Numerical Simulation of Reactive Flows in Overexpanded Supersonic Nozzle with Film Cooling
Reignition phenomena occurring in a supersonic nozzle flow may present a crucial safety issue for rocket propulsion systems. These phenomena concern mainly rocket engines which use H2 gas (GH2) in the film cooling device, particularly when the nozzle operates under over expanded flow conditions at s...
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| Format: | Article |
| Language: | English |
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Wiley
2015-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2015/252404 |
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| _version_ | 1849412089477595136 |
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| author | Mohamed Sellam Amer Chpoun |
| author_facet | Mohamed Sellam Amer Chpoun |
| author_sort | Mohamed Sellam |
| collection | DOAJ |
| description | Reignition phenomena occurring in a supersonic nozzle flow may present a crucial safety issue for rocket propulsion systems. These phenomena concern mainly rocket engines which use H2 gas (GH2) in the film cooling device, particularly when the nozzle operates under over expanded flow conditions at sea level or at low altitudes. Consequently, the induced wall thermal loads can lead to the nozzle geometry alteration, which in turn, leads to the appearance of strong side loads that may be detrimental to the rocket engine structural integrity. It is therefore necessary to understand both aerodynamic and chemical mechanisms that are at the origin of these processes. This paper is a numerical contribution which reports results from CFD analysis carried out for supersonic reactive flows in a planar nozzle cooled with GH2 film. Like the experimental observations, CFD simulations showed their ability to highlight these phenomena for the same nozzle flow conditions. Induced thermal load are also analyzed in terms of cooling efficiency and the results already give an idea on their magnitude. It was also shown that slightly increasing the film injection pressure can avoid the reignition phenomena by moving the separation shock towards the nozzle exit section. |
| format | Article |
| id | doaj-art-656643a7307f4c8fbdb3fe93c47ddb97 |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2015-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-656643a7307f4c8fbdb3fe93c47ddb972025-08-20T03:34:33ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742015-01-01201510.1155/2015/252404252404Numerical Simulation of Reactive Flows in Overexpanded Supersonic Nozzle with Film CoolingMohamed Sellam0Amer Chpoun1Laboratoire de Mécanique et d’Energétique d’Evry (LMEE), 40 rue du Pelvoux, 91020 Evry Cedex, FranceLaboratoire de Mécanique et d’Energétique d’Evry (LMEE), 40 rue du Pelvoux, 91020 Evry Cedex, FranceReignition phenomena occurring in a supersonic nozzle flow may present a crucial safety issue for rocket propulsion systems. These phenomena concern mainly rocket engines which use H2 gas (GH2) in the film cooling device, particularly when the nozzle operates under over expanded flow conditions at sea level or at low altitudes. Consequently, the induced wall thermal loads can lead to the nozzle geometry alteration, which in turn, leads to the appearance of strong side loads that may be detrimental to the rocket engine structural integrity. It is therefore necessary to understand both aerodynamic and chemical mechanisms that are at the origin of these processes. This paper is a numerical contribution which reports results from CFD analysis carried out for supersonic reactive flows in a planar nozzle cooled with GH2 film. Like the experimental observations, CFD simulations showed their ability to highlight these phenomena for the same nozzle flow conditions. Induced thermal load are also analyzed in terms of cooling efficiency and the results already give an idea on their magnitude. It was also shown that slightly increasing the film injection pressure can avoid the reignition phenomena by moving the separation shock towards the nozzle exit section.http://dx.doi.org/10.1155/2015/252404 |
| spellingShingle | Mohamed Sellam Amer Chpoun Numerical Simulation of Reactive Flows in Overexpanded Supersonic Nozzle with Film Cooling International Journal of Aerospace Engineering |
| title | Numerical Simulation of Reactive Flows in Overexpanded Supersonic Nozzle with Film Cooling |
| title_full | Numerical Simulation of Reactive Flows in Overexpanded Supersonic Nozzle with Film Cooling |
| title_fullStr | Numerical Simulation of Reactive Flows in Overexpanded Supersonic Nozzle with Film Cooling |
| title_full_unstemmed | Numerical Simulation of Reactive Flows in Overexpanded Supersonic Nozzle with Film Cooling |
| title_short | Numerical Simulation of Reactive Flows in Overexpanded Supersonic Nozzle with Film Cooling |
| title_sort | numerical simulation of reactive flows in overexpanded supersonic nozzle with film cooling |
| url | http://dx.doi.org/10.1155/2015/252404 |
| work_keys_str_mv | AT mohamedsellam numericalsimulationofreactiveflowsinoverexpandedsupersonicnozzlewithfilmcooling AT amerchpoun numericalsimulationofreactiveflowsinoverexpandedsupersonicnozzlewithfilmcooling |