Aero-engine vibration fault multi-dimensional quantification method and system

Abstract

The invention provides an aero-engine vibration fault multi-dimensional quantification method and system, and relates to the technical field of aero-engines. The aero-engine vibration fault multi-dimensional quantification method comprises the steps that multiple vibration fault modes causing vibration faults are acquired; according to a quantification calculation method, first-dimension quantification is carried out on the multiple vibration fault modes, and first-dimension quantification results are obtained; performing second dimension quantization on the multiple vibration fault modes according to a quantization calculation method, and obtaining second dimension quantization results; and performing joint quantization according to the first dimension quantization result and the second dimension quantization result. According to the aero-engine vibration fault multi-dimensional quantification method, quantification can be carried out based on the first dimension, the second dimension and other dimensions of the vibration fault mode, so that the verification strategy of the vibration fault mode can be formulated according to the quantification result, the vibration fault can be eliminated timely, rapidly and efficiently, and the method has high engineering application value.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engines, and in particular to a multi-dimensional quantification method and system for aero-engine vibration faults. Background Art

[0002] In the 1920s, after the British dynamicist Jeffcott broke the shackles of the idea that "rotors cannot operate above the first critical speed", a large number of rotating machinery were designed to operate at supercritical speeds. The rotor speeds became higher and higher, and the vibration problems of the equipment received more attention and research.

[0003] Fault Tree Analysis (FTA) technology first needs to establish a fault tree model composed of fault events. Based on this model, a qualitative analysis of the fault can be performed. Secondly, based on the probability of occurrence of the fault event, the reliability of the system can be quantitatively analyzed. For a system that is relatively complex in the development stage, it is relatively difficult to use the fault tree analysis technology for vibration fault diagnosis. Although the document "Compressor Vibration Fault Analysis Based on Fault Tree Analysis" applies the fault tree analysis technology to the vibration fault of the compressor, the fault tree model consists of 33 bottom events, and the probability of occurrence of the bottom events cannot be quantified, and only qualitative analysis can be performed. The cause of the fault "three blade tips of the first stage rotor blade of the compressor rub against the corresponding casing" causes a large change in the rotor imbalance. This problem is easier to find from the "hole probe" rather than the result of the fault tree analysis.

[0004] The aircraft engine in the development stage is a very complex system, and its vibration failure mode is unknown, so it is difficult to diagnose based on the existing vibration failure characteristics. For complex systems, especially when multiple factors are coupled, the event boundaries are unclear, and it is difficult to create a fault tree composed of independent events; even if a fault tree is created, it is difficult to analyze due to the complexity and size of the fault tree model. Summary of the invention

[0005] The purpose of the present invention is to provide a multi-dimensional quantification method and system for aircraft engine vibration faults, which can improve the technical problem that it is difficult to eliminate the existing aircraft engine vibration faults in a timely, rapid and efficient manner.

[0006] The embodiments of the present invention can be implemented in the following ways:

[0007] A multi-dimensional quantification method for aero-engine vibration failure, comprising obtaining a plurality of vibration failure modes causing the vibration failure;

[0008] According to the quantitative calculation method, the first dimension of the plurality of vibration failure modes is quantified respectively, and the first dimension quantification result is obtained;

[0009] According to the quantitative calculation method, the second dimension of the plurality of vibration failure modes is quantified respectively, and the second dimension quantification result is obtained;

[0010] Joint quantization is performed according to the first dimensional quantization result and the second dimensional quantization result.

[0011] Optionally, the quantitative calculation method includes:

[0012] Formulate a quantization table, the step of formulating the quantization table comprising:

[0013] Determine the set of factors U that can be considered for the vibration fault: U = {U 1 ,U 2 ,……,U m}; the factor set contains m factors; determine the weight set W corresponding to the factor set: W = {w1, w2, ..., wm}; the weight set contains m weight coefficients, and the weight coefficients correspond to the factors one by one; determine the evaluation set V of each factor i :V i = {V i1 ,V i2 ,……,V ij}; The evaluation set contains J evaluation values, and the evaluation values ​​in the evaluation value set are arranged in descending order, and the number of evaluation values ​​J in the evaluation sets of different factors does not need to be consistent;

[0014] The plurality of vibration failure modes are quantified respectively according to the quantification table, and quantification results are obtained.

[0015] Optionally, the step of quantifying a plurality of vibration failure modes respectively according to the quantification table and obtaining quantification results includes:

[0016] Determine the evaluation of the vibration failure mode under each of the factors and the corresponding evaluation value r i , r i ∈Vi; multiple evaluation values ​​r i Construct the evaluation vector R, R = {r 1 ,r 2 ,……r m};

[0017] The quantified value B of the vibration failure mode is obtained according to the following formula:

[0018]

[0019] Among them, R′ is the transpose of the evaluation vector R;

[0020] Using the quantized value B as the quantized result; or,

[0021] Normalize the quantized value B to obtain the normalized result b:

[0022] b = B / A;

[0023]

[0024] Substitute the normalized result with the quantized result.

[0025] Optionally, the step of determining a set of factors that may be considered for vibration faults comprises:

[0026] The vibration fault is decomposed to obtain a plurality of factors causing the vibration fault, and a plurality of the factors constitute the factor set.

[0027] Optionally, the set of factors for quantifying authenticity includes the mechanism of the failure mode, the conditions under which the failure mode occurs, the consistency with existing test data, and the fact that the failure can be virtually verified through simulation analysis.

[0028] Optionally, the evaluation set of the mechanism of the failure mode includes: the mechanism is clear and does not contradict the basic principles of physics; the failure mechanism is not easy to judge;

[0029] The first dimension quantification is authenticity quantification; the evaluation set of conditions for the occurrence of the failure mode includes: very likely to occur; likely to occur; not easy to judge; unlikely to occur;

[0030] The evaluation set of consistency with the existing test data includes: consistency, no contradiction; partial consistency, no contradiction; no contradiction, but also unable to show its consistency; contradiction with some data;

[0031] The evaluation set of the faults that can be virtually verified through simulation analysis includes: the simulation analysis results are consistent with the measured results, and the simulation analysis boundary conditions are relatively reasonable; the simulation analysis results are consistent with the measured results, and the rationality of the simulation analysis boundary conditions cannot be judged; the fault mode cannot be reproduced through existing simulation technology.

[0032] Optionally, the second dimension quantification is verifiability quantification; the factor set of the verifiability quantification includes: experimental verification based on existing technologies, time cost of verification experiments, cost of verification experiments, and step-by-step verification at each level.

[0033] Optionally, the evaluation set that can be experimentally verified based on the existing technology includes: verifiable, the verification technology is mature; partially verified, the verification technology is mature; partially verified, and the verification technology is not mature; temporarily unverifiable;

[0034] Wherein, when the vibration failure mode is evaluated as temporarily unverifiable for the test verification based on the prior art, the verifiability quantification result is defined as 0;

[0035] The evaluation set of the time cost of the verification test includes: no risk of delaying the project progress; there is a risk of delaying the project progress, but the risk level is low; there is a serious risk of delaying the project progress;

[0036] The evaluation set of the cost of the validation test includes: the cost is very small; the cost is large but acceptable; the cost is expensive and needs to be carefully considered;

[0037] The evaluation set that can be verified step by step at each level includes: can be verified step by step at each level; can perform a small part verification before the final verification; cannot be verified step by step, and can only perform the final verification.

[0038] Optionally, the step of performing joint quantization according to the first dimensional quantization result and the second dimensional quantization result includes:

[0039] Divide the first dimension quantization and the second dimension quantization into a plurality of levels with increasing values;

[0040] The level to which the vibration fault mode belongs is determined according to the obtained quantization result of the first dimension and the quantization result of the second dimension, and a joint quantization distribution table is formed.

[0041] A multi-dimensional quantification system for vibration faults of an aero-engine comprises an acquisition module, the acquisition module is used to acquire a plurality of vibration fault modes causing vibration faults; a calculation module, the calculation module is used to calculate the first dimensional quantification results for the plurality of vibration fault modes respectively according to a quantification calculation method; the calculation module is also used to calculate the second dimensional quantification results for the plurality of vibration fault modes respectively according to the quantification calculation method; and a joint quantization module, the joint quantization module is used to perform joint quantization according to the first dimensional quantization results and the second dimensional quantization results.

[0042] The beneficial effects of the multi-dimensional quantification method and system for aircraft engine vibration failure provided by the embodiments of the present invention include:

[0043] The embodiment of the present invention provides a multi-dimensional quantification method for aero-engine vibration faults, which includes obtaining a plurality of vibration fault modes that cause vibration faults; quantifying the plurality of vibration fault modes in the first dimension according to a quantitative calculation method, and obtaining the first dimension quantification results; quantifying the plurality of vibration fault modes in the second dimension according to a quantitative calculation method, and obtaining the second dimension quantification results; and performing joint quantification according to the first dimension quantification results and the second dimension quantification results. The multi-dimensional quantification method for aero-engine vibration faults can be quantified based on the first dimension, the second dimension and other dimensions of the vibration fault mode, so that a verification strategy for the vibration fault mode can be formulated according to the quantification results, and then the vibration fault can be eliminated in a timely, rapid and efficient manner, and has a strong engineering application value.

[0044] The multi-dimensional quantification system for aircraft engine vibration faults provided by the embodiments of the present invention can be quantified based on multiple dimensions of vibration fault modes, so that a verification strategy for the vibration fault mode can be formulated according to the quantification results, thereby timely, quickly and efficiently eliminating vibration faults, and has the beneficial effect of having strong engineering application value. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] The above features and advantages of the present invention can be better understood after reading the detailed description of the embodiments of the present disclosure in conjunction with the following drawings. In the drawings, the components are not necessarily drawn to scale, and components with similar related properties or features may have the same or similar reference numerals.

[0046] Figure 1 A step diagram of a multi-dimensional quantification method for aircraft engine vibration failure provided according to one aspect of the present invention is shown;

[0047] Figure 2 A relationship diagram of decomposing vibration faults to obtain multiple factors according to one aspect of the present invention is shown;

[0048] Figure 3 A relationship diagram of multiple factors is shown in which a verification process for vibration faults provided according to one aspect of the present invention is decomposed. DETAILED DESCRIPTION

[0049] The present invention is described in detail below in conjunction with the accompanying drawings and specific embodiments. Note that the aspects described below in conjunction with the accompanying drawings and specific embodiments are only exemplary and should not be construed as limiting the scope of protection of the present invention in any way.

[0050] In the description of the present invention, it should be noted that if the terms "upper", "lower", "inside", "outside", "vertical" and the like appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the drawings, or is the orientation or position relationship in which the product of the invention is usually placed when used, rather than indicating or implying that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0051] At the same time, it should be noted that the terms "first", "second", etc. are only used for distinguishing descriptions and cannot be understood as indicating or implying relative importance.

[0052] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified or limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, an integral connection, or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or the internal communication of two components, etc. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0053] Figure 1 This is a step diagram of the multi-dimensional quantification method for aircraft engine vibration failure provided in this embodiment. Figure 1 This embodiment provides a multi-dimensional quantification method for aircraft engine vibration failure, the method comprising:

[0054] S01: Acquire multiple vibration failure modes that cause vibration failure.

[0055] When a vibration fault occurs and the cause of the vibration fault needs to be eliminated, the vibration fault mode that may cause the vibration fault can be preliminarily obtained through analysis and testing of the specific vibration fault, or the vibration fault mode that may cause the vibration fault can be obtained based on expert experience.

[0056] Specifically, this embodiment is explained by taking the vibration failure of the core engine rotor, and the vibration failure is manifested on the rear fulcrum as an example. After analyzing the vibration failure phenomenon, the possible vibration failure modes are preliminarily determined to include: friction, rotor third-order criticality, rotor thermal bending, loose rotor connection, bearing seat resonance, and rear bearing casing resonance. By executing the subsequent steps of the multi-dimensional quantification method of the aircraft engine vibration failure, the verification strategy for the various vibration failure modes is reasonably set. It can be understood that the multi-dimensional quantification method of the aircraft engine vibration failure can also perform multi-dimensional quantification on other vibration failures, and at the same time, the possible vibration failure modes can be set for different vibration failures. The vibration failure of the core engine rotor provided here, and the vibration failure manifested on the rear fulcrum, and the possible vibration failure modes that cause the vibration failure are only examples.

[0057] S02: performing first-dimensional quantification on a plurality of vibration failure modes respectively according to a quantitative calculation method, and obtaining first-dimensional quantification results.

[0058] The quantitative calculation method includes formulating a quantitative table. The specific process of formulating the quantitative table includes:

[0059] S21: Determine the set of factors U that can be considered for vibration failure: U = {U 1 ,U 2 ,……,U m}.

[0060] By decomposing the vibration fault, multiple factors causing the vibration fault are obtained, and the multiple factors constitute the factor set, which includes m factors.

[0061] S22: Determine the weight set W of each factor: W = {W 1 ,W 2 ,……,W m}.

[0062] Determine the weight coefficient of each factor, the weight coefficient corresponds to the factor one by one, and the specific value of the weight coefficient can be set based on expert experience, hierarchical analysis method, etc.

[0063] S23: Determine the evaluation set V for each factor i :V i = {V i1 ,V i2 ,……,V ij}.

[0064] An evaluation set is set for each factor. The specific number of evaluations in the evaluation set of each factor can be determined according to the specific content of the factor. At the same time, each evaluation set also has an evaluation value corresponding to the evaluation. The evaluation set V i There are J evaluation values ​​in the evaluation set, and the evaluation values ​​in the evaluation set are arranged in ascending order, so the evaluation value V i1 It is the one with the largest evaluation value in an evaluation set. At the same time, the size of the evaluation value is used to represent the difference between various evaluation levels, and its specific value can be set according to the specific situation.

[0065] The quantitative calculation method also includes: quantifying various vibration failure modes according to the quantification table and obtaining the quantification results. The process includes: determining the evaluation of the vibration failure mode under each factor and the corresponding evaluation value r i , r i ∈Vi; multiple evaluation values ​​r i Construct the evaluation vector R, R = {r 1 ,r 2 ,……r m}.

[0066] The quantitative value B of the vibration failure mode is obtained according to the following formula:

[0067]

[0068] Where R′ is the transpose of the evaluation vector R.

[0069] Normalize the quantized value B to obtain the normalized result b:

[0070] b = B / A;

[0071]

[0072] In this embodiment, the normalization result b is used as the quantization result. In some other embodiments, the quantization value B may also be directly used as the quantization result.

[0073] In this embodiment, the first dimension quantification is authenticity quantification, and accordingly, the first dimension quantification structure is an authenticity quantification result. The authenticity quantification result is a quantification of the possible occurrence probability of each vibration fault mode.

[0074] Therefore, the specific process of quantifying the authenticity of various vibration failure modes according to the quantitative calculation method and obtaining the authenticity quantification results may include formulating an authenticity quantification table, and quantifying various vibration failure modes according to the authenticity quantification table and obtaining the quantification results.

[0075] In this embodiment, the following Table 1 shows an authenticity quantification table, and the authenticity quantification table can be formulated according to step S21, step S22 and step S23.

[0076] Table 1 Quantification table of authenticity

[0077]

[0078]

[0079] The specific process of formulating the authenticity quantification table is described below.

[0080] The process of executing step S21: Figure 2 A diagram showing the decomposition of vibration faults to obtain multiple factors is shown. Figure 2 As shown, vibration failure modes can generally be divided into three parts: "due to...", "based on..." mechanism / logical relationship" and "causing..." phenomenon. Three factors that need to be considered in the vibration failure factor set are proposed for these three parts. Specifically, the three factors are the mechanism of the failure mode, the conditions for the occurrence of the failure mode, and the consistency with the existing test data. At the same time, due to the rapid development of computer simulation technology, some vibration failures can be simulated vertically, and this direction can also be considered as a factor. Therefore, in this embodiment, the factor set for authenticity quantification also includes the factor that the failure can be virtually verified through simulation analysis, that is, in this embodiment, the number of factors m included in the factor set is 4. It should be noted that the number of factors in the authenticity quantification factor set can also be set according to demand. For example, as the research goes deeper in the future, more factors of vibration failure can also be proposed.

[0081] The process of executing step S22: In this embodiment, since the factor set of vibration fault includes four factors, the obtained weight set also includes four weight coefficients accordingly.

[0082] Specifically, the weight coefficient W corresponding to the failure mode mechanism factor is 1 =1; the weight coefficient W corresponding to the factor of the condition of the failure mode 2 =2; weight coefficient W corresponding to the consistency factor of existing test data 3 =2; the weight coefficient W corresponding to this factor can be verified virtually through simulation analysis. 4 =2.

[0083] The process of executing step S23: Specifically, for factor 1: the mechanism of the failure mode, determine the evaluation set V 1 ; For factor 2: the conditions under which the failure mode occurs, determine the evaluation set V 2 ; For factor 3: consistency with existing test data, determine the evaluation set V 3 ; For factor 4: The fault can be virtually verified through simulation analysis to determine the evaluation set V 4 .

[0084] In this embodiment, the evaluation set of the mechanism of the fault mode includes: the mechanism is clear and does not contradict the basic physical principle; the fault mechanism is not easy to judge. Therefore, the evaluation set V of the mechanism of the fault mode 1 Two evaluation values ​​should be included.

[0085] The evaluation set of conditions for the occurrence of the failure mode includes: very likely to occur; likely to occur; not easy to judge; unlikely to occur. That is, the evaluation set V of the conditions for the occurrence of the failure mode 2 There should be four evaluation values ​​included.

[0086] The evaluation set of consistency with the existing test data includes: consistency, no contradiction; partial consistency, no contradiction; no contradiction, but it is impossible to prove its consistency; there are contradictions with some data. That is, the evaluation set V of consistency with the existing test data 3 Four evaluation values ​​should be included.

[0087] The evaluation set of faults that can be virtually verified by simulation analysis includes: the simulation analysis results are consistent with the measured results, and the simulation analysis boundary conditions are relatively reasonable; the simulation analysis results are consistent with the measured results, and the rationality of the simulation analysis boundary conditions cannot be judged; the fault mode cannot be reproduced by existing simulation technology. That is, the evaluation set V of faults that can be virtually verified by simulation analysis 4 The three evaluation values ​​should be included.

[0088] After formulating the authenticity quantification table shown in Table 1, the authenticity of various vibration fault modes can be quantified and the quantification results can be obtained.

[0089] Quantify the authenticity of the vibration failure mode of rubbing.

[0090] Table 2 Quantification of authenticity of friction vibration failure mode

[0091]

[0092] In Table 2: B = 3 × 1 + 1 × 2 + 2 × 2 + 0 × 2 = 9;

[0093] b=9÷(3×1+3×2+3×2+4×2)=9÷23=0.39.

[0094] Quantify the authenticity of the rotor's third-order critical speed vibration failure mode.

[0095] Table 3 Quantification of the authenticity of the rotor third critical speed vibration failure mode

[0096]

[0097] In Table 3: B = 3 × 1 + 1 × 2 + 3 × 2 + 0 × 2 = 11;

[0098] b=11÷(3×1+3×2+3×2+4×2)=11÷23=0.48.

[0099] Quantify the authenticity of rotor thermal bending as a vibration failure mode.

[0100] Table 4 Quantification of the authenticity of rotor thermal bending vibration failure mode

[0101]

[0102]

[0103] In Table 4: B = 3 × 1 + 2 × 2 + 2 × 2 + 0 × 2 = 11;

[0104] b=11÷(3×1+3×2+3×2+4×2)=11÷23=0.48.

[0105] Quantify the authenticity of a vibration failure mode, a loose rotor connection.

[0106] Table 5 Quantification of the authenticity of vibration failure mode due to loose rotor connection

[0107]

[0108] In Table 4: B = 2 × 1 + 1 × 2 + 3 × 2 + 0 × 2 = 10;

[0109] b=10÷(3×1+3×2+3×2+4×2)=10÷23=0.43.

[0110] Quantify the authenticity of a vibration failure mode, bearing housing resonance.

[0111] Table 6 Quantification of the authenticity of bearing seat resonance vibration failure mode

[0112]

[0113]

[0114] In Table 6: B = 3 × 1 + 3 × 2 + 3 × 2 + 1 × 2 = 17;

[0115] b=17÷(3×1+3×2+3×2+4×2)=17÷23=0.74.

[0116] Quantify the authenticity of the vibration failure mode of rear-loaded casing resonance.

[0117] Table 7 Quantification of authenticity of the resonant vibration failure mode of the rear bearing casing

[0118]

[0119]

[0120] In Table 7: B = 3 × 1 + 3 × 2 + 3 × 2 + 3 × 2 = 21;

[0121] b=21÷(3×1+3×2+3×2+4×2)=21÷23=0.91.

[0122] S03: performing second-dimensional quantification on a plurality of vibration failure modes respectively according to a quantitative calculation method, and obtaining second-dimensional quantification results.

[0123] In this embodiment, the second dimension quantization is verifiability quantization, and accordingly, the second dimension quantization result is a verifiability quantization result. It should be noted that in this embodiment, the first dimension quantization is authenticity quantization, and the second dimension quantization is verifiability quantization. It can be understood that in other embodiments, quantization of other dimensions can also be performed according to the quantization calculation method, and finally joint quantization is performed.

[0124] Since the verifiability quantification of the vibration failure mode is also obtained according to the quantitative calculation method, the specific process of executing step S03 may include formulating a verifiability quantification table, and quantifying a plurality of vibration failure modes respectively according to the verifiability quantification table, and obtaining quantification results.

[0125] In this embodiment, the following Table 8 shows a verifiability quantification table, and the verifiability quantification table can be formulated according to step S21, step S22, and step S23.

[0126] Table 8 Verifiability Quantification Table

[0127]

[0128]

[0129] The specific process of formulating the verifiability quantification table is described below.

[0130] The process of executing step S21: Figure 3 The figure shows the decomposition of the verification process of vibration fault to obtain the relationship diagram of multiple factors. Figure 2 As shown, the verification of aircraft engine vibration failure can be considered from the aspects of the maturity of verification-related technologies, the cost and cycle required for verification implementation, etc., so as to obtain the relevant factors of the verifiability of vibration failure for these three aspects. Specifically, the factors are the experimental verification based on existing technologies, the time cost of the verification test, and the cost cost of the verification test. At the same time, due to the complexity of aircraft engines, it is difficult to verify the performance changes of a certain component in the whole machine system. Generally, it is necessary to carry out layer-by-layer verification: first verify a certain technical problem in a relatively simple component environment, then verify it on a relatively complex simulation tester, and finally conduct whole machine level verification. Therefore, it is necessary to consider the layer-by-layer nature of verification. Therefore, the factor set of verifiability quantification also includes the factor that step-by-step verification can be carried out. In summary, in this embodiment, the number of factors m in the factor set of verifiability quantification is 4.

[0131] The process of executing step S22: In this embodiment, since the factor set of verifiability quantification includes four factors, the obtained weight set also includes four weight coefficients accordingly.

[0132] Specifically, the weight coefficient W corresponding to this factor can be verified by experiments based on existing technologies. 1 =4; the weight coefficient W corresponding to the time cost of the verification test 2 =2; weight coefficient W corresponding to the cost of the verification test 3 =1; the weight coefficient W corresponding to this factor can be verified step by step at each level 4 =4.

[0133] The process of executing step S23: Specifically, for factor 1: experimental verification can be performed based on existing technologies to determine the evaluation set V 1 ; For factor 2: the time cost of the verification test, determine the evaluation set V 2; For factor 3: the cost of the validation test, determine the evaluation set V 3 ; For factor 4: a step-by-step verification can be performed to determine the evaluation set V 4 .

[0134] In this embodiment, the evaluation set that can be experimentally verified based on the existing technology includes: verifiable, the verification technology is mature; partially verified, the verification technology is mature; partially verified, and the verification technology is not mature; temporarily unable to verify.

[0135] Among them, when a vibration failure mode is evaluated as temporarily unverifiable based on the existing technology, the verifiability quantification result is defined as 0.

[0136] The evaluation set of the time cost of the verification test includes: no risk of delay to the project progress; there is a risk of delay to the project progress, but the risk level is low; there is a serious risk of delay to the project progress.

[0137] The evaluation set of cost of validation test includes: very small cost; high cost but acceptable; high cost and requires careful consideration.

[0138] The evaluation sets that can be verified step by step at each level include: can be verified step by step at each level; can perform a small part verification before the final verification; cannot be verified step by step, and can only perform the final verification.

[0139] After the verifiability quantification table shown in Table 8 is formulated according to the above steps, the verifiability quantification can be performed on various vibration failure modes respectively, and the quantification results can be obtained.

[0140] For the vibration failure mode of rubbing, since the cause of rubbing is uncertain and difficult to verify experimentally, the verifiability quantitative result of rubbing is defined as 0.

[0141] The verifiability of the rotor's third-order critical speed vibration failure mode is quantified.

[0142] Table 9 Quantification of the verifiability of the rotor third-order critical speed vibration failure mode

[0143]

[0144] In Table 9: B = 2 × 4 + 2 × 2 + 2 × 1 + 1 × 4 = 18;

[0145] b=18÷(3×4+2×2+2×1+3×4)=9÷30=0.60.

[0146] For the vibration failure mode of rotor thermal bending, it is difficult to verify because the cause of rotor thermal bending is uncertain and the rotor temperature field can also be simulated to verify the occurrence of rotor thermal bending under rotating conditions. The verifiability quantitative result of rotor thermal bending is defined as 0.

[0147] For the vibration failure mode of loose rotor connection, it is difficult to verify because it is related to the actual temperature field and the specific mechanism of "uncoordinated rotor deformation and local loose connection" is unclear. The verifiability quantification result of the loose rotor connection is defined as 0.

[0148] Verifiably quantify the vibration failure mode of bearing seat resonance.

[0149] Table 10 Quantification of the verifiability of bearing seat resonant vibration failure mode

[0150]

[0151] In Table 10: B = 2 × 4 + 2 × 2 + 2 × 1 + 3 × 4 = 26;

[0152] b=26÷(3×4+2×2+2×1+3×4)=26÷30=0.87.

[0153] The vibration failure mode of the rear bearing casing resonance is verifiably quantified.

[0154] Table 11 Quantification of the verifiability of the resonant vibration failure mode of the rear bearing casing

[0155]

[0156] In Table 11: B = 3 × 4 + 2 × 2 + 2 × 1 + 3 × 4 = 30;

[0157] b=30÷(3×4+2×2+2×1+3×4)=30÷30=1.00.

[0158] S04: Perform joint quantification based on the authenticity quantification results and the verifiability quantification results.

[0159] The authenticity quantification and the verifiability quantification are divided into multiple levels with increasing values. Specifically, in this embodiment, they are divided into five levels, respectively: {[0 0.2], (0.2

[0160] 0.4], (0.4 0.6], (0.6 0.8], (0.8 1]}.

[0161] The level to which the vibration fault mode belongs is determined according to the obtained authenticity quantification results and verifiability quantification results, and a joint quantification distribution table is formed. Table 12 below shows the joint quantization distribution table of this embodiment.

[0162] Table 12 Joint quantization distribution table

[0163]

[0164] In Table 12, A: friction vibration failure mode; B: rotor third-order critical vibration failure mode; C: rotor thermal bending vibration failure mode; D: rotor loose connection vibration failure mode; E: bearing seat resonance vibration failure mode; F: rear bearing casing resonance vibration failure mode.

[0165] Although there are many vibration failure modes, the differences between the various vibration failure modes are clearly presented in Table 12 through quantification. Based on the quantification results shown in Table 12, troubleshooting decisions can be made more efficiently and reasonably. Specifically, first, the resonance vibration failure mode of the rear bearing casing is verified, verification tests are planned, rectification measures are formulated, and experimental verification of the vibration failure mode is carried out; secondly, preliminary preparations for the verification of the resonance vibration failure mode of the bearing seat are made simultaneously. In view of the relatively low manufacturing cost of the bearing seat and the short processing and manufacturing period, the frequency modulation structure of the bearing seat is optimized, and the optimized new structure is processed and manufactured. If the rectification measures of the rear bearing casing are verified to be ineffective, the relevant verification of the bearing seat can be carried out immediately.

[0166] An embodiment of the present invention further provides a multi-dimensional quantification system for aircraft engine vibration faults, which can be used to implement the above-mentioned multi-dimensional quantification method for aircraft engine vibration faults. In this embodiment, the multi-dimensional quantification system for aircraft engine vibration faults includes:

[0167] The acquisition module is used to acquire multiple vibration failure modes that cause vibration failures. Specifically, the acquisition module can obtain the multiple vibration failure modes through external input, or can also obtain multiple possible vibration failure modes of the vibration failure by analyzing previous expert experience and test analysis data through setting an analysis module.

[0168] The calculation module is used to calculate the first dimension quantitative calculation results for various vibration failure modes according to the quantitative calculation method, and the calculation module is also used to calculate the second dimension quantitative results for various vibration failure modes according to the quantitative calculation method.

[0169] Specifically, the calculation module can be used to execute step S02 and step S03, and a pre-set authenticity quantification table and a verifiability quantification table can be stored therein. After the acquisition module acquires multiple vibration fault modes, the calculation module forms an authenticity quantification table (for example, Table 2-Table 7) and a verifiability quantification table (for example, Table 9-Table 11) for each vibration fault mode, and obtains the authenticity quantification result and the verifiability quantification result of each vibration fault mode.

[0170] The joint quantization module is used to perform joint quantization based on the first dimension quantization result and the second dimension quantization result.

[0171] Specifically, the joint quantization module jointly quantizes the authenticity quantization results and the verifiability quantization results obtained by the calculation module to form a joint quantization table as shown in Table 12.

[0172] The above description is only a specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by any technician familiar with the technology in the field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. A multi-dimensional quantification method for aircraft engine vibration failure, characterized by: The multi-dimensional quantification method for aircraft engine vibration failure includes: Obtain various vibration failure modes that cause vibration failures; According to the quantitative calculation method, the first dimension of the plurality of vibration failure modes is quantified respectively, and the first dimension quantification result is obtained; According to the quantitative calculation method, the second dimension quantification is performed on the plurality of vibration failure modes respectively, and the second dimension quantification results are obtained; Joint quantization is performed according to the first dimensional quantization result and the second dimensional quantization result.

2. The multi-dimensional quantification method for aircraft engine vibration failure according to claim 1, characterized in that: The quantitative calculation method comprises: Formulate a quantization table, the step of formulating the quantization table comprising: Determine the set of factors U that can be considered for the vibration fault: U = {U1, U2, ..., U m }; the factor set contains m factors; determine the weight set W corresponding to the factor set: W = {w1, w2, ..., wm}; the weight set contains m weight coefficients, and the weight coefficients correspond to the factors one by one; determine the evaluation set V of each factor i :V i = {V i1 ,V i2 ,……,V ij }; The evaluation set contains J evaluation values, and the evaluation values ​​in the evaluation value set are arranged in order from large to small, and the number of evaluation values ​​J in the evaluation sets of different factors does not need to be consistent; The plurality of vibration failure modes are quantified respectively according to the quantification table, and quantification results are obtained.

3. The multi-dimensional quantification method for aircraft engine vibration failure according to claim 2 is characterized in that: The steps of quantifying various vibration failure modes according to the quantification table and obtaining the quantification results include: Determine the evaluation of the vibration failure mode under each of the factors and the corresponding evaluation value r i , r i ∈Vi; multiple evaluation values ​​r i Construct an evaluation vector R, R = {r1, r2, ... r m }; The quantified value B of the vibration failure mode is obtained according to the following formula: Among them, R′ is the transpose of the evaluation vector R; Using the quantized value B as the quantized result; or, Normalize the quantized value B to obtain the normalized result b: b = B / A; The normalized result b is used as the quantization result.

4. The multi-dimensional quantification method for aircraft engine vibration failure according to claim 2, characterized in that: The steps to determine the set of factors that can be considered for vibration failure include: The vibration fault is decomposed to obtain a plurality of factors causing the vibration fault, and a plurality of the factors constitute the factor set.

5. The multi-dimensional quantification method for aircraft engine vibration failure according to claim 4 is characterized in that: The first dimension quantification is authenticity quantification; The set of factors for quantifying authenticity includes the mechanism of the failure mode, the conditions under which the failure mode occurs, the consistency with existing test data, and the fact that the failure can be virtually verified through simulation analysis.

6. The multi-dimensional quantification method for aircraft engine vibration failure according to claim 5, characterized in that: The evaluation set of the mechanism of the failure mode includes: the mechanism is clear and does not contradict the basic principles of physics; the failure mechanism is not easy to judge; The evaluation set of conditions for the occurrence of the failure mode includes: very likely to occur; likely to occur; not easy to judge; unlikely to occur; The evaluation set of consistency with the existing test data includes: consistency, no contradiction; partial consistency, no contradiction; no contradiction, but also unable to show its consistency; contradiction with some data; The evaluation set of the faults that can be virtually verified through simulation analysis includes: the simulation analysis results are consistent with the measured results, and the simulation analysis boundary conditions are relatively reasonable; the simulation analysis results are consistent with the measured results, and the rationality of the simulation analysis boundary conditions cannot be judged; the fault mode cannot be reproduced through existing simulation technology.

7. The multi-dimensional quantification method for aircraft engine vibration failure according to claim 4, characterized in that: The second dimension quantification is verifiability quantification; The set of factors for quantifying verifiability includes: the possibility of experimental verification based on existing technologies, the time cost of the verification test, the cost of the verification test, and the possibility of step-by-step verification at each level.

8. The multi-dimensional quantification method for aircraft engine vibration failure according to claim 7, characterized in that: The evaluation set that can be experimentally verified based on existing technologies includes: verifiable, verification technology is mature; partially verified, verification technology is mature; partially verified, and verification technology is not mature; temporarily unverifiable; Wherein, when the vibration failure mode is evaluated as temporarily unverifiable for the test verification based on the prior art, the verifiability quantification result is defined as 0; The evaluation set of the time cost of the verification test includes: no risk of delaying the project progress; there is a risk of delaying the project progress, but the risk level is low; there is a serious risk of delaying the project progress; The evaluation set of the cost of the validation test includes: the cost is very small; the cost is large but acceptable; the cost is expensive and needs to be carefully considered; The evaluation set that can be verified step by step at each level includes: can be verified step by step at each level; can perform a small part verification before the final verification; cannot be verified step by step, and can only perform the final verification.

9. The multi-dimensional quantification method for aircraft engine vibration failure according to claim 1, characterized in that: The step of performing joint quantization according to the first dimension quantization result and the second dimension quantization result includes: Divide the first dimension quantization and the second dimension quantization into a plurality of levels with increasing values; The level to which the vibration fault mode belongs is determined according to the obtained quantization result of the first dimension and the quantization result of the second dimension, and a joint quantization distribution table is formed.

10. A multi-dimensional quantification system for aircraft engine vibration faults, characterized by: The multi-dimensional quantification system for aircraft engine vibration failures includes: An acquisition module, the acquisition module is used to acquire multiple vibration failure modes that cause vibration failure; A calculation module, the calculation module is used to calculate the first dimension quantization results of the plurality of vibration failure modes according to the quantitative calculation method; the calculation module is also used to calculate the second dimension quantization results of the plurality of vibration failure modes according to the quantitative calculation method; A joint quantization module, wherein the joint quantization module is used to perform joint quantization according to the first dimensional quantization result and the second dimensional quantization result.

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