CN115292924A - Method for designing complete-machine high-cycle fatigue test load spectrum of aero-engine - Google Patents

Method for designing complete-machine high-cycle fatigue test load spectrum of aero-engine Download PDF

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CN115292924A
CN115292924A CN202210902435.XA CN202210902435A CN115292924A CN 115292924 A CN115292924 A CN 115292924A CN 202210902435 A CN202210902435 A CN 202210902435A CN 115292924 A CN115292924 A CN 115292924A
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rotating speed
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cycle fatigue
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CN115292924B (en
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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 provides a method for designing a complete machine high-cycle fatigue test load spectrum of an aircraft engine, which comprises the following steps: determining an examination object of the complete machine high-cycle fatigue test of the aero-engine, wherein the test run 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 rotating speed analysis according to the known vibration data of the parts, and correcting by combining the vibration characteristic dispersity to obtain a known resonance rotating speed analysis result; determining the upper limit and the lower limit of the high-cycle fatigue test examination rotating speed according to the working rotating speed interval range of the aero-engine and the ground test condition, determining the span of a rotating speed subinterval, and finally determining the examination rotating speed and the interval range thereof; on the basis of checking the rotating speed, performing data integration on the known resonance rotating speed, the unknown resonance rotating speed and the critical rotating speed of the whole machine, and determining the checking time of each rotating speed subinterval; and (4) combining the requirement of acceleration and deceleration times to complete the design of the high-cycle fatigue test run load spectrum.

Description

Method for designing complete-machine high-cycle fatigue test load spectrum of aero-engine
Technical Field
The application belongs to the technical field of aero-engines, and particularly relates to a design method of a complete machine high-cycle fatigue test run load spectrum of an aero-engine.
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 safe and reliable use of the aero-engine.
Almost all aircraft engines at present develop a common specification for high cycle fatigue (10) 7 And above) have set forth definite requirements, according to the different requirements of material, engine parts have sufficient high cycle fatigue life to verify the structural reliability of relevant parts (rotor, stator blade, external pipeline, etc.) under the actual service conditions.
In the prior art, development work is generally carried out by combining infinite life design with high cycle fatigue tests of material grade or part grade. For example, at the component level, the components are designed not to generate harmful vibration or have enough margin in the engine working range mainly based on theoretical bases such as campbell diagram and goodman diagram. Most problems of high-cycle fatigue design can be solved in the mode, but the complex working environment of the engine cannot be completely simulated, and the risk of insufficient design verification exists. Secondly, in the whole machine level, although the step test run spectrum is adopted for high-cycle fatigue verification in the prior art, the step test run spectrum adopts a mode of large rotating speed interval and equal time duration, so that the full and complete examination cannot be achieved, and the expected examination effect cannot be achieved within the specified time; in addition, the design with equal time length may have an over-examination problem in some rotation speed sections, which causes waste of time and resources.
Disclosure of Invention
The application aims to provide a design method of a complete-machine high-cycle fatigue test run load spectrum of an aircraft engine, so as to solve or reduce at least one problem in the background art.
The technical scheme of the application is as follows: a design method for a whole-aircraft high-cycle fatigue test load spectrum of an aircraft engine comprises the following steps:
determining an examination object of the complete machine high-cycle fatigue test run of the aero-engine according to the working principle of the aero-engine and the structural characteristics of each part, wherein the test run 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 the checking rotating speed of the engine in the working rotating speed range and the corresponding checking time, wherein the checking rotating speed comprises the following steps:
carrying out resonance rotating speed analysis according to the known vibration data of the parts, and correcting by combining the vibration characteristic dispersity to obtain a known resonance rotating speed analysis result;
determining the upper limit and the lower limit of a high-cycle fatigue test examination rotating speed according to the range of the working rotating speed interval of the aero-engine and the ground test condition, simultaneously 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 examination rotating speed and the range of the examination rotating speed by combining the upper limit and the lower limit of the examination rotating speed;
on the basis of checking the rotating speed, performing data integration on the known resonance rotating speed, the unknown resonance rotating speed and the critical rotating speed of the whole machine, and determining the checking time of each rotating speed subinterval;
and on the basis of finishing the test run load requirement, finishing the design of the high-cycle fatigue test run load spectrum by combining the acceleration and deceleration frequency requirement.
Furthermore, the examination objects comprise rotor blades, stator blades, external pipelines and casing thin-wall parts.
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 complete machine vibration critical rotating speed is determined according to the actual dynamic characteristic condition of the tested engine.
Furthermore, the examination time of each rotating speed subinterval is the maximum value of the residence 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 environment of the whole machine is adopted for examination, the load requirements are formulated respectively according to different parts and different vibration characteristics, the effectiveness, the integrity and the sufficiency of the high-cycle fatigue examination are guaranteed, a scientific, systematic, effective method and an operation flow are established for the design of the high-cycle fatigue test load spectrum of the whole machine, 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 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 flowchart of a whole high cycle fatigue test run load spectrum setting method according to 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.
In order to overcome the problems in the prior art, the high-cycle fatigue design attention points of the aero-engine are combed, the test run load determination principle and method are determined, and the whole machine high-cycle fatigue test run load spectrum compilation process is established, so that the whole machine high-cycle fatigue test run load spectrum design method is formed, and the aim of completely and fully examining the high-cycle fatigue resistance of parts of the aero-engine is fulfilled through the whole machine high-cycle fatigue test run.
As shown in FIG. 1, the method for designing the complete-machine high-cycle fatigue test load spectrum of the aircraft engine comprises the following steps:
1. high cycle fatigue load determination principle
The high-cycle fatigue load determination should comprehensively consider main failure modes of parts of the aero-engine, and determine assessment objects of the complete high-cycle fatigue test of the aero-engine according to the working principle of the aero-engine and the structural characteristics of the parts, wherein the assessment objects include but are not limited to rotor blades, stator blades, external pipelines, thin-walled parts of a casing and the like.
For the parts, the trial 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 speed
The known resonance rotating speed comprises two parts of the resonance rotating speed of parts and the critical rotating speed of the vibration of the whole machine.
The known resonance rotating speed of the part is mainly determined according to the vibration characteristic analysis, the dynamic stress test result and the like of the part.
For each stage of rotor blades, because the actual installed blades have the frequency dispersion degree, in order to achieve the purpose of full verification, the trial run rotating speed is corrected according to the frequency actual measurement result of each stage of blades, and the blades with larger dispersion degree and each dispersion zone with higher frequency concentration are verified as the resonance rotating speed.
For example, for titanium alloy parts, since it exceeds 10 7 The fatigue life after the secondary cycle is still continuously reduced, and the life requirement is 10 9 And (5) performing secondary circulation. However, according to the JSSG-2007 requirement, for titanium, the material performance test should be used, but not the engine test, so that the dwell time of the high-cycle fatigue test run resonance speed is still 10 7 Or 10 8 The secondary loop is the primary determination.
Complete machineThe vibration critical rotating speed is mainly determined according to the actual dynamic characteristic condition of the tested engine by referring to the rotor dynamics analysis result. The critical speed is the speed which is not used by engine, so the staying time is 1X 10 6 And determining a secondary loop.
b) Determining unknown resonant rotational speed
Besides the known resonance rotating speed of the parts and the whole machine, the high-cycle fatigue test run load spectrum also needs to consider the influence of other parts and unknown resonance rotating speed. The staying time refers to JSSG-2007 and relevant data of foreign high-cycle fatigue test run according to 1 x 10 6 The secondary cycle is determined, and the excitation factor is 3 times of the rotating speed.
c) Determining the number of acceleration and deceleration test runs
The change of air flow in the acceleration and deceleration process of the engine can influence the vibration of main parts, so the influence of the acceleration and the deceleration of the engine on the vibration is added in the HCF (High Cycle Fatigue) trial run load spectrum compilation.
2. Determining high cycle fatigue test run load spectrum
The high-cycle fatigue test load spectrum of the whole machine aims at determining the checking rotating speed and the corresponding checking time within the working rotating speed range of the engine, and the specific process of determining the load spectrum comprises the following steps:
(1) And (3) resonance rotating speed analysis: and (3) performing resonance rotating speed analysis by considering known data such as vibration characteristics of the parts, test measurement results and the like, and correcting by considering the dispersion of the vibration characteristics according to situations to obtain a known resonance rotating speed analysis result.
The table 1 is a statistical table of the analysis results of the known resonance rotation speed in an embodiment of the present application.
TABLE 1 analysis of known resonance rotational speeds
Figure BDA0003771346020000051
(2) Determining an examination rotating speed: comprehensively considering the range of the working rotating speed interval of the aero-engine and the ground test condition, and determining the upper limit and the lower limit of the high-cycle fatigue test examination rotating speed; and determining the span of the rotation speed subinterval by considering the control precision of the actual rotation speed of the engine test run, and determining the examination rotation speed and the interval range thereof by combining the upper limit rotation speed and the lower limit rotation speed.
(3) Determining assessment time: on the basis of checking the rotating speed, data integration analysis is carried out on the requirements of the known resonance rotating speed, the unknown resonance rotating speed, the critical rotating speed of the whole machine and the like, and the checking time of each rotating speed subinterval is determined by adopting the maximization principle.
As shown in table 2, the examination time table of each rotation speed subinterval in the embodiment of the present application is obtained, and it can be seen from the table that, for the working condition of 45% of low-pressure relative rotation speed, the longest retention time is "vibration characteristic analysis of rotor blade (-1%), so that the examination time of the rotation speed subinterval is 405min corresponding to the longest retention time; similarly, for the working condition of 46% of the low-pressure relative rotating speed, the longest retention time is the unknown resonance rotating speed, so that the corresponding 83min is selected for the examination time of the rotating speed subinterval. Other cases will not be described in detail.
TABLE 2 rotational speed examination time table
Figure BDA0003771346020000061
(4) Designing a trial load spectrum: and on the basis of the load requirements, the requirement of acceleration and deceleration times is 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 aircraft engine, a high-cycle fatigue test load spectrum is established, and according to the relevant theoretical calculation and test data analysis results, the high-cycle fatigue resistance of the main parts of the aircraft engine can be examined when the parts of the aircraft engine are tested on a ground rack.
According to the method, the environment of the whole machine is adopted for examination, the load requirements are formulated respectively according to different parts and different vibration characteristics, the effectiveness, the integrity and the sufficiency of the high-cycle fatigue examination are guaranteed, a scientific, systematic, effective method and an operation flow are established for the design of the high-cycle fatigue test load spectrum of the whole machine, the working efficiency is improved, and the flight safety is guaranteed.
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 (6)

1. A design method for a whole-engine high-cycle fatigue test load spectrum of an aircraft engine is characterized by comprising the following steps:
determining an examination object of the complete machine high-cycle fatigue test run of the aero-engine according to the working principle of the aero-engine and the structural characteristics of each part, wherein the test run 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 the checking rotating speed of the engine in the working rotating speed range and the corresponding checking time, wherein the checking rotating speed comprises the following steps:
carrying out resonance rotating speed analysis according to known vibration data of the parts, and correcting by combining with the dispersibility of vibration characteristics to obtain a known resonance rotating speed analysis result;
determining the upper limit and the lower limit of a high-cycle fatigue test examination rotating speed according to the range of the working rotating speed interval of the aero-engine and the ground test condition, simultaneously 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 examination rotating speed and the range of the examination rotating speed by combining the upper limit and the lower limit of the examination rotating speed;
on the basis of checking the rotating speed, performing data integration on the known resonance rotating speed, the unknown resonance rotating speed and the critical rotating speed of the whole machine, and determining the checking time of each rotating speed subinterval;
and on the basis of finishing the test run load requirement, the design of the high-cycle fatigue test run load spectrum is finished by combining the acceleration and deceleration frequency requirement.
2. The method for designing the complete-machine high-cycle fatigue test run load spectrum of the aero-engine as claimed in claim 1, wherein the assessment objects comprise rotor blades, stator blades, external pipelines and casing thin-wall parts.
3. The method for designing the complete-machine high-cycle fatigue test-run load spectrum of the aircraft engine according to claim 1, wherein the known resonance rotating speed comprises a part resonance rotating speed and a complete-machine vibration critical rotating speed.
4. The method for designing the complete-machine high-cycle fatigue test-run load spectrum of the aero-engine according to claim 3, wherein the known resonance rotating speed of the part is determined according to the vibration characteristic analysis and dynamic stress test result of the part.
5. The method for designing the complete-machine high-cycle fatigue test-run load spectrum of the aero-engine as claimed in claim 3, wherein the complete-machine vibration critical rotating speed is determined according to the actual power characteristic situation of the tested engine.
6. The design method of the complete machine high-cycle fatigue test run load spectrum of the aircraft engine as claimed in claim 1, wherein the examination time of each rotating speed subinterval is the maximum value of the residence time in the resonance rotating speed, the unknown resonance rotating speed and the complete machine critical rotating speed.
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Citations (3)

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Publication number Priority date Publication date Assignee Title
US20170293712A1 (en) * 2016-04-11 2017-10-12 Airbus Helicopters Deutschland GmbH Probabilistic load and damage modeling for fatigue life management
CN113945388A (en) * 2021-09-28 2022-01-18 太原理工大学 Shortening test method for vibration fatigue test of aeroengine blade
CN114354200A (en) * 2021-12-07 2022-04-15 中国航发控制系统研究所 Method for compiling vibration load spectrum of aircraft engine control system

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170293712A1 (en) * 2016-04-11 2017-10-12 Airbus Helicopters Deutschland GmbH Probabilistic load and damage modeling for fatigue life management
CN113945388A (en) * 2021-09-28 2022-01-18 太原理工大学 Shortening test method for vibration fatigue test of aeroengine blade
CN114354200A (en) * 2021-12-07 2022-04-15 中国航发控制系统研究所 Method for compiling vibration load spectrum of aircraft engine control system

Non-Patent Citations (1)

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Title
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