Influence of Flow Rate Distribution on Combustion Instability of Hypergolic Propellant
Combustion instability is the biggest threat to the reliability of liquid rocket engines, whose prediction and suppression are of great significance for engineering applications. To predict the stability of a combustion chamber with a hypergolic propellant, this work used the method of decoupling un...
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| Format: | Article |
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MDPI AG
2022-09-01
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| Series: | Aerospace |
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| Online Access: | https://www.mdpi.com/2226-4310/9/10/543 |
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| author | Yushan Gao Bingbing Zhang Jinbo Cheng Jingxuan Li Qingfei Fu |
| author_facet | Yushan Gao Bingbing Zhang Jinbo Cheng Jingxuan Li Qingfei Fu |
| author_sort | Yushan Gao |
| collection | DOAJ |
| description | Combustion instability is the biggest threat to the reliability of liquid rocket engines, whose prediction and suppression are of great significance for engineering applications. To predict the stability of a combustion chamber with a hypergolic propellant, this work used the method of decoupling unsteady combustion and acoustic system. The turbulence is described by the Reynolds-averaged Navier–Stokes technique, and the interaction of turbulence and chemistry interaction is described by the eddy-dissipation model. By extracting the flame transfer function of the combustion field, the eigenvalues of each acoustic mode were obtained by solving the Helmholtz equation, thereby predicting the combustion stability for the combustion chamber. By predictions of the combustion chamber instability with different flow rate distributions, it was found that the increasing of inlet flow rate amplitude will improve the stability or instability of combustion. The combustion stability of the chamber was optimized when the flow rate distribution for the oxidant was set more uniform in the radial direction. The heterogeneity of the flow rate distribution in the circumferential direction is not recommended, considering that a homogeneous flow rate distribution in the circumferential direction is beneficial to the combustion stability of the chamber. |
| first_indexed | 2024-03-09T20:57:48Z |
| format | Article |
| id | doaj.art-cc82615c006047e5beef067e0b395e02 |
| institution | Directory Open Access Journal |
| issn | 2226-4310 |
| language | English |
| last_indexed | 2024-03-09T20:57:48Z |
| publishDate | 2022-09-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj.art-cc82615c006047e5beef067e0b395e022023-11-23T22:18:04ZengMDPI AGAerospace2226-43102022-09-0191054310.3390/aerospace9100543Influence of Flow Rate Distribution on Combustion Instability of Hypergolic PropellantYushan Gao0Bingbing Zhang1Jinbo Cheng2Jingxuan Li3Qingfei Fu4Science and Technology on Liquid Rocket Engine Laboratory, Xi’an Aerospace Propulsion Institute, Xi’an 710100, ChinaSchool of Astronautics, Beihang University, Beijing 100191, ChinaSchool of Astronautics, Beihang University, Beijing 100191, ChinaSchool of Astronautics, Beihang University, Beijing 100191, ChinaSchool of Astronautics, Beihang University, Beijing 100191, ChinaCombustion instability is the biggest threat to the reliability of liquid rocket engines, whose prediction and suppression are of great significance for engineering applications. To predict the stability of a combustion chamber with a hypergolic propellant, this work used the method of decoupling unsteady combustion and acoustic system. The turbulence is described by the Reynolds-averaged Navier–Stokes technique, and the interaction of turbulence and chemistry interaction is described by the eddy-dissipation model. By extracting the flame transfer function of the combustion field, the eigenvalues of each acoustic mode were obtained by solving the Helmholtz equation, thereby predicting the combustion stability for the combustion chamber. By predictions of the combustion chamber instability with different flow rate distributions, it was found that the increasing of inlet flow rate amplitude will improve the stability or instability of combustion. The combustion stability of the chamber was optimized when the flow rate distribution for the oxidant was set more uniform in the radial direction. The heterogeneity of the flow rate distribution in the circumferential direction is not recommended, considering that a homogeneous flow rate distribution in the circumferential direction is beneficial to the combustion stability of the chamber.https://www.mdpi.com/2226-4310/9/10/543liquid rocket engineflow rate distributionthermoacoustic decouplingcombustion instability |
| spellingShingle | Yushan Gao Bingbing Zhang Jinbo Cheng Jingxuan Li Qingfei Fu Influence of Flow Rate Distribution on Combustion Instability of Hypergolic Propellant Aerospace liquid rocket engine flow rate distribution thermoacoustic decoupling combustion instability |
| title | Influence of Flow Rate Distribution on Combustion Instability of Hypergolic Propellant |
| title_full | Influence of Flow Rate Distribution on Combustion Instability of Hypergolic Propellant |
| title_fullStr | Influence of Flow Rate Distribution on Combustion Instability of Hypergolic Propellant |
| title_full_unstemmed | Influence of Flow Rate Distribution on Combustion Instability of Hypergolic Propellant |
| title_short | Influence of Flow Rate Distribution on Combustion Instability of Hypergolic Propellant |
| title_sort | influence of flow rate distribution on combustion instability of hypergolic propellant |
| topic | liquid rocket engine flow rate distribution thermoacoustic decoupling combustion instability |
| url | https://www.mdpi.com/2226-4310/9/10/543 |
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