CN115114733B - Multi-level test verification method for service life of turbine blade coating - Google Patents
Multi-level test verification method for service life of turbine blade coating Download PDFInfo
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- CN115114733B CN115114733B CN202210868518.1A CN202210868518A CN115114733B CN 115114733 B CN115114733 B CN 115114733B CN 202210868518 A CN202210868518 A CN 202210868518A CN 115114733 B CN115114733 B CN 115114733B
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- 238000000576 coating method Methods 0.000 title claims abstract description 121
- 238000012360 testing method Methods 0.000 title claims abstract description 111
- 239000011248 coating agent Substances 0.000 title claims abstract description 103
- 238000012795 verification Methods 0.000 title claims abstract description 37
- 238000000034 method Methods 0.000 title claims abstract description 22
- 238000009413 insulation Methods 0.000 claims abstract description 22
- 230000035939 shock Effects 0.000 claims abstract description 17
- 238000013461 design Methods 0.000 claims abstract description 13
- 239000000758 substrate Substances 0.000 claims abstract description 12
- 238000010206 sensitivity analysis Methods 0.000 claims abstract description 7
- 238000011161 development Methods 0.000 claims abstract description 4
- 238000009960 carding Methods 0.000 claims abstract description 3
- 238000010200 validation analysis Methods 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 2
- 230000014759 maintenance of location Effects 0.000 claims 1
- 230000008569 process Effects 0.000 description 8
- 230000000694 effects Effects 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 4
- 238000001816 cooling Methods 0.000 description 3
- 238000004088 simulation Methods 0.000 description 3
- 230000006872 improvement Effects 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 238000005507 spraying Methods 0.000 description 2
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 238000001311 chemical methods and process Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 238000010894 electron beam technology Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000012720 thermal barrier coating Substances 0.000 description 1
- 238000007740 vapor deposition Methods 0.000 description 1
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Abstract
The application provides a multi-level test verification method for the service life of a turbine blade coating, which comprises the following steps: the method comprises the steps of carding engineering development requirements of turbine blades of aero-engines, converting the requirements into design input, and determining coating parameters of the turbine blades according to constraints of the design input, wherein the coating parameters comprise a coating process, a coating thickness and a coating-substrate matching degree; carrying out sensitivity analysis of test influence factors, and determining sensitive parameters and non-sensitive parameters influencing the service life of the blade coating; aiming at sensitive parameters, carrying out a thermal shock test on a simple test piece with a coating, further carrying out a thermal shock test on a single blade with the coating under the condition of meeting the requirement, further carrying out a thermal insulation test on the simple test piece with the coating under the condition of meeting the requirement, further carrying out a thermal insulation test on the single blade with the coating under the condition of meeting the requirement, and further carrying out a thermal insulation test on the complete machine blade with the coating under the condition of meeting the requirement; and curing the coating process parameters on the basis of meeting the requirements of the whole machine.
Description
Technical Field
The application belongs to the technical field of aero-engine tests, and particularly relates to a multi-level test verification method for the service life of a turbine blade coating.
Background
In recent years, with the improvement of the performance requirement of an aero-engine, the temperature bearing capacity of a turbine blade is required to be higher, the traditional composite air film cooling blade approaches the limit of engineering design, no space for large-amplitude improvement exists, and the turbine blade cooling technology only adopting air film cooling cannot meet the requirement of a high-efficiency turbine on the inlet temperature, so that the blade heat insulation coating technology becomes a new breakthrough.
At present, theoretical simulation design and single verification of a flat test piece are mainly focused on blade heat insulation coating design, the simulation of a coating mechanism is mainly developed on the theoretical simulation design level, and key parameters influencing the functionality and durability of the coating are lack of carding and discrimination; in the aspect of experimental verification, the method mainly focuses on the heat insulation effect of the coating, lacks verification on the thermal shock service life, neglects the requirement on the durability of the coating, and lacks the process of sensitivity analysis of influence factors of the coating during verification, so that a plurality of insensitive parameters are brought into the verification process, the verification efficiency is reduced, and extra unnecessary cost is increased. In addition, the characteristic structure of the blade is seriously separated by adopting the flat test piece for verification, the combination compactness of the coating and the base body is closely related to the structural form of the component and the service environment, the test run verification of the whole turbine blade level is lacked in the prior art, and a test piece-component-whole machine level multi-level verification flow is not formed.
Therefore, an effective multi-level test verification method for the turbine blade coating is urgently needed to meet the engineering application of the thermal barrier coating on the turbine blade.
Disclosure of Invention
The application aims to provide a multi-level test verification method for the coating life of a turbine blade, so as to solve or reduce at least one problem in the background art.
The technical scheme of the application is as follows: a turbine blade coating life multi-level test validation method, the method comprising:
step 1, combing engineering development requirements of turbine blades of aero-engines, converting the requirements into design input, and determining coating parameters of the turbine blades according to constraints of the design input, wherein the coating parameters comprise a coating process, a coating thickness and a coating-substrate matching degree;
step 2, carrying out sensitivity analysis of test influence factors, and determining sensitive parameters and non-sensitive parameters influencing the service life of the blade coating;
3, carrying out a thermal shock test on the coated simple test piece aiming at the sensitive parameters, judging whether the test result meets the index requirement, if not, adjusting and optimizing the coating parameters, and if so, entering the next step;
step 4, on the basis of the step 3, carrying out a single blade thermal shock test with a coating, judging whether a test result meets an index requirement, if not, adjusting and optimizing coating parameters, and if so, entering the next step;
step 5, on the basis of the step 4, developing a simple test piece heat insulation test with a coating, judging whether the test result meets the index requirement, if not, adjusting and optimizing the coating parameters, and if so, entering the next step;
step 6, on the basis of the step 5, developing a single blade heat insulation test with a coating, judging whether the test result meets the index requirement, if not, adjusting and optimizing the coating parameters, and if so, entering the next step;
step 7, on the basis of the step 6, developing a complete machine blade heat insulation test with a coating, judging whether a test result meets the complete machine requirement, if not, adjusting and optimizing coating parameters, and if so, entering the next step;
and 8, curing the technological parameters of the coating on the basis of meeting the requirements of the whole machine to form the coating technology meeting the engineering use requirements.
Further, the simple test piece comprises a round tube test piece and/or a flat plate test piece.
Further, the test parameters and indexes of the simple coated test piece and the single coated blade thermal shock test are required to be executed according to corresponding test standards.
Further, the test parameters and indexes of the simple coated test piece and the single coated blade heat insulation test are required to be executed according to corresponding test standards.
Compared with the prior art, the multi-level test verification method for the service life of the turbine blade coating eliminates factors with low influence on the mechanical property and the service life reliability of the coating through the sensitivity analysis of the influence factors of the coating, improves the test verification efficiency and reduces the test cost; the verification of the heat insulation effect and the thermal shock life of the coating is comprehensively considered, the durability and the reliability (thermal shock life) of the coating are further considered while the functionality (heat insulation effect) of the coating is ensured, the service life of the coating is prolonged, and the subsequent verification and use risk are reduced; the complete machine-level test run verification of the turbine blade is carried out, a test piece-member-complete machine-level multi-level and complete test verification flow is formed, the technical maturity is high, the verified coating process can be directly applied to engineering, and the verification period is shortened.
Drawings
In order to more clearly illustrate the technical solutions provided in the present application, the drawings will be briefly described below. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a flow chart of a turbine blade coating life multi-stage validation method 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 drawings in the embodiments of the present application.
According to the multi-level test verification method for the service life of the turbine blade coating, sensitive parameters based on engineering requirements are screened and brought into a test verification process, the verification iteration efficiency is improved, a thermal shock test based on the service working condition of the turbine blade is developed, process parameters meeting the service life requirement of the turbine blade are screened, the design requirement of the service life of the turbine blade is further met, finally, the verification of a turbine blade hanging piece test vehicle is developed, and a test piece-component-complete machine level multi-level test verification process is established;
as shown in FIG. 1, the turbine blade coating life multi-level test verification method comprises the following specific processes:
step 1, combing engineering development requirements of turbine blades of aero-engines, converting the requirements into design input, and determining coating parameters of the turbine blades according to constraints of the design input.
Wherein, the coating parameters mainly comprise:
the coating process comprises the following steps: the coating process comprises a coating chemical process and a physical process, such as plasma coating, electron beam vapor deposition coating and the like;
coating thickness: the thickness of the coating is the spraying thickness of the coating, and the mechanical property of the coating can be directly influenced by the thickness of the coating;
coating-substrate matching degree: in the spraying process, the coating can further penetrate into the substrate, on one hand, the mechanical property of the substrate is influenced, and on the other hand, a coating-substrate bonding layer is formed, so that the bonding strength of the coating and the substrate is determined.
And 2, carrying out test influence factor sensitivity analysis, emphatically analyzing influence factors related to the requirements in the step 1, finally determining sensitive parameters and non-sensitive parameters which influence the service life of the blade coating, and further carrying out verification work on the sensitive parameters.
In the present application, the sensitive parameters mainly include coating process parameters (such as temperature, concentration, holding time and the like during coating processing) and coating-substrate matching parameters (such as matching capability of different substrate materials such as single crystal, ceramic, high temperature alloy and the like and the coating), and the non-sensitive parameters mainly include the coating thickness.
3, carrying out a thermal shock test on the coated round tube test piece according to the sensitive parameters, judging whether the test result meets the index requirement, and if not, adjusting and optimizing the coating process, the coating thickness and the like; and if the index requirement is met, the next step is carried out.
It should be noted that the test parameters, index requirements, and the like of the thermal shock test can refer to corresponding test standards, and are not described herein again.
Step 4, on the basis of the step 3, carrying out a single blade thermal shock test with a coating, judging whether the test result meets the index requirement, and if not, adjusting and optimizing the coating process, the coating thickness and the like; and if the index requirement is met, the next step is carried out.
Step 5, developing a circular tube test piece heat insulation test with a coating on the basis of the step 4, judging whether the test result meets the index requirement, and if not, adjusting and optimizing the coating process, the coating thickness and the like; and if the index requirement is met, the next step is carried out.
It should be noted that, the test parameters, index requirements, and the like of the heat insulation test can refer to the corresponding test standards, and are not described herein again.
Step 6, developing a single blade heat insulation test with a coating on the basis of the step 5, judging whether the test result meets the index requirement, and if not, adjusting and optimizing the coating process, the coating thickness and the like; and if the index requirement is met, the next step is carried out.
Step 7, on the basis of the step 6, developing a complete machine blade heat insulation test with a coating, judging whether a test result meets the complete machine requirement, and if the test result does not meet the index requirement, adjusting and optimizing the coating process, the coating thickness and the like; if the index requirement is met, entering the next step;
and 8, curing the technological parameters of the coating on the basis of meeting the requirements of the whole machine to form the coating technology meeting the engineering use requirements.
Compared with the prior art, the multi-level test verification method for the service life of the turbine blade coating, provided by the application, has the advantages that factors which have lower influence on the mechanical property and the service life reliability of the coating are eliminated through the sensitivity analysis of the influence factors of the coating, the test verification efficiency is improved, and the test cost is reduced; the verification of the heat insulation effect and the thermal shock life of the coating is comprehensively considered, the durability and the reliability (thermal shock life) of the coating are further considered while the functionality (heat insulation effect) of the coating is ensured, the service life of the coating is prolonged, and the subsequent verification and use risk are reduced; the complete machine-level test run verification of the turbine blade is carried out, a test piece-member-complete machine-level multi-level and complete test verification flow is formed, the technical maturity is high, the verified coating process can be directly applied to engineering, and the verification period is shortened.
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 (4)
1. A multi-level test verification method for the coating life of a turbine blade is characterized by comprising the following steps:
step 1, carding engineering development requirements of turbine blades of aero-engines, converting the requirements into design input, and determining coating parameters of the turbine blades according to constraints of the design input, wherein the coating parameters comprise a coating process, a coating thickness and a coating-substrate matching degree;
step 2, carrying out sensitivity analysis of test influence factors, and determining sensitive parameters and non-sensitive parameters influencing the service life of the blade coating, wherein the sensitive parameters comprise coating process parameters representing the temperature, concentration and retention time during coating treatment and coating-substrate matching degree parameters representing the matching capability of different substrate materials and coatings, and the non-sensitive parameters comprise the coating thickness;
3, carrying out a thermal shock test on the simple test piece with the coating aiming at the sensitive parameters, judging whether the test result meets the index requirement, if not, adjusting and optimizing the coating parameters, and if so, entering the next step;
step 4, on the basis of the step 3, carrying out a single blade thermal shock test with a coating, judging whether a test result meets an index requirement, if not, adjusting and optimizing coating parameters, and if so, entering the next step;
step 5, on the basis of the step 4, developing a simple test piece heat insulation test with a coating, judging whether the test result meets the index requirement, if not, adjusting and optimizing the coating parameters, and if so, entering the next step;
step 6, on the basis of the step 5, developing a single blade heat insulation test with a coating, judging whether the test result meets the index requirement, if not, adjusting and optimizing the coating parameters, and if so, entering the next step;
step 7, on the basis of the step 6, developing a complete machine blade heat insulation test with a coating, judging whether a test result meets the complete machine requirement, if not, adjusting and optimizing coating parameters, and if so, entering the next step;
and 8, curing coating process parameters on the basis of meeting the requirements of the whole machine to form a coating process meeting the engineering use requirements.
2. The turbine blade coating life multi-level test validation method of claim 1, wherein the simple test piece comprises a round tube test piece and/or a flat plate test piece.
3. The turbine blade coating life multi-level test validation method of claim 2, wherein the test parameters and indicators of the coated plain test piece and the coated single blade thermal shock test are required to be performed with reference to corresponding test standards.
4. The multi-level test validation method for turbine blade coating life according to claim 2, wherein the test parameters and indexes of the coated simple test piece and the coated single blade heat insulation test are required to be executed by referring to corresponding test standards.
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102565119A (en) * | 2010-12-14 | 2012-07-11 | 中国航空工业集团公司沈阳发动机设计研究所 | Method for measuring cooling effect and thermal insulation effect of turbine blade with thermal barrier coating |
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| CN107084844B (en) * | 2017-04-19 | 2019-02-05 | 西北工业大学 | A kind of test method of blade structure simulation part |
| US11361233B2 (en) * | 2018-08-23 | 2022-06-14 | Siemens Energy Global GmbH & Co. KG | Estimating fatigue life of technical systems |
| CN109446592B (en) * | 2018-10-09 | 2020-02-07 | 湘潭大学 | Method for evaluating application effect of thermal barrier coating of turbine blade |
| CN111693379A (en) * | 2020-06-17 | 2020-09-22 | 北京航空航天大学 | System and method for testing high-temperature mechanical properties of tiny samples of turbine blades with complex configurations |
| CN112162005A (en) * | 2020-08-27 | 2021-01-01 | 湘潭大学 | Method and device for detecting thermal insulation effect of thermal barrier coating of turbine blade |
| CN113011109B (en) * | 2021-01-15 | 2022-05-17 | 浙江大学 | Fatigue analysis method of wind turbine blade coating considering raindrop erosion |
| CN113466041B (en) * | 2021-06-29 | 2024-01-30 | 中国航发沈阳发动机研究所 | Turbine blade seepage layer mechanical property test evaluation method |
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| CN102565119A (en) * | 2010-12-14 | 2012-07-11 | 中国航空工业集团公司沈阳发动机设计研究所 | Method for measuring cooling effect and thermal insulation effect of turbine blade with thermal barrier coating |
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| Title |
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| 李钊 ; 蔡文波 ; .热障涂层技术在航空发动机涡轮叶片上的应用.航空发动机.2015,(05),全文. * |
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