Flow acceleration in an RDRE with gradual chamber constriction.
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| Title: | Flow acceleration in an RDRE with gradual chamber constriction. |
|---|---|
| Authors: | Ross, M.1 (AUTHOR) rossmathiasc@ucla.edu, Burr, J.2,3 (AUTHOR), Desai, Y.4 (AUTHOR), Batista, A.2,5 (AUTHOR), Lietz, C.2 (AUTHOR) |
| Source: | Shock Waves. Apr2023, Vol. 33 Issue 3, p253-265. 13p. |
| Subjects: | Air Force Research Laboratory (Edwards Air Force Base, Calif.), Heat of formation, Combustion chambers, Supersonic flow, Rocket engines, Large eddy simulation models, Thermochemistry, Combustion, Transonic flow |
| Abstract: | Rotating detonation propulsion technologies have the potential to create highly efficient engines in a small form factor. However, the detonation dynamics and complex flowfields inside the combustion chamber are greatly dependent on geometry; in particular, the downstream nozzle design affects dynamics inside the combustion chamber. In this work, three-dimensional large eddy simulations of a gaseous methane–oxygen rotating detonation rocket engine are presented for two geometries. The geometries match experimental tests previously conducted at the Air Force Research Laboratory and are chosen to compare engine operation with and without a converging–diverging nozzle. It is shown that flow in the unconstricted chamber exceeds Mach 1 behind the generated oblique shock structure, but that the addition of a 4.4 ∘ converging section results in supersonic flow existing only in the diverging section of the nozzle. The formation enthalpy of the flow is calculated inside the chamber and demonstrates that the difference in pressures and detonation structures associated with the chamber area constriction do not result in a significant change in energy released through combustion. [ABSTRACT FROM AUTHOR] |
| Copyright of Shock Waves is the property of Springer Nature and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.) | |
| Database: | Engineering Source |
| FullText | Text: Availability: 0 |
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| Header | DbId: egs DbLabel: Engineering Source An: 164552232 AccessLevel: 6 PubType: Academic Journal PubTypeId: academicJournal PreciseRelevancyScore: 0 |
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| Items | – Name: Title Label: Title Group: Ti Data: Flow acceleration in an RDRE with gradual chamber constriction. – Name: Author Label: Authors Group: Au Data: <searchLink fieldCode="AR" term="%22Ross%2C+M%2E%22">Ross, M.</searchLink><relatesTo>1</relatesTo> (AUTHOR)<i> rossmathiasc@ucla.edu</i><br /><searchLink fieldCode="AR" term="%22Burr%2C+J%2E%22">Burr, J.</searchLink><relatesTo>2,3</relatesTo> (AUTHOR)<br /><searchLink fieldCode="AR" term="%22Desai%2C+Y%2E%22">Desai, Y.</searchLink><relatesTo>4</relatesTo> (AUTHOR)<br /><searchLink fieldCode="AR" term="%22Batista%2C+A%2E%22">Batista, A.</searchLink><relatesTo>2,5</relatesTo> (AUTHOR)<br /><searchLink fieldCode="AR" term="%22Lietz%2C+C%2E%22">Lietz, C.</searchLink><relatesTo>2</relatesTo> (AUTHOR) – Name: TitleSource Label: Source Group: Src Data: <searchLink fieldCode="JN" term="%22Shock+Waves%22">Shock Waves</searchLink>. Apr2023, Vol. 33 Issue 3, p253-265. 13p. – Name: Subject Label: Subjects Group: Su Data: <searchLink fieldCode="DE" term="%22Air+Force+Research+Laboratory+%28Edwards+Air+Force+Base%2C+Calif%2E%29%22">Air Force Research Laboratory (Edwards Air Force Base, Calif.)</searchLink><br /><searchLink fieldCode="DE" term="%22Heat+of+formation%22">Heat of formation</searchLink><br /><searchLink fieldCode="DE" term="%22Combustion+chambers%22">Combustion chambers</searchLink><br /><searchLink fieldCode="DE" term="%22Supersonic+flow%22">Supersonic flow</searchLink><br /><searchLink fieldCode="DE" term="%22Rocket+engines%22">Rocket engines</searchLink><br /><searchLink fieldCode="DE" term="%22Large+eddy+simulation+models%22">Large eddy simulation models</searchLink><br /><searchLink fieldCode="DE" term="%22Thermochemistry%22">Thermochemistry</searchLink><br /><searchLink fieldCode="DE" term="%22Combustion%22">Combustion</searchLink><br /><searchLink fieldCode="DE" term="%22Transonic+flow%22">Transonic flow</searchLink> – Name: Abstract Label: Abstract Group: Ab Data: Rotating detonation propulsion technologies have the potential to create highly efficient engines in a small form factor. However, the detonation dynamics and complex flowfields inside the combustion chamber are greatly dependent on geometry; in particular, the downstream nozzle design affects dynamics inside the combustion chamber. In this work, three-dimensional large eddy simulations of a gaseous methane–oxygen rotating detonation rocket engine are presented for two geometries. The geometries match experimental tests previously conducted at the Air Force Research Laboratory and are chosen to compare engine operation with and without a converging–diverging nozzle. It is shown that flow in the unconstricted chamber exceeds Mach 1 behind the generated oblique shock structure, but that the addition of a 4.4 ∘ converging section results in supersonic flow existing only in the diverging section of the nozzle. The formation enthalpy of the flow is calculated inside the chamber and demonstrates that the difference in pressures and detonation structures associated with the chamber area constriction do not result in a significant change in energy released through combustion. [ABSTRACT FROM AUTHOR] – Name: AbstractSuppliedCopyright Label: Group: Ab Data: <i>Copyright of Shock Waves is the property of Springer Nature and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.) |
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| RecordInfo | BibRecord: BibEntity: Identifiers: – Type: doi Value: 10.1007/s00193-022-01117-y Languages: – Code: eng Text: English PhysicalDescription: Pagination: PageCount: 13 StartPage: 253 Subjects: – SubjectFull: Air Force Research Laboratory (Edwards Air Force Base, Calif.) Type: general – SubjectFull: Heat of formation Type: general – SubjectFull: Combustion chambers Type: general – SubjectFull: Supersonic flow Type: general – SubjectFull: Rocket engines Type: general – SubjectFull: Large eddy simulation models Type: general – SubjectFull: Thermochemistry Type: general – SubjectFull: Combustion Type: general – SubjectFull: Transonic flow Type: general Titles: – TitleFull: Flow acceleration in an RDRE with gradual chamber constriction. Type: main BibRelationships: HasContributorRelationships: – PersonEntity: Name: NameFull: Ross, M. – PersonEntity: Name: NameFull: Burr, J. – PersonEntity: Name: NameFull: Desai, Y. – PersonEntity: Name: NameFull: Batista, A. – PersonEntity: Name: NameFull: Lietz, C. IsPartOfRelationships: – BibEntity: Dates: – D: 01 M: 04 Text: Apr2023 Type: published Y: 2023 Identifiers: – Type: issn-print Value: 09381287 Numbering: – Type: volume Value: 33 – Type: issue Value: 3 Titles: – TitleFull: Shock Waves Type: main |
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