Time-Resolved PIV Measurements of Flow Field at the Exit of a Diffuser Mounted on a Rotating Detonation Combustor

Depperschmidt, Daniel; Tobias, Jonathan; Miller, Robert J.; Agrawal, Ajay K.

doi:10.2514/6.2019-4379

Cited by 6 publications

(1 citation statement)

References 11 publications

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“…The probe chosen here is a proprietary design of Vectoflow GmbH, and the manufacturer allows for an inflow angle variation of ±60 • and up to a Mach number of 2. For comparison, Depperschmidt et al [45] experimentally observed flow tilt angles just downstream of the exit of an RDC to vary between ±10 • , while in a numerical study Schwer et al [46] report flow angles close to the outlet throat (but still within the chamber) of −50 • to 23 • . Through a capillary tube similar to the one used in the CTAP probes, but with a standoff length of only 100 mm, a Kulite XTEL190 pressure transducer is attached to the Kiel probe.…”

Section: Instrumentationmentioning

confidence: 99%

Performance analysis of a rotating detonation combustor based on stagnation pressure measurements

Bach

Stathopoulos

Paschereit

et al. 2020

Combustion and Flame

105

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Section: Instrumentationmentioning

confidence: 99%

Performance analysis of a rotating detonation combustor based on stagnation pressure measurements

Bach

Stathopoulos

Paschereit

et al. 2020

Combustion and Flame

105

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Profiling cross-sectional area of a radial rotating detonation combustor to increase pressure gain

Bell

Schwer

Agrawal

2023

Aerospace Science and Technology

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Flow Development in Radial Plane of Rotating Detonation Engine Integrated with Aerospike

Tobias

Agrawal

2023

Journal of Propulsion and Power

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In this study, axial and radial velocity components are measured downstream of a rotating detonation engine (RDE) integrated with an aerospike by using particle image velocimetry (PIV) at 100 kHz. The RDE is operated at high pressures obtained by restricting the RDE exit with a converging nozzle, which also directs the flow radially toward the aerospike. Reactants, methane fuel, and enriched air (67% oxygen and 33% nitrogen) are supplied from separate plenums at ambient temperature. PIV data are presented to investigate how pressure ratios within the RDE channel affect the flow evolution across the aerospike. The RDE is shown to operate stably and consistently in a single wave mode for all six test runs. The study highlights large temporal and spatial variations in both axial and radial flow velocities at the nozzle throat that persist downstream across the aerospike. Each point in the flowfield oscillates at the frequency recorded inside the RDE channel. Overall, the temporally and spatially varying aerospike flowfield is far from the ideal case of a uniform flow at its exit, and it points toward the need to condition the flow within the RDE channel to produce more uniform conditions at the nozzle throat.

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Time-Resolved PIV Measurements of Flow Field at the Exit of a Diffuser Mounted on a Rotating Detonation Combustor

Cited by 6 publications

References 11 publications

Performance analysis of a rotating detonation combustor based on stagnation pressure measurements

Performance analysis of a rotating detonation combustor based on stagnation pressure measurements

Profiling cross-sectional area of a radial rotating detonation combustor to increase pressure gain

Flow Development in Radial Plane of Rotating Detonation Engine Integrated with Aerospike

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