CN120800814A - Blade non-full-order vibration analysis method and system for multi-physical-field dynamic signals - Google Patents
Blade non-full-order vibration analysis method and system for multi-physical-field dynamic signalsInfo
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- CN120800814A CN120800814A CN202511270336.4A CN202511270336A CN120800814A CN 120800814 A CN120800814 A CN 120800814A CN 202511270336 A CN202511270336 A CN 202511270336A CN 120800814 A CN120800814 A CN 120800814A
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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
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H1/00—Measuring characteristics of vibrations in solids by using direct conduction to the detector
- G01H1/003—Measuring characteristics of vibrations in solids by using direct conduction to the detector of rotating machines
- G01H1/006—Measuring characteristics of vibrations in solids by using direct conduction to the detector of rotating machines of the rotor of turbo machines
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- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to the field of gas turbine engine compressor tests, and discloses a method and a system for analyzing blade non-integral-order vibration of a multi-physical-field dynamic signal, wherein the method and the system are used for acquiring airflow excitation frequency and circumferential modal order generated by unstable pneumatic disturbance through dynamic pressure test and acquiring circumferential unstable flow modal characteristics for inducing the blade non-integral-order vibration; and obtaining the vibration frequency and pitch diameter of the blade through dynamic test of the blade vibration, and comprehensively processing the test parameters of the two physical fields to judge the non-full-order vibration of the blade. The method can effectively identify the occurrence of the non-integral-order vibration of the blade, can be used for testing the non-integral-order vibration of the air compressor blade of the aero-engine and analyzing the mechanism of the vibration failure fault of the relevant blade, and has important significance for improving the overall safety and reliability of the air compressor of the aero-engine.
Description
Technical Field
The invention relates to the field of gas turbine engine compressor tests, and discloses a method and a system for analyzing blade non-full-order vibration of multiple physical field dynamic signals.
Background
The high-performance aero-engine has higher and higher requirements on design indexes such as thrust-weight ratio, fuel consumption and the like, and the air compressor with higher efficiency and lighter weight materials becomes the main stream selection of the advanced aero-engine. The single-stage pneumatic load of the upper compressor component is continuously improved in pneumatic design, the structural design of the lightweight blisk and the blisk is adopted in the structure generally, the circumferential distance between compressor stages is further shortened, the weight of the compressor component can be effectively reduced by adopting the design measures, the flow loss is reduced, and the pneumatic efficiency of the compressor is improved.
In the aspect of structural design of the air compressor, a blisk structure is increasingly adopted. The blisk structure can effectively reduce the flow loss caused by air leakage between the tenon and the disc of the traditional disc separation structure. At the same time, the blade root area is subjected to lower stress levels due to the integrated monolithic structure of the disk and blade.
However, because the structural damping of the blisk is relatively small, the unsteady aerodynamic force borne by the blades is continuously enhanced under the condition that the pneumatic load component of the compressor is increased, the blades have small structural damping and bear larger alternating load, and the blades increasingly suffer from the problem of high cycle fatigue caused by non-integral order vibration.
Non-full order vibration of aircraft engine compressor blades is a typical fluid-solid coupling problem involving multiple physical fields of fluid, solids, heat transfer, etc. At present, the generation mechanism of the non-full-order vibration of the compressor blade is not completely clear, and no related test method exists.
Disclosure of Invention
The invention aims to provide a method and a system for analyzing blade non-integral-order vibration of a multi-physical-field dynamic signal, which can effectively identify the occurrence of the blade non-integral-order vibration.
In order to achieve the technical effects, the technical scheme adopted by the invention is as follows:
a blade non-full-order vibration analysis method of a multi-physical field dynamic signal comprises the following steps:
Acquiring vibration frequencies, pitch diameters, airflow excitation frequencies of airflow disturbance of the blade tips of the rotor blades and circumferential modal orders of the rotor blades under a plurality of vibration modes under the test working condition of the air compressor;
calculating the ratio of the sum or difference absolute value of the airflow excitation frequency and the vibration frequency to the compressor rotation frequency under each vibration mode, and rounding;
And if the ratio of at least one rounded corresponding vibration mode is equal to the circumferential modal order, and the absolute value of the sum or difference of the circumferential modal order and the pitch diameter is an integer multiple of the number of the rotor blades, judging that the rotor blades in the corresponding vibration mode vibrate in a non-integral order.
Further, the BTT sensor is adopted to obtain the pitch diameters of the rotor blade under different vibration modes under the test working condition of the compressor, wherein the axial position of the BTT sensor is located close to the front edge position of the blade tip of the rotor blade.
Further, the sampling frequency of the BTT sensor is higher than 100kHz, and the head of the BTT sensor is 0.5-2 mm away from the inner wall surface of the compressor casing.
Further, the vibration frequency of the blade under the corresponding vibration mode under the working condition of the compressor test is obtained by adopting a mode of attaching the strain gauge, and the sampling frequency of the strain gauge is larger than 25kHz.
Further, the compressor turns to the frequencyN/60, where n is the rotational speed of the compressor under test conditions.
In order to achieve the technical effects, the invention also provides a blade non-whole order vibration analysis system of the multi-physical field dynamic signal, which comprises:
the data acquisition module is used for acquiring the vibration frequency, the pitch diameter, the airflow excitation frequency of airflow disturbance of the tip of the rotor blade and the circumferential modal order of the rotor blade under a plurality of vibration modes under the test working condition of the compressor;
the data analysis module is used for calculating the ratio of the sum or difference absolute value of the airflow excitation frequency and the vibration frequency to the rotation frequency of the air compressor under each vibration mode and rounding;
And the non-integral order vibration judging module is used for judging that the rotor blade in the corresponding vibration mode generates non-integral order vibration when the ratio of at least one rounded corresponding vibration mode is equal to the circumferential mode order and the sum or difference absolute value of the circumferential mode order and the pitch diameter is an integral multiple of the number of the rotor blade.
Further, the data acquisition module acquires pitch diameters of the rotor blade under different vibration modes of the rotor blade under the test working condition of the compressor by adopting a BTT sensor, wherein the axial position of the BTT sensor is positioned close to the front edge of the blade tip of the rotor blade.
Further, in the data acquisition module, the sampling frequency of the BTT sensor is higher than 100kHz, and the head of the BTT sensor is 0.5-2 mm away from the inner wall surface of the compressor casing.
Further, in the data acquisition module, a mode of attaching a strain gauge is adopted to acquire the vibration frequency of the blade under the test working condition of the compressor under the corresponding vibration mode, and the sampling frequency of the strain gauge is larger than 25kHz.
Further, in the data analysis module, the compressor converts frequencyN/60, where n is the rotational speed of the compressor under test conditions.
Compared with the prior art, the method has the advantages that the method obtains the airflow excitation frequency and the circumferential modal order generated by unstable pneumatic disturbance through dynamic pressure test, obtains the circumferential unstable flow modal characteristic which causes the non-integral-order vibration of the blade, obtains the blade vibration frequency and the pitch diameter through dynamic test of the blade vibration, comprehensively processes the test parameters of two physical fields, realizes the judgment of the non-integral-order vibration of the blade, can effectively identify the occurrence of the non-integral-order vibration of the blade of the aeroengine compressor, can be used for the test of the non-integral-order vibration of the blade of the aeroengine compressor and the mechanism analysis of related blade vibration failure faults, and has important significance for improving the overall safety and reliability of the aeroengine compressor.
Drawings
FIG. 1 is a flow chart of a method for analyzing blade non-full-order vibration of multiple physical field dynamic signals in example 1 or 2;
FIG. 2 is a block diagram of a system for analyzing blade non-full-order vibration of multiple physical field dynamic signals in embodiment 1;
the device comprises a data acquisition module, a data analysis module and a non-whole order vibration judgment module.
Detailed Description
The present invention will be described in further detail with reference to the following examples and drawings. It should not be construed that the scope of the above subject matter of the present invention is limited to the following embodiments, and all techniques realized based on the present invention are within the scope of the present invention.
Example 1
Referring to fig. 1 and 2, a method for analyzing blade non-full-order vibration of a multi-physical field dynamic signal includes:
Acquiring vibration frequencies, pitch diameters, airflow excitation frequencies of airflow disturbance of the blade tips of the rotor blades and circumferential modal orders of the rotor blades under a plurality of vibration modes under the test working condition of the air compressor;
calculating the ratio of the sum or difference absolute value of the airflow excitation frequency and the vibration frequency to the compressor rotation frequency under each vibration mode, and rounding;
And if the ratio of at least one rounded corresponding vibration mode is equal to the circumferential modal order, and the absolute value of the sum or difference of the circumferential modal order and the pitch diameter is an integer multiple of the number of the rotor blades, judging that the rotor blades in the corresponding vibration mode vibrate in a non-integral order.
In the embodiment, the airflow excitation frequency and the circumferential modal order generated by unstable pneumatic disturbance are obtained through dynamic pressure test, the circumferential unstable flow modal characteristic for inducing the blade to vibrate in an irregular order is obtained, the blade vibration frequency and the pitch diameter are obtained through dynamic test of the blade vibration, the test parameters of two physical fields are comprehensively processed, the judgment of the blade to vibrate in the irregular order is realized, the occurrence of the blade to vibrate in the irregular order can be effectively identified, the method can be used for the test of the blade to vibrate in the irregular order of an aeroengine compressor and the mechanism analysis of failure faults of the related blade vibration, and the method has important significance for improving the overall safety and reliability of the aeroengine compressor.
Based on the same inventive concept, the present embodiment further provides a blade non-integer order vibration analysis system of a multi-physical field dynamic signal, including:
the data acquisition module 1 is used for acquiring the vibration frequency, pitch diameter, airflow excitation frequency of airflow disturbance of the tip of the rotor blade and circumferential modal orders of the rotor blade under a plurality of vibration modes under the test working condition of the compressor;
The data analysis module 2 is used for calculating the ratio of the sum or difference absolute value of the airflow excitation frequency and the vibration frequency to the rotation frequency of the air compressor under each vibration mode and rounding;
and the non-integral-order vibration judging module 3 is used for judging that the rotor blade in the corresponding vibration mode generates non-integral-order vibration when at least one rounded ratio is equal to the circumferential modal order and the sum or difference absolute value of the circumferential modal order and the pitch diameter is an integral multiple of the number of the rotor blades in the corresponding vibration mode.
Example 2
Referring to fig. 1, a method for analyzing blade non-full-order vibration of a multi-physical field dynamic signal includes:
Step one, acquiring vibration frequencies, pitch diameters, airflow excitation frequencies of airflow disturbance of the blade tips of the rotor blades and circumferential modal orders of the rotor blades under a plurality of vibration modes under the test working condition of the compressor;
In the embodiment, a BTT sensor is adopted to obtain the pitch diameters of the rotor blade under different vibration modes under the test working condition of the compressor, wherein the axial position of the BTT sensor is positioned close to the front edge of the tip of the rotor blade, and the sampling frequency of the BTT sensor is higher than 100kHz. When the BTT sensor is installed, the head of the optical fiber sensor needs to be ensured to retract 0.5-2 mm away from the inner wall surface of the casing, and the head of the optical fiber sensor and the tip of the rotor blade are prevented from being bumped and ground during the test.
In this embodiment, a mode of attaching a strain gauge is adopted to monitor modal vibration with dangerous resonance, the sampling frequency of the strain gauge is generally higher than 25kHz, and the vibration frequency of the blade under the corresponding vibration mode of the blade load under the test working condition of the compressor is obtained.
In this embodiment, the circumferential layout and number of dynamic pressure test arrays is determined based on the number of rotor blades. If the number of the dynamic pressure test arrays is enough, the dynamic pressure test arrays are circumferentially distributed uniformly, the number is more than 2 times of the number of the rotor blades, and if the number of the dynamic pressure test arrays is insufficient, the circumferential positions of the dynamic pressure test arrays can be arranged by adopting a compressed sensing sampling method. After the layout of the dynamic pressure test array is determined, the dynamic pressure test array is installed, and information such as airflow excitation frequency fstat and circumferential mode order AWN of airflow disturbance of the blade tip of the rotor blade is obtained, wherein the sampling frequency of the dynamic pressure test array is generally higher than 50kHz. The airflow excitation frequency is obtained through Fourier transform of dynamic pressure test array data, and the circumferential modal order is obtained through space Fourier transform.
Step two, calculating the ratio of the sum or difference absolute value of the airflow excitation frequency and the vibration frequency to the compressor rotating frequency under each vibration mode, and rounding;
in this embodiment, the characteristic value obtained by rounding the ratio of the absolute value of the sum or difference of the airflow excitation frequency and the vibration frequency to the compressor rotation frequency under the corresponding vibration mode WhereinFor the frequency of the excitation of the air flow,For the frequency of the vibration to be mentioned,For the purpose of the frequency conversion of the air compressor,N/60, where n is the rotational speed of the compressor under test conditions,To round the function symbols.
And step three, judging that the rotor blade in the corresponding vibration mode vibrates in a non-integral order if the ratio of at least one rounded corresponding vibration mode is equal to the circumferential modal order and the sum or difference absolute value of the circumferential modal order and the pitch diameter is an integral multiple of the number of the rotor blade.
If the circumferential mode order isAnd one of the vibration modesEqual in value andJudging that the rotor blade generates non-full-order vibration under the corresponding vibration mode, whereinIs an integer of the number of the times,For the number of rotor blades,Is the pitch diameter.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (10)
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Citations (7)
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| WO2008093349A1 (en) * | 2007-02-02 | 2008-08-07 | The Secretary, Department Of Atomic Energy, Govt. Of India | A method for non-intrusive on-line detection of turbine blade condition |
| CN114878167A (en) * | 2022-03-21 | 2022-08-09 | 北京动力机械研究所 | Tester for non-contact measurement of vibration of turbine blade of small turbine engine |
| CN115859536A (en) * | 2023-03-02 | 2023-03-28 | 中国航发四川燃气涡轮研究院 | Asynchronous vibration frequency locking numerical simulation method for rotor blade of gas compressor |
| CN117968829A (en) * | 2023-09-26 | 2024-05-03 | 中国航发沈阳发动机研究所 | A method for measuring vibration frequency of compressor blades of aircraft engines |
| CN117973149A (en) * | 2024-03-18 | 2024-05-03 | 中国航发沈阳发动机研究所 | Design method for cold blade tip clearance of blisk of compression part of aero-engine |
| EP4513151A1 (en) * | 2023-08-21 | 2025-02-26 | Danfoss A/S | Method of monitoring a rotating machine configured for energy transfer having a plurality of subsystems |
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-
2025
- 2025-09-08 CN CN202511270336.4A patent/CN120800814B/en active Active
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| WO2008093349A1 (en) * | 2007-02-02 | 2008-08-07 | The Secretary, Department Of Atomic Energy, Govt. Of India | A method for non-intrusive on-line detection of turbine blade condition |
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| CN115859536A (en) * | 2023-03-02 | 2023-03-28 | 中国航发四川燃气涡轮研究院 | Asynchronous vibration frequency locking numerical simulation method for rotor blade of gas compressor |
| EP4513151A1 (en) * | 2023-08-21 | 2025-02-26 | Danfoss A/S | Method of monitoring a rotating machine configured for energy transfer having a plurality of subsystems |
| CN117968829A (en) * | 2023-09-26 | 2024-05-03 | 中国航发沈阳发动机研究所 | A method for measuring vibration frequency of compressor blades of aircraft engines |
| CN117973149A (en) * | 2024-03-18 | 2024-05-03 | 中国航发沈阳发动机研究所 | Design method for cold blade tip clearance of blisk of compression part of aero-engine |
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