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

Abstract

The application provides an aero-engine vibration fault multi-dimension quantification method and system, and relates to the technical field of aero-engines. The aero-engine vibration fault multi-dimension quantification method comprises the following steps: obtaining multiple vibration fault modes causing vibration faults; performing first-dimension quantification on the multiple vibration fault modes according to a quantification calculation method, and obtaining a first-dimension quantification result; performing second-dimension quantification on the multiple vibration fault modes according to the quantification calculation method, and obtaining a second-dimension quantification result; and performing joint quantification according to the first-dimension quantification result and the second-dimension quantification result. The aero-engine vibration fault multi-dimension quantification method can quantify the vibration fault modes based on the first dimension and the second dimension, so that a verification strategy of the vibration fault modes can be formulated according to the quantification result, and the vibration faults can be timely, quickly and efficiently eliminated, thereby having strong engineering application value.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engines, in particular to an aero-engine vibration fault multi-dimension quantification method and system. BACKGROUND

[0002] In the 1920s, Jeffcott, a British dynamician, broke the shackles of the concept that "rotors cannot work above the first critical speed", and a large number of rotating machines were designed to operate at supercritical speed. As the rotor speed is getting higher and higher, the vibration problem of the equipment has attracted more attention and research.

[0003] Fault tree analysis technology (FTA) first needs to establish a fault tree model composed of fault events, based on which qualitative analysis of faults can be carried out, and secondly, based on the occurrence probability of fault events, quantitative analysis of the reliability of the system can be carried out. For a relatively complex system in the development stage, it is relatively difficult to apply fault tree analysis technology for vibration fault diagnosis. Although the literature "Compressor Vibration Fault Analysis Based on Fault Tree Analysis Method" applies fault tree analysis technology to the vibration fault of the compressor, the fault tree model is composed of 33 bottom events, and the occurrence probability of the bottom events cannot be quantified, only qualitative analysis can be carried out. The fault reason "3 pieces of tip of the first stage rotor blade of the compressor rub against the corresponding casing" leads to a large change in the rotor unbalance, which is more likely to be found through "hole exploration" than the result of fault tree analysis.

[0004] The aero-engine in the development stage is a very complex system, and its vibration fault mode is unknown, so it is difficult to diagnose based on the existing vibration fault characteristics. For a complex system, especially when multiple factors are coupled, the event boundary is not clear, and it is also difficult to create a fault tree composed of various independent events; even if the fault tree is created, it is difficult to analyze due to the complexity and largeness of the fault tree model. SUMMARY

[0005] The purpose of the present application is to provide an aero-engine vibration fault multi-dimension quantification method and system, which can improve the technical problem that the existing aero-engine vibration fault is difficult to timely, quickly and efficiently complete the elimination of vibration fault.

[0006] The embodiments of the present application can be implemented in the following way:

[0007] An aero-engine vibration fault multi-dimension quantification method comprises obtaining multiple vibration fault modes causing vibration faults;

[0008] According to the quantification calculation method, the multiple vibration fault modes are respectively subjected to first-dimension quantification, and a first-dimension quantification result is obtained;

[0009] According to the quantification calculation method, the plurality of vibration fault modes are respectively quantified in a second dimension, and a second dimension quantification result is obtained;

[0010] According to the first dimension quantification result and the second dimension quantification result, joint quantification is performed.

[0011] Optionally, the quantification calculation method comprises:

[0012] A quantification table is formulated, and the step of formulating the quantification table comprises:

[0013] A factor set U that can be considered for the vibration fault is determined: U = {U1, U2, …, Um}; the factor set contains m factors; a weight set W corresponding to the factor set is determined: W = {w1, w2, …, wm}; the weight set contains m weight coefficients, and each weight coefficient corresponds to one factor; an evaluation set V of each factor is determined: V = {V1, V2, …, VJ}; the evaluation set contains J evaluation values, and the evaluation values in the evaluation set are arranged in descending order; the number of evaluation values in the evaluation set of different factors does not need to be consistent; m}; i i i1 i2 ij};

[0014] According to the quantification table, the plurality of vibration fault modes are respectively quantified, and a quantification result is obtained.

[0015] Optionally, the step of quantifying the plurality of vibration fault modes according to the quantification table and obtaining a quantification result comprises:

[0016] The evaluation of the vibration fault mode under each factor and the corresponding evaluation value r i , r i ∈ Vi are determined; a plurality of evaluation values r i constitute an evaluation vector R, R = {r1, r2, …, rm}; m};

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

[0018]

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

[0020] The quantification value B is taken as the quantification result; or,

[0021] The quantification value B is normalized to obtain a normalized result b:

[0022] ​​​​b = B / A;

[0023]

[0024] quantifying the normalization result b.

[0025] Optionally, the step of determining the set of factors that can be considered for the vibration fault comprises:

[0026] decomposing the vibration fault to obtain a plurality of factors that cause the vibration fault, the plurality of factors constituting the set of factors.

[0027] Optionally, the set of factors for the authenticity quantification comprises mechanism of the fault mode, condition for the fault mode to occur, consistency with existing test data, and the fault mode being able to be virtually verified through simulation analysis.

[0028] Optionally, the set of evaluations for the mechanism of the fault mode comprises: the mechanism being clear and not contradicting the basic principles of physics; the fault mechanism being difficult to judge;

[0029] the first dimension quantification being authenticity quantification; the set of evaluations for the condition for the fault mode to occur comprises: the fault mode being likely to occur; the fault mode being possible to occur; the fault mode being difficult to judge; the fault mode being unlikely to occur;

[0030] the set of evaluations for the consistency with existing test data comprises: consistent, no contradiction; partially consistent, no contradiction; no contradiction, but also unable to show consistency; contradiction with part of the data;

[0031] the set of evaluations for the fault mode being able to be virtually verified through simulation analysis comprises: the simulation analysis result is consistent with the actual measurement result, and the simulation analysis boundary condition is reasonable; the simulation analysis result is consistent with the actual measurement result, and the reasonability of the simulation analysis boundary condition is difficult to judge; the fault mode cannot be reproduced through existing simulation technology.

[0032] Optionally, the second dimension quantification is verifiability quantification; the set of factors for the verifiability quantification comprises: the fault mode being able to be verified based on existing technology, time cost of verification test, cost of verification test, and step-by-step verification being able to be performed at different levels.

[0033] Optionally, the set of evaluations for the fault mode being able to be verified based on existing technology comprises: the fault mode being able to be verified, verification technology being mature; the fault mode being partially verified, verification technology being mature; the fault mode being partially verified, and verification technology being not very mature; the fault mode being temporarily unable to be verified;

[0034] wherein, when an evaluation of the vibration fault mode for the fault mode being able to be verified based on existing technology is temporarily unable to be verified, the verifiability quantification result is defined as 0;

[0035] The time cost evaluation set of the verification test includes: no delay risk for project progress; low risk for project progress delay; serious delay risk for project progress;

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

[0037] The step-by-step verification evaluation set includes: step-by-step verification; small part verification before final verification; and final verification only.

[0038] Optionally, the step of jointly quantifying according to the first dimension quantification result and the second dimension quantification result includes:

[0039] The first dimension quantification and the second dimension quantification are divided into multiple value-increasing levels.

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

[0041] An aero-engine vibration fault multi-dimension quantification system includes an acquisition module configured to acquire multiple vibration fault modes causing vibration faults; a calculation module configured to calculate a first dimension quantification result for each of the multiple vibration fault modes according to a quantification calculation method; the calculation module is further configured to calculate a second dimension quantification result for each of the multiple vibration fault modes according to the quantification calculation method; and a joint quantification module configured to jointly quantify according to the first dimension quantification result and the second dimension quantification result.

[0042] The aero-engine vibration fault multi-dimension quantification method and system provided by the embodiments of the present application have the following beneficial effects:

[0043] The aero-engine vibration fault multi-dimension quantification method provided by the embodiments of the present application includes acquiring multiple vibration fault modes causing vibration faults; performing first dimension quantification on each of the multiple vibration fault modes according to a quantification calculation method, and obtaining a first dimension quantification result; performing second dimension quantification on each of the multiple vibration fault modes according to the quantification calculation method, and obtaining a second dimension quantification result; and jointly quantifying according to the first dimension quantification result and the second dimension quantification result. The aero-engine vibration fault multi-dimension quantification method can quantize the vibration fault modes based on the first dimension, the second dimension, and other dimensions, so as to formulate a verification strategy for the vibration fault modes according to the quantification results, and then timely, quickly and efficiently complete the elimination of the vibration faults, and has strong engineering application value.

[0044] The embodiment of the present application provides the aviation engine vibration fault multi-dimension quantification system, can quantize based on vibration fault mode multiple dimensions, so that the verification strategy of the vibration fault mode can be formulated according to the quantification result, and then the vibration fault can be timely, quickly and efficiently eliminated, and the beneficial effects of strong engineering application value are achieved. BRIEF DESCRIPTION OF DRAWINGS

[0045] The above features and advantages of the present application can be better understood by reading the detailed description of embodiments of the present application in conjunction with the following drawings, in which the components are not necessarily drawn to scale and components of similar or identical function or features can have the same or similar reference label.

[0046] Figure 1 A step diagram of an aviation engine vibration fault multi-dimension quantification method according to an aspect of the present application is shown;

[0047] Figure 2 A relationship diagram of decomposing a vibration fault to obtain multiple factors according to an aspect of the present application is shown;

[0048] Figure 3 A relationship diagram of decomposing a vibration fault verification process to obtain multiple factors according to an aspect of the present application is shown. DETAILED DESCRIPTION

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

[0050] In the description of the present application, it should be noted that if the terms such as "upper", "lower", "inner", "outer", "vertical" and the like indicate the orientation or positional relationship shown in the drawings, or the orientation or positional relationship of the product in use, and are not indicative or suggestive of the device or element having a specific orientation or being constructed and operated in a specific orientation, therefore, it cannot be understood as limiting the present application.

[0051] At the same time, it should be noted that if the terms "first", "second" and the like are used only for differentiation description, and cannot be understood as indicating or suggesting relative importance.

[0052] In the description of the present application, it is also necessary to explain that, unless otherwise explicitly specified or limited, the terms "mounting", "connection", "connecting" should be understood broadly, for example, can be fixed connection, can be integrally connected, or can be detachably connected; can be mechanical connection, or can be electrical connection; can be directly connected, or can be indirectly connected through an intermediate medium, or internal communication of two elements, etc. The specific meaning of the above terms in the present application can be understood by the person skilled in the art according to the specific circumstances.

[0053] Figure 1 The step diagram of the multi-dimensional quantification method of the aero-engine vibration fault provided in the embodiment is shown in FIG. 1. Figure 1 The embodiment provides a multi-dimensional quantification method of aero-engine vibration fault, which comprises the following steps:

[0054] S01: Obtain a plurality of vibration fault modes causing vibration faults.

[0055] When a vibration fault occurs and the vibration fault needs to be excluded for the reason of the fault, etc., the vibration fault mode that may cause the vibration fault can be obtained according to the specific vibration fault analysis and test, or the vibration fault mode that may cause the vibration fault can also be obtained according to the experience of experts, etc.

[0056] Specifically, the embodiment takes the vibration fault of the core engine rotor and the vibration fault appearing on the rear support point as an example for illustration. The vibration fault is analyzed, and the possible vibration fault modes are preliminarily determined to include: rubbing, rotor third-order critical, rotor thermal bending, rotor connection not firm, bearing seat resonance, and rear load casing resonance. Through the subsequent steps of the multi-dimensional quantification method of the aero-engine vibration fault, a verification strategy is reasonably set for the plurality of vibration fault modes. It can be understood that the multi-dimensional quantification method of the aero-engine vibration fault can also be used for multi-dimensional quantification of other vibration faults, and the possible vibration fault modes of different vibration faults can be set accordingly. The vibration fault of the core engine rotor and the vibration fault appearing on the rear support point, and the possible vibration fault modes causing the vibration fault provided herein are only examples.

[0057] S02: According to the quantification calculation method, the plurality of vibration fault modes are respectively quantified in the first dimension, and a first dimension quantification result is obtained.

[0058] The quantification calculation method comprises formulating a quantification table, and the specific process of formulating the quantification table comprises:

[0059] S21: Determine the factor set U that can be considered for the vibration fault: U = {U1, U2, …, U m}.

[0060] By decomposing the vibration fault, multiple factors leading to the vibration fault are obtained. These multiple factors constitute a factor set, which contains m factors.

[0061] S22: Determine the weight set W for each factor: W = {W1, W2, ..., W...} m}

[0062] Determine the weight coefficients for each factor. Each weight coefficient corresponds to a factor, and the specific values ​​of the weight coefficients can be set based on expert experience, analytic hierarchy process, 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 up for each factor. The specific number of evaluations in each factor's evaluation set can be determined based on the specific content of the factor. Each evaluation set also has a corresponding evaluation value. The evaluation set V... i The set contains J evaluation values, and the evaluation values ​​in the set are arranged in ascending order, therefore the evaluation value V is... i1 This is the highest evaluation value in a set of evaluations. The evaluation value is used to characterize the differences between various evaluation levels, and its specific value can be set according to specific circumstances.

[0065] The quantitative calculation method also includes: quantifying multiple vibration fault modes according to a quantification table and obtaining the quantification results. This process includes: determining the evaluation of the vibration fault mode under each factor and the corresponding evaluation value r. i r i ∈Vi; multiple evaluation values ​​r i The evaluation vector R is formed, R = {r1, r2, ..., r}. m}

[0066] The quantization value B of the vibration fault 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 the embodiment, the normalized result b is taken as the quantization result, and in some other embodiments, the quantization value B can also be taken as the quantization result directly.

[0073] In the embodiment, the first dimension is quantized as a true-false quantization, and correspondingly, the first dimension quantization structure is a true-false quantization result. The true-false quantization result is a quantization of the possible occurrence probability of each vibration fault mode.

[0074] Therefore, according to the quantization calculation method, the multiple vibration fault modes are respectively quantized as true-false quantization, and the specific process of obtaining the true-false quantization result can include formulating a true-false quantization table, and quantizing the multiple vibration fault modes according to the true-false quantization table to obtain the quantization result.

[0075] In the embodiment, Table 1 below shows the true-false quantization table, which can be formulated according to steps S21, S22 and S23.

[0076] Table 1 True-false quantization table

[0077]

[0078]

[0079] The specific process of formulating the true-false quantization table is described below.

[0080] The process of performing step S21 is as follows: Figure 2 A relationship diagram for decomposing the vibration fault to obtain multiple factors is shown. As shown in Figure 2 The vibration fault mode can generally be divided into three parts of "due to …", "based on … mechanism / logical relationship" and "resulting in … phenomenon", and three factors that need to be considered in the vibration fault factor set are proposed for the three parts. Specifically, the three factors are the mechanism of the fault mode, the condition for the occurrence of the fault mode, and the consistency with the existing test data. At the same time, due to the rapid development of computer simulation technology, some vibration faults can be simulated vertically, and this direction can also be considered as a factor. Therefore, in the embodiment, the factor set for true-false quantization also includes the factor that the fault can be virtually verified through simulation analysis, that is, the number of factors m included in the factor set in the embodiment is 4. It should be noted that the number of factors in the factor set for true-false quantization can also be set according to requirements, for example, more factors of the vibration fault can be proposed in the future as the research further deepens.

[0081] The process of performing step S22 is as follows: In the embodiment, since the factor set of the vibration fault includes four factors, correspondingly, the weight set obtained also includes four weight coefficients.

[0082] Specifically, the weight coefficient W1 corresponding to the factor of the mechanism of the failure mode is 1; the weight coefficient W2 corresponding to the factor of the condition of the failure mode is 2; the weight coefficient W3 corresponding to the factor of the consistency with the existing test data is 2; and the weight coefficient W4 corresponding to the factor of the virtual verification of the failure through simulation analysis is 2.

[0083] The process of performing step S23 is as follows: specifically, the evaluation set V1 is determined for the factor 1: the mechanism of the failure mode; the evaluation set V2 is determined for the factor 2: the condition of the failure mode; the evaluation set V3 is determined for the factor 3: the consistency with the existing test data; and the evaluation set V4 is determined for the factor 4: the virtual verification of the failure through simulation analysis.

[0084] In this embodiment, the evaluation set of the mechanism of the failure mode includes: the mechanism is clear and does not conflict with the physical basic principle; and the failure mechanism is not easy to judge. Therefore, two evaluation values should be included in the evaluation set V1 of the mechanism of the failure mode.

[0085] The evaluation set of the condition of the failure mode includes: the condition is likely to occur; the condition is possible to occur; the condition is not easy to judge; and the condition is not likely to occur. That is, four evaluation values should be included in the evaluation set V2 of the condition of the failure mode.

[0086] The evaluation set of the consistency with the existing test data includes: the consistency is consistent and has no conflict; the consistency is partially consistent and has no conflict; the consistency has no conflict but cannot indicate the consistency; and the consistency has conflict with part of the data. That is, four evaluation values should be included in the evaluation set V3 of the consistency with the existing test data.

[0087] The evaluation set of the virtual verification of the failure through simulation analysis includes: the simulation analysis result is consistent with the measured result, and the simulation analysis boundary condition is reasonable; the simulation analysis result is consistent with the measured result, and the reasonability of the simulation analysis boundary condition cannot be judged; and the failure mode cannot be reproduced through the existing simulation technology. That is, three evaluation values should be included in the evaluation set V4 of the virtual verification of the failure through simulation analysis.

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

[0089] The authenticity of the vibration failure mode of the impact and friction is quantified.

[0090] Table 2: Authenticity quantification of the impact and friction vibration failure mode

[0091]

[0092] In Table 2: B = 3x1 + 1x2 + 2x2 + 0x2 = 9;

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

[0094] The rotor third order critical speed vibration fault mode is quantified for authenticity.

[0095] Table 3 rotor third order critical speed vibration fault mode authenticity quantification

[0096]

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

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

[0099] The rotor thermal bending vibration fault mode is quantified for authenticity.

[0100] Table 4 rotor thermal bending vibration fault mode authenticity quantification

[0101]

[0102]

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

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

[0105] The rotor connection is not firm vibration fault mode is quantified for authenticity.

[0106] Table 5 rotor connection is not firm vibration fault mode authenticity quantification

[0107]

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

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

[0110] The bearing seat resonance vibration fault mode is quantified for authenticity.

[0111] Table 6 bearing seat resonance vibration fault mode authenticity quantification

[0112]

[0113]

[0114] In Table 6: B = 3x1 + 3x2 + 3x2 + 1x2 = 17;

[0115] b = 17 ÷ (3x1 + 3x2 + 3x2 + 4x2) = 17 ÷ 23 = 0.74.

[0116] The authenticity of the vibration fault mode of the rear load-bearing nacelle resonance is quantified.

[0117] Table 7 authenticity quantification of the vibration fault mode of the rear load-bearing nacelle resonance

[0118]

[0119]

[0120] In Table 7: B = 3x1 + 3x2 + 3x2 + 3x2 = 21;

[0121] b = 21 ÷ (3x1 + 3x2 + 3x2 + 4x2) = 21 ÷ 23 = 0.91.

[0122] S03: According to the quantification calculation method, the second dimension quantification is performed on the plurality of vibration fault modes, and the second dimension quantification result is obtained.

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

[0124] Since the verifiability quantification of the vibration fault mode is also obtained according to the quantification calculation method, the specific process of performing step S03 can include formulating a verifiability quantification table, and quantifying a plurality of vibration fault modes according to the verifiability quantification table, and obtaining the quantification result.

[0125] In this embodiment, Table 8 below shows the verifiability quantification table, which can be formulated according to steps S21, S22 and 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 performing step S21 is as follows: Figure 3A decomposition of the verification process of the vibration fault is shown to obtain a relationship diagram of a plurality of factors. As shown in Figure 2 The verification of the vibration fault of the aero-engine can be considered from the maturity of the related technology, the cost and period required for the verification implementation, and thus the related factors of the vibration fault verifiability are obtained in terms of the three aspects. Specifically, the factors are that the test verification can be based on the existing technology, the time cost of the verification test, and the cost of the verification test. Meanwhile, due to the complexity of the aero-engine, it is difficult to verify the performance change of a certain part in the whole system, and generally a hierarchical verification needs to be carried out: first, a certain technical problem is verified in a relatively simple part environment, then verified on a relatively complex simulation tester, and finally verified at the whole machine level, so it is necessary to consider the hierarchical nature of the verification. Therefore, the factor set of the verifiability quantification also includes the factor that the step-by-step verification of the hierarchical level can be carried out, and thus in the embodiment, the number of factors m in the factor set of the verifiability quantification is 4.

[0131] The process of performing step S22: in the embodiment, since the factor set of the verifiability quantification contains four factors, the weight set obtained also contains four weight coefficients.

[0132] Specifically, the weight coefficient W1 corresponding to the factor that the test verification can be based on the existing technology is 4; the weight coefficient W2 corresponding to the factor of the time cost of the verification test is 2; the weight coefficient W3 corresponding to the factor of the cost of the verification test is 1; and the weight coefficient W4 corresponding to the factor that the step-by-step verification of the hierarchical level can be carried out is 4.

[0133] The process of performing step S23: specifically, for factor 1: the test verification can be based on the existing technology, the evaluation set V1 is determined; for factor 2: the time cost of the verification test, the evaluation set V2 is determined; for factor 3: the cost of the verification test, the evaluation set V3 is determined; and for factor 4: the step-by-step verification of the hierarchical level can be carried out, the evaluation set V4 is determined.

[0134] In the embodiment, the evaluation set of the test verification based on the existing technology includes: verifiable, verification technology mature; partially verifiable, verification technology mature; partially verifiable, and verification technology not very mature; temporarily unverifiable.

[0135] Wherein, when the evaluation of a certain vibration fault mode for the test verification based on the existing technology is temporarily unverifiable, the verifiability quantification result is defined as 0.

[0136] The evaluation set of the time cost of the verification test includes: no delay risk to the project progress; low risk of delay to the project progress; and serious delay risk to the project progress.

[0137] The evaluation set of cost of verification test includes: very small cost; relatively large cost but acceptable; expensive cost and needs to be considered carefully.

[0138] The evaluation set of step-by-step verification at each level includes: step-by-step verification at each level; small part verification before final verification; and final verification only.

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

[0140] For the vibration fault mode of rubbing, since the cause of rubbing is uncertain, it is difficult to perform test verification, and therefore the quantification result of verifiability of rubbing is defined as 0.

[0141] The vibration fault mode of the third order critical speed of the rotor is quantified for verifiability.

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

[0143]

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

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

[0146] For the vibration fault mode of rotor thermal bending, since the cause of rotor thermal bending is uncertain, and the temperature field of the rotor can also be simulated to verify the thermal bending of the rotor under rotating conditions, it is difficult to verify, and therefore the quantification result of verifiability of rotor thermal bending is defined as 0.

[0147] For the vibration fault mode of loose connection of the rotor, since it is related to the actual temperature field, and the specific mechanism of "incoordination of rotor deformation and local loose connection" is not clear, it is difficult to verify, and therefore the quantification result of verifiability of loose connection of the rotor is defined as 0.

[0148] The vibration fault mode of bearing seat resonance is quantified for verifiability.

[0149] Table 10: Quantification of verifiability of the vibration fault mode of bearing seat resonance

[0150]

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

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

[0153] The verifiability quantification of the rear load casing resonance vibration fault mode is performed.

[0154] Table 11 Verifiability quantification of the rear load casing resonance vibration fault mode

[0155]

[0156] In Table 11, B = 3 x 4 + 2 x 2 + 2 x 1 + 3 x 4 = 30.

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

[0158] S04: Joint quantification is performed according to the authenticity quantification result and the verifiability quantification result.

[0159] The authenticity quantification and the verifiability quantification are divided into multiple numerical increasing levels. Specifically, in the embodiment, five levels are divided respectively, which are {[0 0.2], (0.2 0.4], (0.4 0.6], (0.6 0.8], (0.8 1]} respectively.

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

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

[0162] Table 12 Joint quantification distribution table

[0163]

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

[0165] Although there are various vibration fault modes, the differences between the various vibration fault modes are obviously presented in Table 12 through quantification, and based on the quantification results as shown in Table 12, troubleshooting decisions can be made more efficiently and reasonably. Specifically, first, the rear load casing resonance vibration fault mode is verified, a verification test is planned, an improvement measure is formulated, and a vibration fault mode test verification is performed; second, the preliminary preparation for the bearing seat resonance vibration fault mode verification is simultaneously completed, and the bearing seat is optimized in frequency modulation structure, and the new structure after optimization is processed and manufactured, and if the rear load casing improvement measure is not verified to be effective, the related verification of the bearing seat can be immediately carried out.

[0166] Embodiments of the present application also provide an aero-engine vibration fault multi-dimensional quantification system, which can be used to implement the aero-engine vibration fault multi-dimensional quantification method described above. In the present embodiment, the aero-engine vibration fault multi-dimensional quantification system comprises:

[0167] The acquisition module is used to acquire a plurality of vibration fault modes causing the vibration fault. Specifically, the acquisition module can obtain the plurality of vibration fault modes through external input, or the vibration fault modes can be obtained by analyzing the previous expert experience and test analysis data through the analysis module or other means.

[0168] The calculation module is used to calculate the first-dimensional quantification calculation result of each vibration fault mode according to the quantification calculation method, and the calculation module is also used to calculate the second-dimensional quantification result of each vibration fault mode according to the quantification calculation method.

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

[0170] The joint quantification module is used to perform joint quantification according to the first-dimensional quantification result and the second-dimensional quantification result.

[0171] Specifically, the joint quantification module performs joint quantification on the authenticity quantification result and the verifiability quantification result obtained by the calculation module to form the joint quantification table as shown in Table 12.

[0172] The above merely illustrates the specific embodiments of the present application, but the protection scope of the present application is not limited thereto, and any person skilled in the art can easily think of the changes or replacements within the technical scope disclosed by the present application, which should be covered within the protection scope of the present application.

Claims

1. A multi-dimensional quantification method for vibration faults in aero-engines, characterized in that: The multi-dimensional quantification method for aero-engine vibration faults includes: To acquire multiple vibration fault modes that cause vibration failure; The vibration fault modes are quantized in the first dimension according to the quantization calculation method, and the first dimension quantization result is obtained; wherein, the first dimension quantization is the authenticity quantization. The vibration fault modes are quantized in the second dimension according to the quantization calculation method, and the second dimension quantization results are obtained; wherein, the second dimension quantization is verifiable quantization. Joint quantization is performed based on the quantization results of the first dimension and the quantization results of the second dimension. The steps for joint quantization based on the quantization results of the first dimension and the quantization results of the second dimension include: The first and second dimensions of quantization are divided into multiple numerically increasing levels; Based on the obtained first-dimensional quantization results and second-dimensional quantization results, the level to which the vibration fault mode belongs is determined, and a joint quantization distribution table is formed.

2. The multi-dimensional quantification method for aero-engine vibration faults according to claim 1, characterized in that: The quantization calculation method includes: The steps for developing a quantification table include: The set of factors U that can be considered for the vibration fault is: 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 one-to-one with the factors; determine the evaluation set V for 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 set are arranged in descending order. The number J of evaluation values ​​in the evaluation sets of different factors does not need to be the same. The various vibration fault modes are quantified according to the quantization table, and the quantization results are obtained.

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

4. The multi-dimensional quantification method for aero-engine vibration faults according to claim 2, characterized in that: The steps to determine the set of factors to consider for vibration faults include: The vibration fault is decomposed to obtain multiple factors that cause the vibration fault, and the multiple factors constitute the factor set.

5. The multi-dimensional quantification method for aero-engine vibration faults according to claim 4, characterized in that: 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 aero-engine vibration faults according to claim 5, characterized in that: The evaluation set of the failure modes' mechanisms includes: mechanisms that are clear and do not contradict basic physical principles; and failure mechanisms that are not easy to determine. The evaluation set of conditions for the occurrence of the failure mode includes: likely to occur; possible; difficult to determine; unlikely to occur; The evaluation set for consistency with existing test data includes: consistent, with no contradictions; partially consistent, with no contradictions; no contradictions, but still cannot demonstrate consistency; and contradictory to some data. The evaluation set of 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 reasonableness of the simulation analysis boundary conditions cannot be judged; and the fault mode cannot be reproduced by existing simulation technology.

7. The multi-dimensional quantification method for aero-engine vibration faults according to claim 4, characterized in that: The set of factors for quantifying verifiability includes: the ability to conduct experimental verification based on existing technology, the time cost of verification experiments, the cost of verification experiments, and the ability to conduct step-by-step verification at different levels.

8. The multi-dimensional quantification method for aero-engine vibration faults according to claim 7, characterized in that: The evaluation set that can be experimentally verified based on existing technologies includes: verifiable, with mature verification technology; partially verifiable, with mature verification technology; partially verifiable, with less mature verification technology; and temporarily unverifiable. Wherein, if a vibration failure mode is evaluated as temporarily unverifiable based on existing technology, the verifiability quantification result is defined as 0. The evaluation set of time costs for the verification experiment includes: no risk of project delay; risk of project delay, but low level of risk; and risk of serious project delay. The cost evaluation set for the verification test includes: very low cost; high cost, but acceptable cost; and expensive cost, requiring careful consideration. The evaluation set that can be verified step by step includes: those that can be verified step by step; those that can be partially verified before final verification; and those that cannot be verified step by step and can only be verified in the final stage.

9. A multi-dimensional quantification system for vibration faults in aero-engines, characterized in that: The multi-dimensional quantification system for aero-engine vibration faults includes: An acquisition module is used to acquire multiple vibration fault modes that cause vibration faults; The calculation module is used to calculate and obtain a first-dimensional quantization result for each of the various vibration fault modes according to a quantization calculation method; the calculation module is also used to calculate and obtain a second-dimensional quantization result for each of the various vibration fault modes according to a quantization calculation method; wherein, the first-dimensional quantization is a authenticity quantization, and the second-dimensional quantization is a verifiability quantization. The joint quantization module is used to perform joint quantization based on the first dimension quantization result and the second dimension quantization result. The joint quantization process includes: dividing the first dimension quantization and the second dimension quantization into multiple numerically increasing levels; determining the level to which the vibration fault mode belongs based on the obtained first dimension quantization result and the second dimension quantization result, and forming a joint quantization distribution table.

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