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Characteristic timescales for detonation-based rocket propulsion systems.

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Title: Characteristic timescales for detonation-based rocket propulsion systems.
Authors: Dave, R. T.1 (AUTHOR), Burr, J. R.2 (AUTHOR), Ross, M. C.2 (AUTHOR), Lietz, C. F.2 (AUTHOR), Bennewitz, J. W.1 (AUTHOR) john.bennewitz@uah.edu
Source: Shock Waves. Apr2024, Vol. 34 Issue 2, p193-214. 22p.
Subjects: Propulsion systems, Rockets (Aeronautics), Acoustic resonance, Rocket engines, Detonation waves, Combustion kinetics, Blast effect, Stiffness (Mechanics)
Abstract: Characteristic timescales for rotating detonation rocket engines (RDREs) are described in this study. Traveling detonations within RDREs create a complex reacting flow field involving processes spanning a range of timescales. Specifically, characteristic times associated with combustion kinetics (detonation and deflagration), injection (e.g., flow recovery), flow (e.g., mixture residence time), and acoustic modes are quantified using first-principle analyses to characterize the RDRE-relevant physics. Three fuels are investigated including methane, hydrogen, and rocket-grade kerosene RP-2 for equivalence ratios from 0.25 to 3 and chamber pressures from 0.51 to 10.13 MPa, as well as for a case study with a standard RDRE geometry. Detonation chemical timescales range from 0.05 to 1000 ns for the induction and reaction times; detonation-based chemical equilibrium, however, spans a larger range from approximately 0.5 to 200 μ s for the flow condition and fuel. This timescale sensitivity has implications regarding maximizing detonative heat release, especially with pre-detonation deflagration in real systems. Representative synthetic detonation wave profiles are input into a simplified injector model that describes the periodic choking/unchoking process and shows that injection timescales typically range from 5 to 50 μ s depending on injector stiffness; for detonations and low-stiffness injectors, target reactant flow rates may not recover prior to the next wave arrival, preventing uniform mixing. This partially explains the detonation velocity deficit observed in RDREs, as with the standard RDRE analyzed in this study. Finally, timescales tied to chamber geometry including residence time are on the order of 100–10,000 μ s and acoustic resonance times are 10– 1000 μ s. Overall, this work establishes characteristic time and length scales for the relevant physics, a valuable step in developing tools to optimize future RDRE designs. [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.)
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DbLabel: Engineering Source
An: 178353638
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PubType: Academic Journal
PubTypeId: academicJournal
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  Data: Characteristic timescales for detonation-based rocket propulsion systems.
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  Data: <searchLink fieldCode="AR" term="%22Dave%2C+R%2E+T%2E%22">Dave, R. T.</searchLink><relatesTo>1</relatesTo> (AUTHOR)<br /><searchLink fieldCode="AR" term="%22Burr%2C+J%2E+R%2E%22">Burr, J. R.</searchLink><relatesTo>2</relatesTo> (AUTHOR)<br /><searchLink fieldCode="AR" term="%22Ross%2C+M%2E+C%2E%22">Ross, M. C.</searchLink><relatesTo>2</relatesTo> (AUTHOR)<br /><searchLink fieldCode="AR" term="%22Lietz%2C+C%2E+F%2E%22">Lietz, C. F.</searchLink><relatesTo>2</relatesTo> (AUTHOR)<br /><searchLink fieldCode="AR" term="%22Bennewitz%2C+J%2E+W%2E%22">Bennewitz, J. W.</searchLink><relatesTo>1</relatesTo> (AUTHOR)<i> john.bennewitz@uah.edu</i>
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  Data: <searchLink fieldCode="JN" term="%22Shock+Waves%22">Shock Waves</searchLink>. Apr2024, Vol. 34 Issue 2, p193-214. 22p.
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  Data: <searchLink fieldCode="DE" term="%22Propulsion+systems%22">Propulsion systems</searchLink><br /><searchLink fieldCode="DE" term="%22Rockets+%28Aeronautics%29%22">Rockets (Aeronautics)</searchLink><br /><searchLink fieldCode="DE" term="%22Acoustic+resonance%22">Acoustic resonance</searchLink><br /><searchLink fieldCode="DE" term="%22Rocket+engines%22">Rocket engines</searchLink><br /><searchLink fieldCode="DE" term="%22Detonation+waves%22">Detonation waves</searchLink><br /><searchLink fieldCode="DE" term="%22Combustion+kinetics%22">Combustion kinetics</searchLink><br /><searchLink fieldCode="DE" term="%22Blast+effect%22">Blast effect</searchLink><br /><searchLink fieldCode="DE" term="%22Stiffness+%28Mechanics%29%22">Stiffness (Mechanics)</searchLink>
– Name: Abstract
  Label: Abstract
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  Data: Characteristic timescales for rotating detonation rocket engines (RDREs) are described in this study. Traveling detonations within RDREs create a complex reacting flow field involving processes spanning a range of timescales. Specifically, characteristic times associated with combustion kinetics (detonation and deflagration), injection (e.g., flow recovery), flow (e.g., mixture residence time), and acoustic modes are quantified using first-principle analyses to characterize the RDRE-relevant physics. Three fuels are investigated including methane, hydrogen, and rocket-grade kerosene RP-2 for equivalence ratios from 0.25 to 3 and chamber pressures from 0.51 to 10.13 MPa, as well as for a case study with a standard RDRE geometry. Detonation chemical timescales range from 0.05 to 1000 ns for the induction and reaction times; detonation-based chemical equilibrium, however, spans a larger range from approximately 0.5 to 200 μ s for the flow condition and fuel. This timescale sensitivity has implications regarding maximizing detonative heat release, especially with pre-detonation deflagration in real systems. Representative synthetic detonation wave profiles are input into a simplified injector model that describes the periodic choking/unchoking process and shows that injection timescales typically range from 5 to 50 μ s depending on injector stiffness; for detonations and low-stiffness injectors, target reactant flow rates may not recover prior to the next wave arrival, preventing uniform mixing. This partially explains the detonation velocity deficit observed in RDREs, as with the standard RDRE analyzed in this study. Finally, timescales tied to chamber geometry including residence time are on the order of 100–10,000 μ s and acoustic resonance times are 10– 1000 μ s. Overall, this work establishes characteristic time and length scales for the relevant physics, a valuable step in developing tools to optimize future RDRE designs. [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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        Value: 10.1007/s00193-024-01174-5
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      – Code: eng
        Text: English
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      Pagination:
        PageCount: 22
        StartPage: 193
    Subjects:
      – SubjectFull: Propulsion systems
        Type: general
      – SubjectFull: Rockets (Aeronautics)
        Type: general
      – SubjectFull: Acoustic resonance
        Type: general
      – SubjectFull: Rocket engines
        Type: general
      – SubjectFull: Detonation waves
        Type: general
      – SubjectFull: Combustion kinetics
        Type: general
      – SubjectFull: Blast effect
        Type: general
      – SubjectFull: Stiffness (Mechanics)
        Type: general
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      – TitleFull: Characteristic timescales for detonation-based rocket propulsion systems.
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              Text: Apr2024
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              Y: 2024
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