Detonation Transition Around Cylindrical Reflector of Pulse Detonation Engine Initiator

Wakita, Masashi; Tamura, M.; Terasaka, Akihiro; Sajiki, Kazuya; Totani, Tsuyoshi; Nagata, Harunori

doi:10.2514/1.b34704

Cited by 3 publications

(2 citation statements)

References 18 publications

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“…Previous detonation experiments 5,6 showed that detonation waves tend to propagate as roughly planar waves that diffract at sharp external corners. Within the diffracted portion of the detonation wave, the combustion decouples from the pressure wave and transitions to deflagration.…”

Section: Introductionmentioning

confidence: 98%

Experimental Analogue of a Pre-Mixed Rotating Detonation Engine In Plane Flow

Andrus¹,

King²,

Fotia

et al. 2015

53rd AIAA Aerospace Sciences Meeting

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The mixing effects of fuel and oxidizer in the operation of non-premixed rotating detonation engines (RDE) are not well understood. This experiment explores feed systems for premixed RDE operation. A linear detonation test section was constructed that closely replicates the conditions of a proposed rotating detonation engine. Optically accessible walls facilitate velocity measurements as the detonation travels along a 0.038 cm (0.15 inch) x 15.2 cm (6.0 inch) x 61.0 cm (24 inch) channel. Pre-mixed hydrogen and air are injected into the channel from a mixing plenum with a series of 160 expansion nozzles featuring throat diameters of 0.43 mm (0.017 inches) or 1.04 mm (0.041 inches). Choked flame is only maintained across the field of view during the final test case. Emission of shock waves from a combustion zone are observed and linked to turbulent flow. Shock waves are not seen propagating back into the mixing plenum. Even in the absence of choked flame, six test events experienced flashback, indicating that a small nozzle throat diameter is insufficient to prevent flashback in a pre-mixed detonation engine. Nomenclature a = speed of sound, m/s d i = shock front location at time i-1/2, m f = video frame rate, s -1 h = height, m i = time index L p = pixel to meter conversion factor ṁ = mass flow rate, kg/s V i = Velocity of shock front at time i-1/2, m/s x i = horizontal pixel measurement, pixels  = mass fraction fuel to air equivalence ratio

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Section: Introductionmentioning

confidence: 98%

Experimental Analogue of a Pre-Mixed Rotating Detonation Engine In Plane Flow

Andrus¹,

King²,

Fotia

et al. 2015

53rd AIAA Aerospace Sciences Meeting

View full text Add to dashboard Cite

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“…More work could be invested into transitioning the detonation wave from the detonation tube into the test section. While the detonation inside of the tube is predominantly a planar wave, when it diffuses at the exit of the tube, it becomes more of a cylindrical detonation wave [85]. Rather than a simple expansion of the detonation tube into the combustion channel, shock shapers and other tricks could be used to match the shape and profile to be more similar to that of what propagates in the FSRDE.…”

Section: Chapter 7: Recommendations For Future Workmentioning

confidence: 99%

Experimental investigation for characterizing and improving inlet designs in rotating detonation engines

Sisler¹

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Rotating detonation engines (RDEs) present great potential for significant improvement in efficiency for land based power generation systems, in addition to aircraft propulsion devices. They offer the advantage of a net pressure gain across the combustor, as well as high exhaust temperatures and less entropy production due to detonative combustion. These improvements provide direct correlation to improved overall efficiency and thermal efficiency of gas turbine engines. RDEs surpass their conventional combustor counterparts in terms of their geometric size and simpler mechanical design. Among many areas of much needed research to further the technology readiness level (TRL) of RDEs, the inlet design is paramount to the successful operation of a rotating detonation engine. The inlet is one of the central impetuses behind current RDE research.

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