A method for formulating vibration load spectrum of aircraft engine accessories
The method formulates a vibration load spectrum for aircraft engine accessories by analyzing component data to create a reliable simulation of engine conditions, improving test accuracy and efficiency.
Patent Information
- Application Number
- CN202210688322.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2022-06-16
- Publication Date
- 2024-12-20
- Estimated Expiration
- 2042-06-16
AI Technical Summary
Current vibration tests on aircraft engine accessories use general load spectra that do not accurately reflect the diverse vibration environments, leading to unreliable test results.
A method to formulate a vibration load spectrum by measuring and analyzing vibration data of aircraft engine components, calculating tolerance limits, and identifying key vibration sources to create a vibration environment profile and frequency range, which is then used to design specific vibration tests for each region of the engine.
This approach enhances the reliability of vibration tests by accurately simulating actual engine conditions, reducing the need for separate spectra for each accessory and optimizing resource use.
Smart Images
Figure CN115096600B_ABST
Abstract
Description
Technical Field
[0001] The present application belongs to the technical field of formulating vibration load spectra of aircraft engine accessories, and specifically relates to a method for formulating vibration load spectra of aircraft engine accessories. Background Art
[0002] Aircraft engine accessories are subjected to severe vibration loads when the aircraft engine is working. Vibration tests on aircraft engine accessories can be conducted to evaluate their anti-vibration performance, which can provide a basis for the design and improvement of aircraft engine accessories.
[0003] Currently, vibration tests on aircraft engine accessories mostly use general load spectra. The differences in the vibration environments of various aircraft engine accessories are quite different from the actual conditions, and the reliability of the test results is poor.
[0004] This application is proposed in view of the above-mentioned technical defects.
[0005] It should be noted that the disclosure of the above background technology content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above content has been disclosed on the filing date of this application, the above background technology should not be used to evaluate the novelty and creativity of the present application. Summary of the invention
[0006] The purpose of the present application is to provide a method for formulating a vibration load spectrum of an aircraft engine accessory to overcome or alleviate at least one of the known technical deficiencies.
[0007] The technical solution of this application is:
[0008] A method for formulating a vibration load spectrum of an aero-engine accessory, comprising:
[0009] Measuring vibration data of each component of the aircraft engine at the location of the component, and obtaining vibration spectrum data of each component of the aircraft engine at the location of the component;
[0010] Calculate the vibration spectrum data of each component of the aircraft engine and the upper tolerance limit under different aircraft engine operating conditions;
[0011] The upper limit of the tolerance of the vibration spectrum data of each component of the aircraft engine under different aircraft engine working conditions is enveloped by region to obtain the vibration environment profile of each region of the aircraft engine;
[0012] Analyze the vibration characteristics of various areas of aircraft engines;
[0013] Calculate the frequency range of vibration characteristics of each area of the aircraft engine;
[0014] Based on the vibration environment profile, vibration characteristics and vibration characteristic frequency range of each area of the aircraft engine, the vibration load spectrum of each area of the aircraft engine is obtained.
[0015] According to at least one embodiment of the present application, in the above-mentioned method for formulating the vibration load spectrum of aircraft engine accessories, the vibration data of the positions of the aircraft engine accessories are measured to obtain the vibration spectrum data of the positions of the aircraft engine accessories, specifically:
[0016] The vibration data of each aircraft engine component at the location is measured, and the vibration data of each aircraft engine component at the location is converted into frequency domain data by fast Fourier transform to obtain the vibration spectrum data of each aircraft engine component at the location.
[0017] According to at least one embodiment of the present application, in the above-mentioned method for formulating the vibration load spectrum of aircraft engine accessories, the upper limit of the tolerance of the vibration spectrum data at the location of each aircraft engine accessory under different aircraft engine working conditions is enveloped by region to obtain the vibration environment profile of each region of the aircraft engine, specifically:
[0018] The upper tolerance limits of the vibration spectrum data of each component of the aero-engine under different aero-engine operating conditions are analyzed by envelope processing in each casing area to obtain the vibration environment profile of each casing area of the aero-engine.
[0019] According to at least one embodiment of the present application, in the above-mentioned method for formulating the vibration load spectrum of aircraft engine accessories, the vibration characteristic frequency range of each area of the aircraft engine is calculated as follows:
[0020] Identify key vibration sources in various areas of aircraft engines;
[0021] Based on the design speed of the aircraft engine and combined with the key vibration source properties of each area of the aircraft engine, the vibration characteristic frequency range of each area of the aircraft engine is calculated.
[0022] According to at least one embodiment of the present application, in the above-mentioned method for formulating the vibration load spectrum of aircraft engine accessories, the identification of key vibration sources in various areas of the aircraft engine is specifically:
[0023] The key vibration source is the vibration source in each area of the aircraft engine that matches its vibration characteristic frequency.
[0024] According to at least one embodiment of the present application, in the above-mentioned method for formulating the vibration load spectrum of an aircraft engine component, the typical vibration positions of various regions of the aircraft engine are identified;
[0025] Measure vibration data of typical vibration locations in various areas of aircraft engines;
[0026] Statistically analyze the dispersion of vibration data at typical vibration locations in each region of the aircraft engine, and calculate the vibration load spectrum correction coefficients for each region of the aircraft engine;
[0027] The vibration load spectrum of each area of the aircraft engine is corrected by using the vibration load spectrum correction coefficient of each area of the aircraft engine.
[0028] According to at least one embodiment of the present application, in the above-mentioned method for formulating the vibration load spectrum of aircraft engine accessories, the identifying of typical vibration positions of various regions of the aircraft engine is specifically:
[0029] The location of the component with the highest vibration level in each area of the aircraft engine is its typical vibration position. BRIEF DESCRIPTION OF THE DRAWINGS
[0030] Figure 1 It is a schematic diagram of a method for formulating a vibration load spectrum of an aircraft engine accessory provided in an embodiment of the present application.
[0031] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and cannot be understood as limitations on this patent. DETAILED DESCRIPTION
[0032] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.
[0033] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall be the common meanings understood by the general technicians in the field to which this application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inside", "outside" and other words indicating orientation used in the description of this application are only used to indicate the relative direction or positional relationship, and do not imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, so it cannot be understood as a limitation on this application. The "first", "second", "third" and similar terms used in the description of this application are only used for descriptive purposes to distinguish different components, and cannot be understood as indicating or implying relative importance. The similar words "one", "one" or "the" used in the description of this application should not be understood as an absolute limitation on quantity, but should be understood as the existence of at least one. The similar words "including" or "comprising" used in the description of this application mean that the elements or objects appearing in front of the word include the elements or objects listed after the word and their equivalents, without excluding other elements or objects.
[0034] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installed", "connected", "connected" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or the internal connection of two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.
[0035] The following is combined with Figure 1 This application is described in further detail.
[0036] A method for formulating a vibration load spectrum of an aero-engine accessory, comprising:
[0037] Measuring vibration data of each component of the aircraft engine at a location where the components and accessories are located may be a method of designing a special test run of the aircraft engine, measuring vibration data of each component and accessory of the aircraft engine at a location where the components and accessories are located, and obtaining vibration spectrum data of each component and accessory of the aircraft engine at a location where the components and accessories are located;
[0038] Calculate the vibration spectrum data of each component of the aircraft engine and the upper tolerance limit under different aircraft engine operating conditions;
[0039] The upper limit of the tolerance of the vibration spectrum data of each component of the aircraft engine under different aircraft engine working conditions is enveloped by region to obtain the vibration environment profile of each region of the aircraft engine;
[0040] Analyze the vibration characteristics of various areas of aircraft engines;
[0041] Calculate the frequency range of vibration characteristics of each area of the aircraft engine;
[0042] Based on the vibration environment profile, vibration characteristics and vibration characteristic frequency range of each area of the aircraft engine, the vibration load spectrum of each area of the aircraft engine is obtained.
[0043] As for the method for formulating the vibration load spectrum of aircraft engine accessories disclosed in the above-mentioned embodiment, it can be understood by those skilled in the art that its design is based on the measured vibration data of the locations of the various aircraft engine accessories, and the vibration spectrum data of the locations of the various aircraft engine accessories and their upper tolerance limits under different aircraft engine operating conditions are obtained. Then, the upper tolerance limits of the vibration spectrum data of the locations of the various aircraft engine accessories under different aircraft engine operating conditions are enveloped by region to obtain the vibration environment profile of each region of the aircraft engine. The vibration environment profile, vibration characteristics and vibration characteristic frequency range of each region of the aircraft engine are combined to obtain the vibration load spectrum of each region of the aircraft engine. Vibration tests can be performed on the accessories in each region of the aircraft engine respectively based on the above-mentioned method. The test results have high reliability. Moreover, the vibration data of the locations of the various aircraft engine accessories are classified by region to obtain the vibration load spectrum of each region of the aircraft engine, without having to formulate a separate vibration load spectrum for each accessory on the aircraft engine, which can greatly improve work efficiency.
[0044] In some optional embodiments, in the above-mentioned method for formulating the vibration load spectrum of aircraft engine accessories, the vibration data of the positions of the aircraft engine accessories are measured to obtain the vibration spectrum data of the positions of the aircraft engine accessories, specifically:
[0045] The vibration data of each aircraft engine component at the location is measured, and the vibration data of each aircraft engine component at the location is converted into frequency domain data by fast Fourier transform to obtain the vibration spectrum data of each aircraft engine component at the location.
[0046] In some optional embodiments, in the above-mentioned method for formulating the vibration load spectrum of aircraft engine accessories, the upper limit of the tolerance of the vibration spectrum data at the location of each aircraft engine accessory under different aircraft engine working conditions is enveloped by region to obtain the vibration environment profile of each region of the aircraft engine, specifically:
[0047] The upper limits of the tolerance of the vibration spectrum data of the locations of various accessories of the aircraft engine under different aircraft engine working conditions are enveloped by casing area to obtain the vibration environment profile of each casing area of the aircraft engine. That is, the vibration data of the locations of various accessories of the aircraft engine are classified by casing area. Each casing of the aircraft engine has a very similar vibration environment. The vibration data of the locations of various accessories of the aircraft engine are classified by casing area to obtain the vibration load spectrum of each casing area of the aircraft engine. Based on this, vibration tests are performed on the accessories in each casing area of the aircraft engine respectively, which can ensure the reliability of the test results and is simple and easy to implement.
[0048] In some optional embodiments, in the above-mentioned method for formulating the vibration load spectrum of aircraft engine accessories, the vibration characteristic frequency range of each area of the aircraft engine is calculated as follows:
[0049] Identify key vibration sources in various areas of aircraft engines;
[0050] Based on the design speed of the aircraft engine and combined with the key vibration source properties of each area of the aircraft engine, the vibration characteristic frequency range of each area of the aircraft engine is calculated.
[0051] In some optional embodiments, in the above-mentioned method for formulating the vibration load spectrum of aircraft engine accessories, the identification of key vibration sources in various areas of the aircraft engine is specifically:
[0052] The key vibration source is the vibration source in each area of the aircraft engine that matches its vibration characteristic frequency.
[0053] In some optional embodiments, in the above-mentioned method for formulating the vibration load spectrum of the aircraft engine accessories, the typical vibration positions of various regions of the aircraft engine are identified;
[0054] Measuring vibration data of typical vibration positions in various areas of an aircraft engine can be used to collect vibration data of typical vibration positions in various areas of an aircraft engine during routine test runs of the aircraft engine;
[0055] Statistically analyze the dispersion of vibration data at typical vibration locations in each region of the aircraft engine, and calculate the vibration load spectrum correction coefficients for each region of the aircraft engine;
[0056] The vibration load spectrum of each area of the aircraft engine is corrected by using the vibration load spectrum correction coefficient of each area of the aircraft engine.
[0057] When the vibration data of each component of an aero-engine is measured at a location of a single aero-engine special test run, the number of samples is limited, and it is difficult to cover the situations of different aircraft units and their life stages. If the vibration data of each component of an aero-engine is measured at a location of aero-engine special test runs for multiple times, the number of samples will be expanded, but the number of vibration measurement points will be large, the cycle will be long, the cost will be high, and there will be a large waste of manpower and material resources. The method for formulating the vibration load spectrum of components of an aero-engine disclosed in the above embodiment can be understood by technicians in the field that its design is based on identifying the typical vibration positions of various regions of an aero-engine, and through conventional aero-engine tests, vibration data of typical vibration positions of various regions of an aero-engine are collected, and then the dispersion of vibration data of typical vibration positions of various regions of an aero-engine is counted, and the vibration load spectrum correction coefficient of each region of an aero-engine is calculated, and the vibration load spectrum of each region of an aero-engine is corrected, so that the samples can effectively cover the situations of different aircraft units and their life stages, and the number of vibration measurement points is small, the cost is low, and manpower and material resources are saved.
[0058] In some optional embodiments, in the above-mentioned method for formulating the vibration load spectrum of aircraft engine accessories, the identifying of typical vibration positions of various regions of the aircraft engine is specifically:
[0059] The location of the component with the highest vibration level in each area of the aircraft engine is its typical vibration position.
[0060] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other.
[0061] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.
Claims
1. A method for formulating a vibration load spectrum of an aircraft engine accessory, characterized in that: include: Measuring vibration data of each component of the aircraft engine at the location of the component, and obtaining vibration spectrum data of each component of the aircraft engine at the location of the component; Calculate the vibration spectrum data of each component of the aircraft engine and the upper tolerance limit under different aircraft engine operating conditions; The upper limit of the tolerance of the vibration spectrum data of each component of the aircraft engine under different aircraft engine working conditions is enveloped by region to obtain the vibration environment profile of each region of the aircraft engine; Analyze the vibration characteristics of various areas of aircraft engines; Calculate the frequency range of vibration characteristics of each area of the aircraft engine; Based on the vibration environment profile, vibration characteristics and vibration characteristic frequency range of each area of the aircraft engine, the vibration load spectrum of each area of the aircraft engine is obtained; The vibration data of each component of the aircraft engine at the location of the component is measured to obtain the vibration spectrum data of each component of the aircraft engine at the location of the component, specifically: Measuring vibration data of each component of the aircraft engine at a location where the component is located, converting the vibration data of each component of the aircraft engine at a location where the component is located into frequency domain data by fast Fourier transform, and obtaining vibration spectrum data of each component of the aircraft engine at a location where the component is located; The tolerance upper limit of the vibration spectrum data at the position of each component of the aircraft engine under different aircraft engine working conditions is enveloped by region to obtain the vibration environment profile of each region of the aircraft engine, specifically: The upper limit of the tolerance of the vibration spectrum data of each component of the aircraft engine under different aircraft engine working conditions is processed by envelope processing in the casing area to obtain the vibration environment profile of each casing area of the aircraft engine; The vibration characteristic frequency range of each area of the aircraft engine is calculated as follows: Identify key vibration sources in various areas of aircraft engines; Based on the design speed of the aircraft engine and combined with the key vibration source properties of each area of the aircraft engine, the vibration characteristic frequency range of each area of the aircraft engine is calculated.
2. The method for formulating the vibration load spectrum of an aircraft engine accessory according to claim 1, characterized in that: The identification of key vibration sources in various areas of the aircraft engine is specifically: The key vibration source is the vibration source in each area of the aircraft engine that matches its vibration characteristic frequency.
3. The method for formulating the vibration load spectrum of an aircraft engine accessory according to claim 2, characterized in that: Identify typical vibration locations in various areas of an aircraft engine; Measure vibration data of typical vibration locations in various areas of aircraft engines; Statistically analyze the dispersion of vibration data at typical vibration locations in each region of the aircraft engine, and calculate the vibration load spectrum correction coefficients for each region of the aircraft engine; The vibration load spectrum of each area of the aircraft engine is corrected by using the vibration load spectrum correction coefficient of each area of the aircraft engine.
4. The method for formulating the vibration load spectrum of an aircraft engine accessory according to claim 3, characterized in that: The identification of typical vibration positions of various areas of the aircraft engine is specifically as follows: The location of the component with the highest vibration level in each area of the aircraft engine is its typical vibration position.