The Generalized Tensor Model for Numerical Investigation of Combustion and Flow Processes in Liquid Rocket Engine Chamber
Combustion and flow thermogasdynamics is one of the most sophisticated computational stages in liquid rocket engine (LRE) design. A considerable amount of different methodologies used to conduct the thermogasdynamic analysis of the combustion and flow process and...
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| Format: | Article |
| Language: | English |
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Turkish Air Force Academy
2023-01-01
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| Series: | Havacılık ve Uzay Teknolojileri Dergisi |
| Subjects: | |
| Online Access: | https://jast.hho.msu.edu.tr/index.php/JAST/article/view/514/374 |
| _version_ | 1797915251958611968 |
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| author | Nijat Abdulla Parviz Abdullayev |
| author_facet | Nijat Abdulla Parviz Abdullayev |
| author_sort | Nijat Abdulla |
| collection | DOAJ |
| description | Combustion and flow thermogasdynamics is one of the most sophisticated computational stages in liquid rocket engine (LRE) design. A considerable amount of different methodologies used to conduct the thermogasdynamic analysis of the combustion and flow process and obtain the accurate estimates of the parameters of the LRE chamber is known. However, the development of a generalized mathematical model that would have a capability of being applied for any unique combustion case by, hence, yielding reliable results and, nevertheless, be efficient in any application still remains to be an issue. The following paper considers the development of a generalized tensor model the application of which for any desired propellant configuration yields unique results. In addition considered the application of the mentioned model at significant nozzle sections. Moreover the current paper, also, considers an approach based on the specific area in order to compute the parameters at the nozzle throat. The uniqueness of this methodology stems from the fact that the findings appear to be more accurate than those acquired using conventional methods. The paper accurately summarizes the application of the generalized tensor model based on an example problem which involves the combustion of liquid methane with liquid oxygen. |
| first_indexed | 2024-04-10T12:38:48Z |
| format | Article |
| id | doaj.art-b4baee2be8a14e3ab35ab9c21b8645d3 |
| institution | Directory Open Access Journal |
| issn | 1304-0448 2148-1059 |
| language | English |
| last_indexed | 2024-04-10T12:38:48Z |
| publishDate | 2023-01-01 |
| publisher | Turkish Air Force Academy |
| record_format | Article |
| series | Havacılık ve Uzay Teknolojileri Dergisi |
| spelling | doaj.art-b4baee2be8a14e3ab35ab9c21b8645d32023-02-15T16:14:25ZengTurkish Air Force AcademyHavacılık ve Uzay Teknolojileri Dergisi1304-04482148-10592023-01-011611540The Generalized Tensor Model for Numerical Investigation of Combustion and Flow Processes in Liquid Rocket Engine ChamberNijat Abdulla0https://orcid.org/0000-0003-3669-0501Parviz Abdullayev1https://orcid.org/0000-0002-0248-9941DEFTECH, Department of Research and Development, Suleyman Sani Akhundov, 1E, Baku, AzerbaijanNational Aviation Academy, Department of Flight Vehicles and Jet Engines, AZ1045, Baku, AzerbaijanCombustion and flow thermogasdynamics is one of the most sophisticated computational stages in liquid rocket engine (LRE) design. A considerable amount of different methodologies used to conduct the thermogasdynamic analysis of the combustion and flow process and obtain the accurate estimates of the parameters of the LRE chamber is known. However, the development of a generalized mathematical model that would have a capability of being applied for any unique combustion case by, hence, yielding reliable results and, nevertheless, be efficient in any application still remains to be an issue. The following paper considers the development of a generalized tensor model the application of which for any desired propellant configuration yields unique results. In addition considered the application of the mentioned model at significant nozzle sections. Moreover the current paper, also, considers an approach based on the specific area in order to compute the parameters at the nozzle throat. The uniqueness of this methodology stems from the fact that the findings appear to be more accurate than those acquired using conventional methods. The paper accurately summarizes the application of the generalized tensor model based on an example problem which involves the combustion of liquid methane with liquid oxygen.https://jast.hho.msu.edu.tr/index.php/JAST/article/view/514/374liquid rocket enginecombustion and flow processesgeneralized tensor model |
| spellingShingle | Nijat Abdulla Parviz Abdullayev The Generalized Tensor Model for Numerical Investigation of Combustion and Flow Processes in Liquid Rocket Engine Chamber Havacılık ve Uzay Teknolojileri Dergisi liquid rocket engine combustion and flow processes generalized tensor model |
| title | The Generalized Tensor Model for Numerical Investigation of Combustion and Flow Processes in Liquid Rocket Engine Chamber |
| title_full | The Generalized Tensor Model for Numerical Investigation of Combustion and Flow Processes in Liquid Rocket Engine Chamber |
| title_fullStr | The Generalized Tensor Model for Numerical Investigation of Combustion and Flow Processes in Liquid Rocket Engine Chamber |
| title_full_unstemmed | The Generalized Tensor Model for Numerical Investigation of Combustion and Flow Processes in Liquid Rocket Engine Chamber |
| title_short | The Generalized Tensor Model for Numerical Investigation of Combustion and Flow Processes in Liquid Rocket Engine Chamber |
| title_sort | generalized tensor model for numerical investigation of combustion and flow processes in liquid rocket engine chamber |
| topic | liquid rocket engine combustion and flow processes generalized tensor model |
| url | https://jast.hho.msu.edu.tr/index.php/JAST/article/view/514/374 |
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