CN114812994A - Method for identifying dynamic vibration measurement mode of aero-engine blade based on inner product correlation - Google Patents

Method for identifying dynamic vibration measurement mode of aero-engine blade based on inner product correlation Download PDF

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CN114812994A
CN114812994A CN202210375079.0A CN202210375079A CN114812994A CN 114812994 A CN114812994 A CN 114812994A CN 202210375079 A CN202210375079 A CN 202210375079A CN 114812994 A CN114812994 A CN 114812994A
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stress
vibration mode
inner product
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杜青
张建
刘一雄
郭勇
李莹
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AECC Shenyang Engine Research Institute
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M7/00—Vibration-testing of structures; Shock-testing of structures
    • G01M7/02—Vibration-testing by means of a shake table
    • G01M7/022—Vibration control arrangements, e.g. for generating random vibrations
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/14—Testing gas-turbine engines or jet-propulsion engines
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M7/00—Vibration-testing of structures; Shock-testing of structures
    • G01M7/02—Vibration-testing by means of a shake table
    • G01M7/025—Measuring arrangements
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
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Abstract

The application provides an aeroengine blade dynamic vibration measurement type identification method based on inner product correlation, which comprises the following steps: arranging a plurality of stress measuring points on the blade to obtain the resonant rotating speed, the resonant frequency and the actually measured stress value of the blade, and expressing the actually measured stress value as an actually measured stress vector; carrying out dynamic frequency analysis under different rotating speed conditions to obtain frequency values and node stress of each order under each rotating speed condition, and establishing a dynamic frequency database; selecting a dynamic frequency rotating speed closest to the resonance rotating speed from a dynamic frequency database, and selecting a plurality of frequencies with the resonance frequency in a preset range to determine the frequencies as suspected resonance type frequencies; respectively selecting the calculated stress values of a plurality of stress measuring points in the suspected vibration mode, and expressing the calculated stress values as the calculated stress vector of each suspected vibration mode; calculating the inner product correlation degree between the actually measured stress vector and each calculated stress vector; and determining the most relevant inner product correlation degree of the calculated stress vector and the measured stress vector according to the magnitude, wherein the suspected vibration mode frequency corresponding to the most relevant inner product correlation degree is the vibration mode frequency corresponding to the resonance vibration mode.

Description

Method for identifying dynamic vibration measurement mode of aero-engine blade based on inner product correlation
Technical Field
The application belongs to the technical field of aero-engines, and particularly relates to an aero-engine blade dynamic vibration measurement type identification method based on inner product correlation.
Background
Due to the influences of factors such as centrifugal force, temperature and aerodynamic force, a compressor and turbine blades in an aircraft engine bear large load in the actual working state of the engine, and forced resonance and blade vibration induced by airflow may occur, even destructive vibration is generated, and the safety and the service life of the engine are damaged. Therefore, in the work of engine development, troubleshooting and the like, the dynamic stress measurement work of the blade must be carried out.
The dynamic stress measurement test of the engine blade can obtain the resonant frequency of the blade and the dynamic stress value of the position of the patch under different working conditions. Because the number of the strain gauges is limited, the maximum vibration stress of each resonance vibration mode is difficult to monitor comprehensively, so that blade resonance vibration mode judgment and maximum stress conversion are required to be carried out according to limited data information, and whether the maximum vibration stress point under each resonance vibration mode meets the requirement of high-cycle fatigue life is further judged so as to ensure the safe operation of an engine.
In a current engine blade dynamic stress measurement (dynamic measurement for short) test, the judgment process of the blade resonance vibration mode is as follows:
1) selecting strain gauges on the same blade, and recording the actually measured resonance frequency of the blade and the actually measured vibration stress of different strain gauges at a certain resonance time;
2) carrying out dynamic frequency analysis on the blades at corresponding or similar rotating speeds to obtain blade calculation resonance frequency considering centrifugal force and temperature influence and calculation relative vibration stress of corresponding patch positions and patch directions;
3) comparing the measured resonance frequency with the theoretical calculation frequency, and determining the frequency difference as a suspected vibration mode within an acceptable range;
4) and determining a suspected vibration mode according to the frequency, comparing the actually measured and calculated vibration stress ratios of different measuring points, determining that the ratios are not reverse and the difference of the ratios is within an acceptable range, and determining the order vibration mode.
However, the above method or process for determining the resonant mode of the blade has the following disadvantages:
a) the vibration mode of the blade is judged according to the vibration stress ratio of each measuring point, the workload is complex, and certain subjectivity exists;
b) in the multi-wheel dynamic measurement process, the resonance frequency is very rich under the influence of factors such as working line adjustment, airflow attack angle change, intake distortion and the like, different vibration modes need to be repeatedly compared, and the working efficiency is low;
c) for the high-order vibration mode, vibration stress is large and is mostly concentrated at corner positions, the stress of the positions where no obvious vibration occurs is too small, the stress difference of each measuring point is very different, and a uniform high-order vibration mode identification standard is difficult to form; moreover, for an excessively small actually measured stress value, error factors of a test system are difficult to eliminate, the error brings great influence on a stress ratio value, and difficulty is increased for high-order vibration mode identification.
Disclosure of Invention
The application aims to provide an identification method of a dynamic vibration mode of an aero-engine blade based on inner product correlation, so as to solve or reduce at least one problem in the background art.
The technical scheme of the application is as follows: an aeroengine blade dynamic vibration measurement type identification method based on inner product correlation comprises the following steps:
arranging a plurality of strain gauges on the blade to form stress measurement points and carrying out a blade dynamic stress measurement test to obtain the resonance rotating speed and the resonance frequency of the blade and the actually measured stress values of the measurement points, and representing the actually measured stress values of the measurement points as an actually measured stress vector in sequence;
carrying out dynamic frequency analysis under different rotating speed conditions to obtain frequency values of each order and node stress of each strain gauge position under each rotating speed condition, and establishing a dynamic frequency database of the blade and the corresponding strain gauge arrangement scheme;
selecting a dynamic frequency rotating speed which is closest to the resonance rotating speed from a dynamic frequency database, and further selecting a plurality of frequencies within a preset range with the resonance frequency from the dynamic frequency database to determine the frequencies as suspected resonance type frequencies;
respectively selecting the calculated stress values of a plurality of stress measuring points in the suspected vibration mode, and commonly representing the calculated stress values as the calculated stress vector of each suspected vibration mode in sequence;
calculating the inner product correlation degree between the actually measured stress vector and each calculated stress vector;
and comparing the relative magnitude of each inner product correlation degree, determining the inner product correlation degree which is most relevant to the calculated stress vector and the measured stress vector, and then selecting the suspected vibration mode frequency corresponding to the most relevant inner product correlation degree from the dynamic frequency database as the vibration mode frequency corresponding to the resonance vibration mode.
Furthermore, the position of the strain gauge is selected to be close to the maximum stress point where the resonance mode is likely to occur according to the previous dynamic stress measurement result or the analytical result of the Campbell diagram.
Further, the positions where the vibration is obvious include a blade root position suitable for a first-order vibration mode and a blade tip position suitable for a high-order vibration mode.
Furthermore, the node stress direction of each strain gauge is consistent with the patch direction of the strain gauge.
Further, when a plurality of frequencies are selected from the dynamic frequency database and are determined as pseudo-mode frequencies, the difference from the range of the resonant frequency is 5%.
Further, the method for calculating the inner product correlation between the actually measured stress vector and each calculated stress vector comprises the following steps:
Figure BDA0003590027190000031
in the formula, C n Is the inner product correlation;
Figure BDA0003590027190000032
is an actually measured stress vector;
Figure BDA0003590027190000033
calculating a stress vector for the n-order mode shape;
σ A 、σ B 、σ C 、σ Z the measured stress value is the measured stress value of a measuring point A, B, C … Z;
σ An 、σ Bn 、σ Cn 、σ Zn stress values are calculated for the n order mode down point A, B, C … Z correspondence.
Further, the inner product correlation C of the identified mode shape max ＝max{C 1 ,C 2 ,...,C n }。
According to the method for identifying the dynamic vibration mode of the engine blade based on the inner product correlation calculation, the correlation degrees of the actually measured vibration stress and the near-order calculated vibration stress are quickly sequenced, an exact basis is provided for vibration mode identification, and the working efficiency is remarkably improved; moreover, the method has good applicability to high-order vibration modes, and influences brought by undersized actual measurement stress values are considered more reasonably in the vibration mode identification process.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
Fig. 1 is a schematic flow chart of a dynamic vibration measurement mode identification method according to the present application.
Fig. 2 is a schematic diagram of a position of a strain gauge attached to a blade in an embodiment of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
According to the method, a relative vibration stress database of each node of the blade under different vibration modes is established according to the dynamic stress measurement and analysis result of the blade of the engine, and an identification method of the dynamic vibration mode of the blade of the aero-engine based on the inner product correlation is established by introducing an inner product correlation calculation method.
As shown in fig. 1, the method for identifying the dynamic vibration mode of the blade of the aircraft engine provided by the application comprises the following steps:
1) according to the patch scheme, the strain gauge is arranged on the blade, the position of the patch is combined with the previous dynamic measurement result or the analytical result of the Campbell diagram to select the position with obvious vibration, the position is close to the maximum stress point where the resonance vibration mode is likely to occur, and the accuracy of vibration mode identification is improved. The first-order vibration mode is generally located at the position of a blade root, and the high-order vibration mode is generally located at the position of a blade tip.
For example, in this embodiment, A, B, C, D four measuring points are provided on a certain blade, and the positions of the four measuring points formed by four strain gauges adhered to the blade are shown in fig. 2, wherein two strain gauges a to B are arranged at the axial front and rear edges of the blade tip of the blade, a strain gauge D is arranged in the middle of the blade root of the blade, and a strain gauge C is arranged at the front edge part of the radial middle part of the blade. The four measuring points A, B, C, D are provided on the blade in the following.
Carrying out dynamic test and recording resonance speed N t Resonant frequency F t And the measured stress value sigma of each measuring point A 、σ B 、σ C 、σ D And representing the stress values as measured stress vectors
Figure BDA0003590027190000051
Resonant rotational speed N, obtained for example by a dynamic test t 7000r/min, corresponding resonance frequency F t 3000Hz, and the actually measured stress value sigma A 、σ B 、σ C 、σ D 40,60,80,120, the stress vector was determined
Figure BDA0003590027190000056
Namely (40,60,80, 120).
2) Dynamic frequency analysis under different rotating speed conditions is carried out and is used for correspondingly inquiring the dynamic resonance rotating speed; and outputting the frequency values of each order and the node stress of each patch position under each rotating speed condition. It should be noted that the direction of the nodal force should be consistent with the patch direction of the strain gauge; and establishing a dynamic frequency database of the blade and the corresponding patch scheme.
3) Picking and resonating from a frequency-dependent databaseRotational speed N t Closest dynamic frequency speed N f And further selecting a resonant frequency F therein t Frequencies within a certain range (typically 5%) are determined as suspected mode frequencies, which can be labeled as F f1 、F f2 、F f3 …F fn 。
For example, the resonance speed N is selected according to the analysis result t Closest dynamic frequency speed N f 7200r/min, the range of the corresponding suspected vibration mode frequency band is 2850-3150 Hz, except the head end frequency and the tail end frequency of the frequency band, five suspected vibration mode frequencies are obtained by taking every 100Hz as step length, namely the determined suspected vibration mode frequency is F f1 ＝2850、F f2 ＝2900、F f3 ＝3000、F f4 ＝3100，F f5 ＝3150Hz。
4) And respectively taking out the calculated stress values of A, B, C, D four measuring points in the suspected vibration modes, and sequentially and commonly representing the calculated stress values as the calculated stress vector of each suspected vibration mode:
Figure BDA0003590027190000052
Figure BDA0003590027190000053
for example, the calculated stress vector in this embodiment is:
Figure BDA0003590027190000054
Figure BDA0003590027190000055
Figure BDA0003590027190000061
5) according to the formula
Figure BDA0003590027190000062
Respectively calculating the actually measured stress vectors
Figure BDA0003590027190000063
And each calculated stress vector
Figure BDA0003590027190000064
Inner product correlation degree C between 1 、C 2 、C 3 、C 4 。
In this embodiment, the measured stress vector obtained by the above formula
Figure BDA0003590027190000065
And calculating the stress vector
Figure BDA0003590027190000066
The inner product correlation degree between the two is respectively C 1 ＝0.9959、C 2 ＝0.9335、C 3 ＝0.9998、C 4 ＝0.8908、C 5 ＝0.5734；
7) Comparing the inner product correlation C 1 ～C 4 By the formula C max ＝max{C 1 ,C 2 ,C 3 ,C 4 Determining the inner product correlation degree C of the most correlated calculated stress vector and the measured stress vector max Then, the most relevant inner product correlation C is selected from the dynamic frequency database max Corresponding suspected mode frequency F fn The frequency of the mode shape corresponding to the resonance mode shape.
In this example, by C max ＝max{C 1 ,C 2 ,C 3 ,C 4 Determining C 3 Selecting suspected vibration pattern frequency F from dynamic frequency database for the most relevant inner product correlation degree f3 3000Hz represents the mode frequency corresponding to the resonance mode.
On the basis of determining the vibration mode frequency, the maximum stress conversion work can be performed according to the data related to the dynamic frequency database related to the vibration mode frequency, and then whether the maximum vibration stress point under the resonance vibration mode meets the requirement of the high cycle fatigue life is judged, which is not repeated herein.
The method of the application has the following advantages:
a) the measured vibration stress and the calculated vibration stress are respectively expressed as a vector (n measuring points), and the Euclidean space R is in n dimensions n In (1),the included angle of the vector is adopted to describe the correlation between the test vibration mode and the calculated vibration mode, the workload is small, the thought is clear, and objective vibration mode judgment can be realized;
b) for different resonance frequencies, the correlation degrees of the actually measured vibration stress and the calculated vibration stress of the similar order can be quickly sequenced by utilizing the relative vibration stress database of each order established in the early stage and combining the inner product correlation degree calculation method, so that an exact basis is provided for vibration mode identification, and the working efficiency is remarkably improved;
c) for the high-order mode shape, even if the stress ratio values of the measuring points are different greatly, the inner product correlation degree model is still suitable, the calculated value takes the relatively large stress measured by the high-order measuring points as the leading factor, and the relatively small stress measured by the low-order measuring points has little influence on the calculated value, thereby being consistent with the actual mode shape judgment method.
According to the method for identifying the dynamic vibration mode of the engine blade based on the inner product correlation calculation, the correlation degrees of the actually measured vibration stress and the near-order calculated vibration stress are quickly sequenced, an exact basis is provided for vibration mode identification, and the working efficiency is remarkably improved; moreover, the method has good applicability to high-order vibration modes, and influences brought by undersized actual measurement stress values are reasonably considered in the vibration mode identification process.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims (7)

1. An aeroengine blade dynamic vibration measurement type identification method based on inner product correlation is characterized by comprising the following steps:
arranging a plurality of strain gauges on the blade to form stress measurement points and carrying out a blade dynamic stress measurement test to obtain the resonance rotating speed and the resonance frequency of the blade and the actually measured stress values of the measurement points, and representing the actually measured stress values of the measurement points as an actually measured stress vector in sequence;
carrying out dynamic frequency analysis under different rotating speed conditions to obtain frequency values of each order and node stress of each strain gauge position under each rotating speed condition, and establishing a dynamic frequency database of the blade and the corresponding strain gauge arrangement scheme;
selecting a dynamic frequency rotating speed which is closest to the resonance rotating speed from a dynamic frequency database, and further selecting a plurality of frequencies within a preset range with the resonance frequency from the dynamic frequency database to determine the frequencies as suspected resonance type frequencies;
respectively selecting the calculated stress values of a plurality of stress measuring points in the suspected vibration mode, and commonly representing the calculated stress values as the calculated stress vector of each suspected vibration mode in sequence;
calculating the inner product correlation degree between the actually measured stress vector and each calculated stress vector;
and comparing the relative magnitude of each inner product correlation degree, determining the inner product correlation degree which is most relevant to the calculated stress vector and the measured stress vector, and then selecting the suspected vibration mode frequency corresponding to the most relevant inner product correlation degree from the dynamic frequency database as the vibration mode frequency corresponding to the resonance vibration mode.
2. The method for identifying the dynamic vibration mode of the aero-engine blade based on the inner product correlation degree as claimed in claim 1, wherein the position where the strain gauge is arranged is selected to be a position where vibration is obvious according to a previous dynamic stress measurement result or a Campbell diagram analysis result so as to be close to a maximum stress point where a resonance vibration mode is likely to occur.
3. The method for identifying the dynamic vibration mode of the aero-engine blade based on the inner product correlation degree as claimed in claim 2, wherein the positions where the vibration is obvious comprise a blade root position suitable for a first-order vibration mode and a blade tip position suitable for a high-order vibration mode.
4. The method for identifying the dynamic vibration mode of the aero-engine blade based on the inner product correlation degree as claimed in claim 1, wherein the node stress direction of each strain gauge is consistent with the patch direction of each strain gauge.
5. The method according to claim 1, wherein the range difference from the resonant frequency is 5% when a plurality of frequencies are selected from the dynamic frequency database and determined as the suspected vibration mode frequency.
6. The method for identifying the dynamic vibration mode of the aero-engine blade based on the inner product correlation degree as claimed in claim 1, wherein the method for calculating the inner product correlation degree between the measured stress vector and each calculated stress vector comprises the following steps:
Figure FDA0003590027180000021
in the formula, C n Is the inner product correlation;
Figure FDA0003590027180000022
is an actually measured stress vector;
Figure FDA0003590027180000023
calculating a stress vector for the n-order mode shape;
σ An 、σ B 、σ C 、σ Z the measured stress value is the measured stress value of a measuring point A, B, C … Z;
σ An 、σ Bn 、σ Cn 、σ Zn stress values are calculated for the n order mode down point A, B, C … Z correspondence.
7. The method for identifying a vibration mode for a blade of an aircraft engine based on inner product correlation as claimed in claim 6, wherein the inner product correlation C of the identified vibration mode max ＝max{C 1 ,C 2 ,...,C n }。
CN202210375079.0A 2022-04-11 2022-04-11 Method for identifying dynamic vibration measurement mode of aero-engine blade based on inner product correlation Pending CN114812994A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116910427A (en) * 2023-09-14 2023-10-20 清华大学 Forced resonance calculation method taking wake sweep and wake pulsation into consideration

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116910427A (en) * 2023-09-14 2023-10-20 清华大学 Forced resonance calculation method taking wake sweep and wake pulsation into consideration
CN116910427B (en) * 2023-09-14 2023-12-12 清华大学 Forced resonance calculation method taking wake sweep and wake pulsation into consideration

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