Outflow Boundary Conditions for Turbine-Integrated Rotating Detonation Combustors Article Swipe
Tsung-Ming Hsieh
,
K. Mark Bryden
,
Richard P. Dalton
,
John Crane
,
Tom I-P. Shih
·
YOU?
·
· 2025
· Open Access
·
· DOI: https://doi.org/10.3390/app152211922
YOU?
·
· 2025
· Open Access
·
· DOI: https://doi.org/10.3390/app152211922
This study examines outflow boundary conditions (BCs) in computational fluid dynamics (CFD) simulations of a transition duct with and without guide vanes that converts supersonic flow exiting a rotating detonation combustor (RDC) to subsonic flow to drive a turbine. Since the flow exiting the transition duct has swirling shock waves with significant spatial and temporal variations in pressure, temperature, and Mach number, imposing proper BCs poses a challenge. To ensure all swirling shock waves exit the transition duct without creating non-physical reflected waves at its outlet, this study examined three outflow BCs: (1) the average pressure imposed at the duct’s outlet, (2) a nonreflecting BC (NRBC) with a specified average pressure imposed at the duct’s outlet, (3) the average pressure imposed at the outlet of an extension duct made up of a buffer layer and a sponge layer. This study is based on the three-dimensional, unsteady density-weighted-ensemble-averaged continuity, Navier–Stokes, and energy equations for a thermally perfect gas closed by the realizable k–ε model and “enhanced” wall functions. The results obtained show that imposing an average pressure at the transition duct’s outlet produces spurious waves that degrade the physical meaningfulness of the solution. When the NRBC was applied, swirling shock waves exited the duct’s outlet without creating spurious waves. However, its usage requires the gas to be thermally, as well as calorically, perfect, which this study shows could be a concern. By imposing the average pressure at the outlet of an extension duct, the gas does not need to be calorically perfect. The results obtained show the effects of the sponge layer’s length and coarsening ratio on damping nonuniformities in non-physical reflected waves to ensure the flow exiting the transition duct’s outlet can do so as if there are no boundaries present and has the desired average pressure—even though the BC is applied at the extension duct’s outlet.
Related Topics
Concepts
Mechanics
Duct (anatomy)
Outflow
Mach number
Shock wave
Supersonic speed
Physics
Detonation
Shock diamond
Boundary layer
Inflow
Combustor
Boundary value problem
Oblique shock
Static pressure
Spurious relationship
Stagnation enthalpy
Isentropic process
Shock (circulatory)
Wake
Mach wave
Moving shock
Choked flow
Overall pressure ratio
Classical mechanics
Dynamic pressure
Compressible flow
Flow (mathematics)
Geology
Materials science
Rotational symmetry
Heat capacity ratio
Total pressure
Meteorology
Stagnation temperature
Computational fluid dynamics
Metadata
- Type
- article
- Language
- en
- Landing Page
- https://doi.org/10.3390/app152211922
- https://www.mdpi.com/2076-3417/15/22/11922/pdf?version=1762755345
- OA Status
- gold
- References
- 36
- OpenAlex ID
- https://openalex.org/W7104512636
All OpenAlex metadata
Raw OpenAlex JSON
- OpenAlex ID
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https://openalex.org/W7104512636Canonical identifier for this work in OpenAlex
- DOI
-
https://doi.org/10.3390/app152211922Digital Object Identifier
- Title
-
Outflow Boundary Conditions for Turbine-Integrated Rotating Detonation CombustorsWork title
- Type
-
articleOpenAlex work type
- Language
-
enPrimary language
- Publication year
-
2025Year of publication
- Publication date
-
2025-11-10Full publication date if available
- Authors
-
Tsung-Ming Hsieh, K. Mark Bryden, Richard P. Dalton, John Crane, Tom I-P. ShihList of authors in order
- Landing page
-
https://doi.org/10.3390/app152211922Publisher landing page
- PDF URL
-
https://www.mdpi.com/2076-3417/15/22/11922/pdf?version=1762755345Direct link to full text PDF
- Open access
-
YesWhether a free full text is available
- OA status
-
goldOpen access status per OpenAlex
- OA URL
-
https://www.mdpi.com/2076-3417/15/22/11922/pdf?version=1762755345Direct OA link when available
- Concepts
-
Mechanics, Duct (anatomy), Outflow, Mach number, Shock wave, Supersonic speed, Physics, Detonation, Shock diamond, Boundary layer, Inflow, Combustor, Boundary value problem, Oblique shock, Static pressure, Spurious relationship, Stagnation enthalpy, Isentropic process, Shock (circulatory), Wake, Mach wave, Moving shock, Choked flow, Overall pressure ratio, Classical mechanics, Dynamic pressure, Compressible flow, Flow (mathematics), Geology, Materials science, Rotational symmetry, Heat capacity ratio, Total pressure, Meteorology, Stagnation temperature, Computational fluid dynamicsTop concepts (fields/topics) attached by OpenAlex
- Cited by
-
0Total citation count in OpenAlex
- References (count)
-
36Number of works referenced by this work
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