CN115356121A - Method for evaluating damage of service life and residual service life of turbine blade in service environment - Google Patents
Method for evaluating damage of service life and residual service life of turbine blade in service environment Download PDFInfo
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- CN115356121A CN115356121A CN202210972071.2A CN202210972071A CN115356121A CN 115356121 A CN115356121 A CN 115356121A CN 202210972071 A CN202210972071 A CN 202210972071A CN 115356121 A CN115356121 A CN 115356121A
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- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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Abstract
The application belongs to the field of life measurement of turbine blades of aero-engines, and discloses a method for evaluating damage to the service life and the residual life of a turbine blade in a service environment, which comprises the steps of carrying out real service state test run and service load statistical analysis on the turbine blade of an aero-engine, and correcting a calculation state; measuring the service blade temperature of the turbine blade of the aircraft engine; correcting the known temperature calculation model to obtain a corrected temperature calculation model; correcting the known input load, and performing a real turbine blade sampling simulation test on the non-service blade based on the corrected input load to obtain the mechanical property of the non-service blade under the actual service condition of a real component; and correcting the material model, inputting load after correction based on the calculation state after correction, and obtaining a life damage evaluation model of the turbine blade of the aircraft engine under the service environment after correction by using the corrected material model, thereby providing a systematic accurate life damage evaluation method of the turbine blade under the service environment.
Description
Technical Field
The application belongs to the field of life measurement of turbine blades of aeroengines, and particularly relates to a method for evaluating damage of service life and residual life of a turbine blade in a service environment.
Background
The invention relates to the field of strength design of aero-engines, in particular to application of strength and service life design of turbine blades, and the design can also be used for strength and service life design reference of other parts.
The turbine blade is one of the most critical parts of the aero-engine, the working environment of the turbine blade is quite severe, the borne load is quite complex, the structure of the turbine blade is provided with a complex geometric shape and an inner cavity, the turbine blade is in a quite complex stress state in work, the damage mode is complex, a plurality of influence factors are caused, and meanwhile, the test verification is difficult to perform. The life damage assessment of turbine blades is itself a relatively complex system engineering involving multiple disciplines of strength, structure, pneumatics, heat transfer, materials, testing, failure analysis, and the like. The service life analysis process relates to materials, loads, method models and the like, wherein the outstanding key technical problems comprise acquisition of the actual service load (temperature) of the turbine blade, incapability of mastering the difference between an actual component and a standard part and the like, and accordingly the turbine service life analysis precision is low; the test verification process relates to principle component level, simulation component level, component level (great difficulty) and whole machine level tests, blade damage evaluation can be carried out through multi-level tests combined with metallographic structure analysis technology, but true damage evaluation based on the component level tests is great difficulty. Meanwhile, by combining engineering design and problems in use, the service life damage evaluation requirement of the turbine blade of the aero-engine under the service environment cannot be met only through a single specialty, so that a multi-specialty collaborative service life damage evaluation method suitable for engineering under the service environment of the turbine blade of the aero-engine is urgently needed to be established.
In the prior art, various schools in academies and universities in China mainly develop researches aiming at the technical difficulties of the foregoing various specialties, and no multi-specialty collaborative life damage evaluation method and system are formed.
1) In the design stage of the service life of the turbine blade of the aero-engine, due to the influence of comprehensive factors such as load, materials and service life models, the accuracy of a service life analysis result is low, the deviation from a complete machine trial run and an external field use result is large, and the technical support for the service life determination of the engine is to be improved;
2) Aiming at the test verification stage of the turbine blade of the aero-engine, the service life test verification difficulty of the turbine blade under the service condition is high, the complete machine level test is mainly relied on, and an effective simulation part level and real component level test verification method is lacked;
3) In the prior art, the development of the technical capability of the profession is emphasized more, the synergistic fusion of the professions is not concerned, the requirement for evaluating the service life damage of the turbine blade of the aero-engine in the service environment cannot be met, and the improvement of the comprehensiveness and the engineering transformation of the technical capability of the related professions are not facilitated.
Disclosure of Invention
In order to solve the above problem, the present application provides a method for evaluating life damage of a turbine blade in a service environment, including:
step S1: carrying out real service state test run and service load statistical analysis on the turbine blade of the aircraft engine, correcting the known calculation state, and obtaining the corrected calculation state;
step S2: measuring the temperature of the blades of the aeroengine in service in the service state of the engine;
and step S4: correcting a known temperature calculation model based on the temperature of the service blade to obtain a corrected temperature calculation model;
step S5: based on the corrected calculation state and the corrected temperature calculation model, correcting the known input load to obtain a corrected input load;
step S6: based on the corrected input load, performing a real turbine blade sampling simulation test on the non-service blade to obtain the mechanical property of the non-service blade under the actual service condition of a real component; correcting the known material model in the database to obtain a corrected material model;
step S7: and (4) inputting the load after correction and the material model after correction based on the calculation state after correction to obtain a life damage evaluation model of the turbine blade of the aircraft engine in the service environment.
Preferably, the step S1 of performing test run and service load statistical analysis on the real service state includes: and identifying the large state time and acquiring the relevant section temperature, pneumatic load and rotating speed load parameters of the engine in the large state time.
Preferably, the known calculation state is corrected based on the large state time and the section temperature, the aerodynamic load and the rotating speed load parameters related to the engine in the large state time, and the strength point and the service life point for designing the aircraft engine, wherein the large state time is the process time from the engine to enter one preset state to enter another preset state.
Preferably, after measuring the in-service blade temperature in step S2, there is also an interpretation of the in-service blade temperature, which comprises: detecting the service blades by a metallographic structure detection technology, judging the actual service temperature of the service blades according to the result of the metallographic structure detection, and checking the judgment result of the actual service temperature of the service blades and the temperature of the service blades.
Preferably, the in-service blade temperature is corrected again for the corrected calculated state.
Preferably, the corrected input load includes: corrected temperature load and corrected pneumatic load.
Preferably, after the life damage evaluation model of the aircraft engine turbine blade in the service environment is obtained, the strength and life results of the plurality of turbine blades are calculated through the evaluation model, the results are compared with the strength and life results of the plurality of turbine blades in a test run and a service test, and the life damage evaluation model of the aircraft engine turbine blade in the service environment meeting the preset requirements is obtained through multiple iterations.
A method for evaluating damage of residual life of a turbine blade in a service environment comprises the following steps:
sampling the blades after service to obtain a test piece after service;
carrying out a real turbine blade sampling simulation test on the test piece, and respectively carrying out metallographic structure analysis on the test piece before and after the test;
combining the test result and the metallographic structure analysis result to obtain service damage and service life of the blade in service under the actual service condition;
the service life damage evaluation method under the turbine blade service environment is used for calculating the service life of the service blade, and the residual service life of the service blade is obtained through the service life, the service damage and the service life.
The advantages of the application include:
1) The method for evaluating the multi-professional collaborative life damage of the turbine blade of the aircraft engine in the service environment is provided, so that the life analysis precision of the turbine blade of the aircraft engine is improved;
2) Providing a test verification method for an aircraft engine turbine blade suitable for engineering, and realizing service damage and residual life evaluation of the turbine blade;
3) The method provides a multi-professional technical capability improving thought and technical development system for aero-engine turbine blades, wherein the multi-professional technical capability improving thought and technical development system is used for improving the relevant strength, structure, aerodynamics, heat transfer, materials, testing, failure analysis and the like of the aero-engine turbine blades, and is beneficial to the comprehensive development of professional technical capability and the improvement of multi-professional collaborative design capability.
Drawings
FIG. 1 is a flow chart of a method for evaluating life damage of a turbine blade in a service environment according to a preferred 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 accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments in the present application without making creative efforts shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
As shown in fig. 1, the method provided by the present application includes:
For convenience of explanation and calculation, the step is to uniformly acquire known parameters in the calculation step, and define various known data for evaluating the service life damage of the turbine blade of the aircraft engine in the service environment, and the known data comprises the following steps: calculating state, service state, blade model, real blade, material performance data, service load, pneumatic data and temperature data; wherein the calculation state is a theoretical state designed for the aircraft engine; and service load, pneumatic data and temperature data have different parameters under different engine states.
According to various parameters and states in the step 1, carrying out real service state test run and service load statistical analysis, and identifying large state time and section temperature, pneumatic load and rotating speed load parameters related to an engine;
the large state time is the process time from the time when the aircraft engine enters one preset state to the time when the aircraft engine enters the other preset state; the section temperature is the ambient temperature of a given section of the engine.
Correcting the calculated state based on the large state time obtained in the step 2 and the cross-section temperature, the pneumatic load and the rotating speed load parameters related to the engine of the large state time, and combining strength points and service life points for designing the aircraft engine to determine a set of corrected calculated state covering the service life of the real service condition;
step 4, measuring service environment
Carrying out temperature measurement data analysis of the actual service working condition of the engine on the basis of the condition of the corrected calculation state obtained in the step 3, namely measuring the actual working temperature of the turbine blade of the engine, perfecting the corrected calculation state, and simultaneously matching the actually measured temperature of the blade in service with the statistical load of the corresponding corrected calculation state;
And (3) detecting the turbine blade after service by a metallographic structure detection technology, judging the actual service temperature of the turbine blade according to the detection result, mutually verifying the actual service temperature of the turbine blade and the service temperature of the turbine blade obtained in the step (4), and matching the actual service temperature of the turbine blade with the corrected statistical load of the calculation state in the step (3).
Based on the steps 2, 3, 4 and 5, correcting the known temperature calculation model of the database to obtain a corrected temperature calculation model, and improving the calculation accuracy of the temperature load;
Based on the corrected calculation state in the step (3), applying the corrected blade temperature model in the step (6) to carry out load calculation under the actual service working condition of the engine;
And 7, based on the load calculation in the step 7, correcting the known input load of the database, and acquiring the corrected input load required by the service life evaluation of the actual service state of the engine, wherein the corrected input load comprises a corrected temperature load and a corrected pneumatic load.
Step 9, material data supplement
Based on the step 8, quickly acquiring material performance data within a service temperature range by applying an accelerated test method according to the corrected temperature load;
Based on the turbine blade model in the step 1, an unused blade sampling scheme and a simulation test piece design scheme are formulated and used for obtaining the real mechanical properties of different parts of the turbine blade;
Based on the sampling scheme in the step 10 and the corrected temperature load in the step 8, carrying out a real turbine blade sampling simulation test to obtain the mechanical property of a real component under the actual service condition;
Based on the test results of the steps 9 and 11, correcting the known material model in the database to obtain a corrected material model, further improving the precision of the material model, and further improving the service life calculation precision of the turbine blade;
Analyzing the actual service environment strength and the service life of the turbine blade based on the calculation state after the correction in the step 3, the input load after the correction in the step 8 and the corrected material model in the step 12;
And comparing the strength and service life analysis results obtained by calculation in the step 13 with strength and service life analysis results obtained by trial run and service, judging whether the calculation results meet the design requirements of the service life of the engine, and iterating for multiple times to obtain a service life damage evaluation model of the turbine blade of the aircraft engine in the service environment, which meets the preset requirements.
Based on the step 14, combining the data input in the step 1, a turbine blade simulation test scheme is formulated, wherein the test scheme comprises a service blade sampling test and metallographic structure detection.
Formulating a test scheme based on the step 15, and processing to obtain a serving blade sampling simulation test piece;
Obtaining a test piece based on the step 16, and carrying out a real turbine blade sampling simulation test according to the test scheme of the step 15;
Carrying out metallographic structure analysis before and after sampling according to the test scheme in the step 15;
Combining the test results of the step 17 and the step 18 with the metallographic structure analysis result to obtain service damage and service life of the typical part of the real component under the actual service condition;
And (3) combining the service life calculation result in the step 14 and the service damage and the used service life of the typical part in the step 19, and evaluating the service damage and the residual service life of other concerned parts of the turbine blade.
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 (8)
1. A method for evaluating life damage of a turbine blade in a service environment is characterized by comprising the following steps:
step S1: carrying out real service state test run and service load statistical analysis on the turbine blade of the aircraft engine, correcting the known calculation state, and obtaining the corrected calculation state;
step S2: measuring the temperature of the blades of the aeroengine in service in the service state of the engine;
and step S4: correcting a known temperature calculation model based on the service blade temperature to obtain a corrected temperature calculation model;
step S5: based on the corrected calculation state and the corrected temperature calculation model, correcting the known input load to obtain a corrected input load;
step S6: based on the corrected input load, carrying out a real turbine blade sampling simulation test on the non-service blade to obtain the mechanical property of the non-service blade under the actual service condition of a real component; correcting the known material model in the database to obtain a corrected material model;
step S7: and inputting the load after correction and the material model after correction based on the calculation state after correction to obtain a life damage evaluation model of the turbine blade of the aircraft engine in the service environment.
2. The method for evaluating life damage of a turbine blade in a service environment as claimed in claim 1, wherein the step S1 of the real service state test run and service load statistical analysis includes: the method comprises the steps of identifying large state time, and obtaining relevant section temperature, pneumatic load and rotating speed load parameters of the engine in the large state time, wherein the large state time is the process time from the engine entering one preset state to the engine entering the other preset state.
3. The method for evaluating life damage of a turbine blade in a service environment as claimed in claim 2, wherein the known calculated state is corrected based on the large state time and the section temperature, the aerodynamic load and the rotating speed load parameters related to the engine in the large state time by combining the strength point and the life point for designing the aircraft engine.
4. The method for evaluating life damage of a turbine blade in service according to claim 1, wherein after measuring the temperature of the blade in service in step S2, there is also an interpretation of the temperature of the blade in service, the interpretation of the temperature of the blade in service comprising: detecting the service blades by a metallographic structure detection technology, judging the actual service temperature of the service blades according to the result of the metallographic structure detection, and checking the judgment result of the actual service temperature of the service blades and the temperature of the service blades.
5. The method for life damage assessment of a turbine blade in service environment of claim 1, wherein said service blade temperature is re-corrected for post-correction calculated conditions.
6. The turbine blade in-service life damage assessment method of claim 1, wherein said modified input load comprises: corrected temperature load and corrected pneumatic load.
7. The method for evaluating the service life damage of the turbine blades in the service environment of the aircraft engine as claimed in claim 1, wherein after obtaining the service life damage evaluation model of the turbine blades in the service environment of the aircraft engine, the evaluation model is used for calculating the strength and service life results of the plurality of turbine blades, comparing the strength and service life results with the strength and service life results of the plurality of turbine blades in a test run and service test, and iterating for multiple times to obtain the service life damage evaluation model of the turbine blades in the service environment of the aircraft engine, which meets the preset requirements.
8. A method for evaluating damage of residual life of a turbine blade in a service environment is characterized by comprising the following steps:
sampling the blades after service to obtain a test piece after service;
carrying out a real turbine blade sampling simulation test on the test piece, and respectively carrying out metallographic structure analysis on the test piece before and after the test;
combining the test result and the metallographic structure analysis result to obtain service damage and service life of the blade in service under the actual service condition;
calculating the service life of the in-service blade by using the method for evaluating the service life damage of the turbine blade in the service environment according to any one of claims 1 to 7, and obtaining the residual service life of the in-service blade through the service life, the service damage and the used service life.
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| CN202210972071.2A CN115356121A (en) | 2022-08-14 | 2022-08-14 | Method for evaluating damage of service life and residual service life of turbine blade in service environment |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115979345A (en) * | 2022-12-30 | 2023-04-18 | 共青科技职业学院 | Artificial intelligence prediction system and prediction method for residual life of marine gas turbine blade |
| CN117129332A (en) * | 2023-08-29 | 2023-11-28 | 中国航发湖南动力机械研究所 | Method and system for acquiring strength life input data of engine complete machine corrosion test |
| CN117330319A (en) * | 2023-08-31 | 2024-01-02 | 南京航空航天大学 | Method for monitoring damage of whole engine life test run structure of small turboshaft engine |
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2022
- 2022-08-14 CN CN202210972071.2A patent/CN115356121A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115979345A (en) * | 2022-12-30 | 2023-04-18 | 共青科技职业学院 | Artificial intelligence prediction system and prediction method for residual life of marine gas turbine blade |
| CN115979345B (en) * | 2022-12-30 | 2023-09-22 | 共青科技职业学院 | Artificial intelligence marine gas turbine blade residual life prediction system and prediction method |
| CN117129332A (en) * | 2023-08-29 | 2023-11-28 | 中国航发湖南动力机械研究所 | Method and system for acquiring strength life input data of engine complete machine corrosion test |
| CN117129332B (en) * | 2023-08-29 | 2024-05-10 | 中国航发湖南动力机械研究所 | Method and system for acquiring strength life input data of engine complete machine corrosion test |
| CN117330319A (en) * | 2023-08-31 | 2024-01-02 | 南京航空航天大学 | Method for monitoring damage of whole engine life test run structure of small turboshaft engine |
| CN117330319B (en) * | 2023-08-31 | 2024-04-02 | 南京航空航天大学 | Method for monitoring damage of whole engine life test run structure of small turboshaft engine |
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