The method of calculating the minimum creep rate of turbine blades of gas turbine engines based on the degradation of the alloy microstructure
In the current global economic conditions, airlines need to curtail financial expenses. It is known that the share of airline costs for maintenance and repair (MR) in the total cost structure amounts to at least 20%, of which more than 40% is for the repair and maintenance of aircraft engines (AE)....
Saved in:
| Main Authors: | , , |
|---|---|
| Format: | Article |
| Language: | Russian |
| Published: |
Moscow State Technical University of Civil Aviation
2023-03-01
|
| Series: | Научный вестник МГТУ ГА |
| Subjects: | |
| Online Access: | https://avia.mstuca.ru/jour/article/view/2136 |
| Tags: |
Add Tag
No Tags, Be the first to tag this record!
|
| _version_ | 1849408744189853696 |
|---|---|
| author | Y. V. Petrov O. A. Ratenko V. K. Kharina |
| author_facet | Y. V. Petrov O. A. Ratenko V. K. Kharina |
| author_sort | Y. V. Petrov |
| collection | DOAJ |
| description | In the current global economic conditions, airlines need to curtail financial expenses. It is known that the share of airline costs for maintenance and repair (MR) in the total cost structure amounts to at least 20%, of which more than 40% is for the repair and maintenance of aircraft engines (AE). According to the actual expertise, this item of expenditure will continue to grow due to the inevitable sophistication of AE structures, which is specified by the need to increase the efficiency and ecological compatibility. One of the possible ways of curbing maintenance and repair expenses is to transit for the operation of on-condition components which are currently in operation until the overhaul life is exhausted. For example, turbine blades of gas turbine engines (GTE) can be pertinent to such elements. It is a common fact that turbine blades operate in challenging environment: they are affected by excessive temperatures, severe centrifugal loads, aggressive gas media, and their destruction generally occurs because of the accumulation of fatigue damage and creep. The alloy microstructure significantly degrades and deforms before macroscopic damage develops. The early detection of microscopic damage in the alloy is the tool which allows for the transition to GTE oncondition turbine blades operation. The article presents the method for calculating the minimum creep rate of the Inconel 738LC alloy based on microstructural changes under operating conditions. The obtained results are proposed to be used for calculating the residual life of turbine blades by the creep parameter. |
| format | Article |
| id | doaj-art-b895ccd906e449bc91fff26f84d3dd5e |
| institution | Kabale University |
| issn | 2079-0619 2542-0119 |
| language | Russian |
| publishDate | 2023-03-01 |
| publisher | Moscow State Technical University of Civil Aviation |
| record_format | Article |
| series | Научный вестник МГТУ ГА |
| spelling | doaj-art-b895ccd906e449bc91fff26f84d3dd5e2025-08-20T03:35:41ZrusMoscow State Technical University of Civil AviationНаучный вестник МГТУ ГА2079-06192542-01192023-03-012619510310.26467/2079-0619-2023-26-1-95-1031467The method of calculating the minimum creep rate of turbine blades of gas turbine engines based on the degradation of the alloy microstructureY. V. Petrov0O. A. Ratenko1V. K. Kharina2Moscow State Technical University of Civil AviationMoscow State Technical University of Civil AviationMoscow State Technical University of Civil AviationIn the current global economic conditions, airlines need to curtail financial expenses. It is known that the share of airline costs for maintenance and repair (MR) in the total cost structure amounts to at least 20%, of which more than 40% is for the repair and maintenance of aircraft engines (AE). According to the actual expertise, this item of expenditure will continue to grow due to the inevitable sophistication of AE structures, which is specified by the need to increase the efficiency and ecological compatibility. One of the possible ways of curbing maintenance and repair expenses is to transit for the operation of on-condition components which are currently in operation until the overhaul life is exhausted. For example, turbine blades of gas turbine engines (GTE) can be pertinent to such elements. It is a common fact that turbine blades operate in challenging environment: they are affected by excessive temperatures, severe centrifugal loads, aggressive gas media, and their destruction generally occurs because of the accumulation of fatigue damage and creep. The alloy microstructure significantly degrades and deforms before macroscopic damage develops. The early detection of microscopic damage in the alloy is the tool which allows for the transition to GTE oncondition turbine blades operation. The article presents the method for calculating the minimum creep rate of the Inconel 738LC alloy based on microstructural changes under operating conditions. The obtained results are proposed to be used for calculating the residual life of turbine blades by the creep parameter.https://avia.mstuca.ru/jour/article/view/2136turbine bladealloy microstructuregamma-prime phasecoagulationcreepmonkman-grant relationship |
| spellingShingle | Y. V. Petrov O. A. Ratenko V. K. Kharina The method of calculating the minimum creep rate of turbine blades of gas turbine engines based on the degradation of the alloy microstructure Научный вестник МГТУ ГА turbine blade alloy microstructure gamma-prime phase coagulation creep monkman-grant relationship |
| title | The method of calculating the minimum creep rate of turbine blades of gas turbine engines based on the degradation of the alloy microstructure |
| title_full | The method of calculating the minimum creep rate of turbine blades of gas turbine engines based on the degradation of the alloy microstructure |
| title_fullStr | The method of calculating the minimum creep rate of turbine blades of gas turbine engines based on the degradation of the alloy microstructure |
| title_full_unstemmed | The method of calculating the minimum creep rate of turbine blades of gas turbine engines based on the degradation of the alloy microstructure |
| title_short | The method of calculating the minimum creep rate of turbine blades of gas turbine engines based on the degradation of the alloy microstructure |
| title_sort | method of calculating the minimum creep rate of turbine blades of gas turbine engines based on the degradation of the alloy microstructure |
| topic | turbine blade alloy microstructure gamma-prime phase coagulation creep monkman-grant relationship |
| url | https://avia.mstuca.ru/jour/article/view/2136 |
| work_keys_str_mv | AT yvpetrov themethodofcalculatingtheminimumcreeprateofturbinebladesofgasturbineenginesbasedonthedegradationofthealloymicrostructure AT oaratenko themethodofcalculatingtheminimumcreeprateofturbinebladesofgasturbineenginesbasedonthedegradationofthealloymicrostructure AT vkkharina themethodofcalculatingtheminimumcreeprateofturbinebladesofgasturbineenginesbasedonthedegradationofthealloymicrostructure AT yvpetrov methodofcalculatingtheminimumcreeprateofturbinebladesofgasturbineenginesbasedonthedegradationofthealloymicrostructure AT oaratenko methodofcalculatingtheminimumcreeprateofturbinebladesofgasturbineenginesbasedonthedegradationofthealloymicrostructure AT vkkharina methodofcalculatingtheminimumcreeprateofturbinebladesofgasturbineenginesbasedonthedegradationofthealloymicrostructure |