain gauge 1 (956 Hz), and strain gauge 3 (3753 Hz) all exceed 50 MPa, which correspond to the natural frequencies of the 1st, 3rd, and 10th modes of blade 8111, respectively. Therefore, the maximum stress points at the leading edge of the blade corresponding to the 1st, 3rd, and 10th modes are designated as vulnerable areas.

[0042] This invention also discloses a vulnerable area division system for aero-engine blades corresponding to the above-described division method, comprising:

[0043] Modal calculation module: Used to establish a numerical model of the actual blade to be tested, import it into the finite element analysis software, set the material parameters of each numerical model, give the mesh type, boundary conditions and blade rotation speed, and calculate the modes of each blade.

[0044] Data extraction and recording module: used to extract the natural frequencies and stress distributions of the first ten modes of each numerical model from the calculation results of blade modes, and record the location of the maximum stress point at the leading edge and the leading edge cross-sectional dimensions of each mode of each numerical model.

[0045] Dangerous blade screening module: Based on the leading edge cross-sectional dimension data of the first three modes of each numerical model, it filters out numerical models whose leading edge cross-sectional radius is less than or equal to a set value and marks them as dangerous numerical models.

[0046] Vulnerable Area Marking Module: Based on the dynamic stress measurement data of the actual blade corresponding to the dangerous numerical model, this module filters out the corresponding order where the dynamic stress is greater than or equal to the dangerous threshold. The maximum stress point at the leading edge of the dangerous numerical model blade corresponding to this order is the vulnerable area of ​​the actual blade corresponding to the dangerous numerical model.

[0047] The present invention also provides an apparatus, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the steps of the above-described method for dividing vulnerable areas of aero-engine blades.

[0048] The present invention also provides a computer-readable storage medium storing a computer program thereon, which, when executed by a processor, implements the steps of the above-described method for dividing vulnerable areas of aero-engine blades.

Claims

1. A method for dividing a vulnerable region of a turbine blade of an aeroengine, characterized in that, The method comprises the following steps: (1) establishing a plurality of numerical models of real blades to be tested, giving test conditions, and calculating the blade modes corresponding to each numerical model; (2) extracting the natural frequencies and stress distributions of the first ten orders of modes of each numerical model from the calculation results of the blade modes, and recording the position of the maximum stress point of the leading edge and the cross-sectional size data of the leading edge of each order of each numerical model; (3) according to the cross-sectional size data of the leading edge under the first three orders of modes of each numerical model, screening out the numerical models with cross-sectional size data of the leading edge less than or equal to a set value, and marking them as dangerous numerical models; (4) according to the dynamic stress measurement data of the real blades corresponding to the dangerous numerical models, screening out the corresponding orders with dynamic stress greater than or equal to a dangerous threshold value, and the maximum stress point of the leading edge of the blade of the dangerous numerical model corresponding to the order is the vulnerable area of the real blade corresponding to the dangerous numerical model.

2. The method of claim 1, wherein: In step (1), the numerical models of the real blades to be tested are established, imported into a finite element analysis software, the material parameters of each numerical model are set, the grid type, boundary conditions and blade speed are given, and each blade mode is calculated.

3. The gas turbine engine blade vulnerable area partitioning method of claim 2, wherein: The material parameters include density, elastic modulus and Poisson's ratio.

4. The gas turbine engine blade vulnerable area partitioning method of claim 1, wherein: In step (3), the cross-sectional size data of the leading edge is the numerical value of the radius of the cross section of the leading edge.

5. The gas turbine engine blade vulnerable area delineation method of claim 1, wherein: In step (4), the dangerous threshold value of the dynamic stress is 50 MPa.

6. An aeroengine blade vulnerable area partitioning system, characterized in that, It comprises: a mode calculation module for establishing a plurality of numerical models of real blades to be tested, giving test conditions, and calculating the blade modes corresponding to each numerical model; a data extraction and recording module for extracting the natural frequencies and stress distributions of the first ten orders of modes of each numerical model from the calculation results of the blade modes, and recording the position of the maximum stress point of the leading edge and the cross-sectional size data of the leading edge of each order of each numerical model; a dangerous blade screening module for screening out the numerical models with cross-sectional size data of the leading edge less than or equal to a set value according to the cross-sectional size data of the leading edge under the first three orders of modes of each numerical model, and marking them as dangerous numerical models; a vulnerable area marking module for screening out the corresponding orders with dynamic stress greater than or equal to a dangerous threshold value according to the dynamic stress measurement data of the real blades corresponding to the dangerous numerical models, and the maximum stress point of the leading edge of the blade of the dangerous numerical model corresponding to the order is the vulnerable area of the real blade corresponding to the dangerous numerical model.

7. The turbine blade vulnerable region partitioning system of claim 6, wherein: The mode calculation module comprises: establishing a numerical model of a real blade to be tested, importing it into a finite element analysis software, setting the material parameters of each numerical model, giving the grid type, boundary conditions and blade speed, and calculating each blade mode.

8. The turbine blade vulnerable area partitioning system of claim 6, wherein: In the dangerous blade screening module, the cross-sectional size data of the leading edge is the numerical value of the radius of the cross section of the leading edge.

9. An apparatus comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, wherein, The processor executes the computer program to realize the steps of the method of any one of claims 1 to 5.

10. A computer-readable storage medium having stored thereon a computer program, characterized in that, The computer program is executed by the processor to realize the steps of the method of any one of claims 1 to 5.

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