CN115292924B - Design method of high-cycle fatigue test run load spectrum of whole aeroengine - Google Patents

Design method of high-cycle fatigue test run load spectrum of whole aeroengine Download PDF

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CN115292924B
CN115292924B CN202210902435.XA CN202210902435A CN115292924B CN 115292924 B CN115292924 B CN 115292924B CN 202210902435 A CN202210902435 A CN 202210902435A CN 115292924 B CN115292924 B CN 115292924B
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cycle fatigue
rotating speed
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沈锡钢
白天明
宋学舟
曹航
张勇
刘洋
尚尔魁
曲文宇
许丽叶
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AECC Shenyang Engine Research Institute
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Abstract

The application discloses a load spectrum design method for complete machine high cycle fatigue test of an aeroengine, which comprises the following steps: determining an examination object of the complete machine high cycle fatigue test of the aeroengine, wherein the test load of the examination object is determined according to the influence of the known resonance rotating speed, the unknown resonance rotating speed and the acceleration and deceleration times on vibration; carrying out resonance rotation speed analysis according to the known vibration data of the parts, and correcting by combining the dispersion of the vibration characteristics to obtain a known resonance rotation speed analysis result; according to the working speed interval range of the aeroengine and ground test conditions, determining the upper limit and the lower limit of the high cycle fatigue test checking speed, determining the speed subinterval span, and finally determining the checking speed and the interval range thereof; on the basis of the checking rotation speed, carrying out data integration on the known resonance rotation speed, the unknown resonance rotation speed and the critical rotation speed of the whole machine, and determining the checking time of each rotation speed subinterval; and the design of the high-cycle fatigue test run load spectrum is completed by combining the acceleration and deceleration times requirement.

Description

Design method of high-cycle fatigue test run load spectrum of whole aeroengine
Technical Field
The application belongs to the technical field of aeroengines, and particularly relates to a design method of a complete machine high-cycle fatigue test run load spectrum of an aeroengine.
Background
The life design of the aero-engine needs to consider various influencing factors, wherein the design of high cycle fatigue resistance is one of key technologies for ensuring the safe and reliable use of the aero-engine.
Almost all aircraft engines currently develop universal specifications for high cycle fatigue (10 7 And above) all put forward clear requirements, according to the different materials, the engine parts are required to have enough high cycle fatigue life to verify the structural reliability of the relevant parts (rotor, stator blades, external pipelines, etc.) under the actual use conditions.
In the prior art, development work is generally carried out by adopting an infinite life design combined with a high cycle fatigue test at the material level or the component level. For example, first, at the part level, the parts are designed to have a sufficient margin without harmful vibration or vibration in the engine operating range based mainly on theoretical basis such as campbell diagram, goldman diagram, etc. This approach can solve most of the problems of high cycle fatigue design, but cannot fully simulate the complex working environment of the engine, with the risk of inadequate design verification. Secondly, in the whole machine level, although the step test run spectrum is adopted for high cycle fatigue verification in the past in the durable test run, the step test run spectrum adopts a mode of large rotating speed interval and equal duration, so that the full and complete examination cannot be achieved, and the expected examination effect cannot be achieved in the specified time; in addition, the design of the equal time length can also have the problem of being checked in certain rotating speed sections, so that the waste of time and resources is caused.
Disclosure of Invention
The purpose of the application is to provide a design method of a complete machine high cycle fatigue test run load spectrum of an aeroengine, so as to solve or alleviate at least one problem in the background technology.
The technical scheme of the application is as follows: a design method of a high-cycle fatigue test run load spectrum of an aircraft engine comprises the following steps:
according to the working principle of the aero-engine and the structural characteristics of each part, determining an examination object of the complete machine high cycle fatigue test of the aero-engine, wherein the test load of the examination object is determined according to the influence of the known resonance rotating speed, the unknown resonance rotating speed and the acceleration and deceleration times on vibration;
determining an examination rotational speed of an engine in a working rotational speed range and a corresponding examination time thereof comprises:
carrying out resonance rotation speed analysis according to the known vibration data of the parts, and correcting by combining the dispersion of the vibration characteristics to obtain a known resonance rotation speed analysis result;
determining the upper limit and the lower limit of the checking rotating speed of the high cycle fatigue test according to the working rotating speed interval range of the aero-engine and the ground test conditions, determining the span of a rotating speed subinterval according to the control precision of the actual rotating speed of the aero-engine test, and determining the checking rotating speed and the interval range thereof by combining the upper limit and the lower limit of the checking rotating speed;
on the basis of the checking rotation speed, carrying out data integration on the known resonance rotation speed, the unknown resonance rotation speed and the critical rotation speed of the whole machine, and determining the checking time of each rotation speed subinterval;
on the basis of completing the test load requirement, the high cycle fatigue test load spectrum design is completed by combining the acceleration and deceleration times requirement.
Further, the examination object comprises a rotor blade, a stator blade, an external pipeline and a casing thin-wall piece.
Further, the known resonance rotating speed comprises a part resonance rotating speed and a complete machine vibration critical rotating speed.
Further, the known resonance rotating speed of the part is determined according to the vibration characteristic analysis and dynamic stress test results of the part.
Further, the vibration critical rotation speed of the whole engine is determined according to the actual power characteristic condition of the tested engine.
Furthermore, the checking time of each rotating speed subinterval is the maximum value of the stay time in the resonance rotating speed, the unknown resonance rotating speed and the critical rotating speed of the whole machine.
According to the method, the complete machine environment is adopted for checking, load requirements are respectively formulated according to different parts and different vibration characteristics, the effectiveness, the integrity and the sufficiency of high-cycle fatigue checking are guaranteed, a scientific, systematic and effective method and operation flow are established for the design of the complete machine high-cycle fatigue test load spectrum, the working efficiency is improved, and the flight safety is guaranteed.
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In order to more clearly illustrate the technical solutions provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are only some embodiments of the present application.
FIG. 1 is a flow chart of a method for setting the whole high cycle fatigue test loading spectrum.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
In order to overcome the problems in the prior art, the method for designing the load spectrum of the high cycle fatigue test of the aircraft engine is established by combing the attention points of the high cycle fatigue design of the aircraft engine, defining the test load determining principle and method, and establishing the load spectrum programming flow of the high cycle fatigue test of the aircraft engine, so that the method for designing the load spectrum of the high cycle fatigue test of the aircraft engine is formed, and the purpose of completely and fully checking the high cycle fatigue resistance of parts of the aircraft engine is achieved by the high cycle fatigue test of the aircraft engine.
As shown in fig. 1, the method for designing the load spectrum of the complete machine high cycle fatigue test of the aero-engine comprises the following steps:
1. high cycle fatigue load determination principle
The main damage mode of the parts of the aeroengine is comprehensively considered in the high cycle fatigue load determination, and the assessment object of the complete machine high cycle fatigue test of the aeroengine is determined according to the working principle of the aeroengine and the structural characteristics of each part, including but not limited to rotor blades, stator blades, external pipelines, a case thin-wall part and the like.
For the parts, the test run load determination mainly considers three factors of known resonance rotating speed, unknown resonance rotating speed and acceleration and deceleration.
a) Determining a known resonant rotational speed
The known resonance rotating speed also comprises two parts, namely the resonance rotating speed of the parts and the vibration critical rotating speed of the whole machine.
The known resonance rotating speed of the parts is mainly determined according to vibration characteristic analysis, dynamic stress test results and the like of the parts.
For each stage of rotor blades, as the frequency dispersion degree exists in the actual installed blades, in order to achieve the purpose of full verification, the test run speed is corrected according to the actual measurement result of the frequency of each stage of blades, and each dispersion band with high frequency concentration degree is used as the resonance speed for verification of the blades with high dispersion degree.
For example, for titanium alloy parts, since it exceeds 10 7 The fatigue life after the secondary cycle still continues to be reduced, and the life requirement is 10 9 And (5) circulating for a second time. However, according to JSSG-2007 requirement, "for titanium, material performance test should be used instead of engine test", so that the residence time of resonance rotation speed of high cycle fatigue test is still 10 7 Or 10 8 The secondary loop is determined primarily.
The vibration critical rotation speed of the whole machine is mainly determined according to the actual dynamic characteristic condition of the tested engine by referring to the rotor dynamics analysis result. Since the critical rotation speed is the normal rotation speed of the engine, the residence time is 1×10 6 And (5) determining secondary circulation.
b) Determining unknown resonant rotational speed
Besides the known resonance speeds of the components and the whole machine, the high-cycle fatigue test run load spectrum also needs to consider the influences of other components and unknown resonance speeds. The retention time refers to the relevant data of JSSG-2007 and overseas high-cycle fatigue test run according to 1 multiplied by 10 6 And determining the secondary circulation, wherein the excitation factor is 3 times of the rotation speed.
c) Determining the times of acceleration and deceleration test run
The vibration of main parts can be influenced by the change of air flow in the acceleration and deceleration process of the engine, so that the influence of the acceleration and deceleration of the engine on the vibration is added in the establishment of the HCF (High Cycle Fatigue, namely high cycle fatigue) test load spectrum.
2. Determining a high cycle fatigue test run load spectrum
The aim of the high cycle fatigue test load spectrum of the whole machine is to determine the checking rotating speed and the corresponding checking time in the working rotating speed range of the engine, and the specific process of determining the load spectrum comprises the following steps:
(1) Resonance rotational speed analysis: and (3) carrying out resonance rotation speed analysis by considering known data such as vibration characteristics of parts, test measurement results and the like, and obtaining a known resonance rotation speed analysis result after correcting by optionally considering the dispersion of the vibration characteristics.
Table 1 is a statistical table of known resonant rotational speed analysis results according to an embodiment of the present application.
TABLE 1 known resonant rotational speed analysis results
Figure BDA0003771346020000051
(2) Determining an assessment rotating speed: comprehensively considering the working speed interval range of the aero-engine and the ground test conditions, and determining the upper limit and the lower limit of the high cycle fatigue test examination speed; and (3) considering the control precision of the actual rotation speed of the engine test run, determining the span of the rotation speed subinterval, and determining the checking rotation speed and the interval range thereof by combining the upper limit rotation speed and the lower limit rotation speed.
(3) Determining the checking time: on the basis of the checking rotation speed, data integration analysis is carried out on the requirements of the known resonance rotation speed, the unknown resonance rotation speed, the critical rotation speed of the whole machine and the like, and the checking time of each rotation speed subinterval is determined by adopting a maximization principle.
As shown in table 2, which is an examination schedule of each rotation speed subinterval in an embodiment of the present application, it can be seen from the table that, for the working condition of 45% of the low-pressure relative rotation speed, the residence time is the longest, namely "analysis of vibration characteristics of rotor blade (-1%), so that the examination time of the rotation speed subinterval is selected to be 405min corresponding to the examination time; similarly, for the working condition of 46% of the low-pressure relative rotation speed, the residence time is the longest unknown resonance rotation speed, so that the corresponding 83min is selected for the checking time of the rotation speed subinterval. Other cases will not be described in detail.
Table 2 rotational speed assessment schedule
Figure BDA0003771346020000061
(4) And (3) test run load spectrum design: on the basis of the load requirements, the acceleration and deceleration times requirements are fully considered, and the design of the high-cycle fatigue test run load spectrum is completed.
According to the principle of determining the high cycle fatigue test load of the parts of the aero-engine, a high cycle fatigue test load spectrum is established, and according to the analysis results of related theoretical calculation and test data, the high cycle fatigue resistance of main parts of the aero-engine can be checked when the ground bench tests.
According to the method, the complete machine environment is adopted for checking, load requirements are respectively formulated according to different parts and different vibration characteristics, the effectiveness, the integrity and the sufficiency of high-cycle fatigue checking are guaranteed, a scientific, systematic and effective method and operation flow are established for the design of the complete machine high-cycle fatigue test load spectrum, the working efficiency is improved, and the flight safety is guaranteed.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in 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 (6)

1. The design method of the whole high-cycle fatigue test run load spectrum of the aero-engine is characterized by comprising the following steps of:
according to the working principle of the aero-engine and the structural characteristics of each part, determining an examination object of the complete machine high cycle fatigue test of the aero-engine, wherein the test load of the examination object is determined according to the influence of the known resonance rotating speed, the unknown resonance rotating speed and the acceleration and deceleration times on vibration;
determining an examination rotational speed of an engine in a working rotational speed range and a corresponding examination time thereof comprises:
carrying out resonance rotation speed analysis according to the known vibration data of the parts, and correcting by combining the dispersion of the vibration characteristics to obtain a known resonance rotation speed analysis result;
determining the upper limit and the lower limit of the checking rotating speed of the high cycle fatigue test according to the working rotating speed interval range of the aero-engine and the ground test conditions, determining the span of a rotating speed subinterval according to the control precision of the actual rotating speed of the aero-engine test, and determining the checking rotating speed and the interval range thereof by combining the upper limit and the lower limit of the checking rotating speed;
on the basis of the checking rotation speed, data integration is carried out on the known resonance rotation speed, the unknown resonance rotation speed and the critical rotation speed of the whole machine, and the checking time of each rotation speed subinterval is determined by adopting a maximization principle;
on the basis of completing the test load requirement, the high cycle fatigue test load spectrum design is completed by combining the acceleration and deceleration times requirement.
2. The method for designing the complete machine high-cycle fatigue test load spectrum of the aeroengine according to claim 1, wherein the assessment object comprises a rotor blade, a stator blade, an external pipeline and a case thin-wall piece.
3. The method for designing the complete machine high cycle fatigue test run load spectrum of the aeroengine according to claim 1, wherein the known resonance rotation speed comprises a resonance rotation speed of a part and a complete machine vibration critical rotation speed.
4. The method for designing the complete machine high cycle fatigue test load spectrum of the aeroengine according to claim 3, wherein the known resonance rotating speed of the parts is determined according to the vibration characteristic analysis and dynamic stress test results of the parts.
5. The method for designing the complete machine high cycle fatigue test run load spectrum of the aeroengine according to claim 3, wherein the complete machine vibration critical rotation speed is determined according to the actual power characteristic condition of the tested engine.
6. The method for designing the complete machine high cycle fatigue test load spectrum of the aeroengine according to claim 1, wherein the checking time of each rotating speed subinterval is the maximum value of the stay time in the resonance rotating speed, the unknown resonance rotating speed and the complete machine critical rotating speed.
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