Pulse detonation engine air induction system analysis

Pegg, R. J.; Hunter, L.; Couch, B D

doi:10.2514/6.1996-2918

Cited by 25 publications

(10 citation statements)

References 2 publications

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“…There is concern of unstart in a Mach 5 inlet although careful design appears to be able to address this. 38 Experimental studies at Mach 2.1-2.5 appear to confirm that the flow oscillation did not unstart the inlet. 39,40 On the exhaust end, there is concern on the structural integrity of turbine blades due to the repeated impingement of high-pressure waves, as well as on the performance of nozzles in a fluctuating flow.…”

Section: Introductionmentioning

confidence: 88%

Rotating Detonation Wave Propulsion: Experimental Challenges, Modeling, and Engine Concepts

Braun

Massa³

et al. 2014

Journal of Propulsion and Power

490

117

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Rotating detonation engines (RDEs), also known as continuous detonation engines, have gained much worldwide interest lately. Such engines have huge potential benefits arising from their simplicity of design and manufacture, lack of moving parts, high thermodynamic efficiency and high rate of energy conversion that may be even more superior than pulse detonation engines, themselves the subject of great interest. However, due to the novelty of the concept, substantial work remains to demonstrate feasibility and bring the RDE to reality. An assessment of the challenges, ranging from understanding basic physics through utilizing rotating detonations in aerospace platforms, is provided.

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Section: Introductionmentioning

confidence: 88%

Rotating Detonation Wave Propulsion: Experimental Challenges, Modeling, and Engine Concepts

Braun

Massa³

et al. 2014

Journal of Propulsion and Power

490

117

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“…Those studies claim that in order for the PDE cycle to be competitive with conventional turbojet/turboramjet systems, they will be required to operate in the 75-100 Hz range with near stoichiometric fuel-air mixtures. It is expected that for power production the range need not be the same but similar to that for propulsion [16].…”

Section: Frequencymentioning

confidence: 99%

Exergy Analysis of a Hybrid Pulse Detonation Power Device

Bellini

2010

Journal of Propulsion and Power

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“…This variant is currently thought to be useful for space launch only up to about Mach 4 or so, given increases in the total temperature of the captured airstream at high velocities. Pegg and his colleagues have shown that airbreathing PDEs have potential application as the low speed cycle of an airbreathing space access vehicle 11 .…”

Section: Pulsed Detona Tion Enginesmentioning

confidence: 99%

An evaluation of two alternate propulsion concepts for Bantam-Argus - Deeply-cooled turbojet + rocket and pulsed detonation rocket + ramjet

Germain

Olds

1999

35th Joint Propulsion Conference and Exhibit

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The Bantam-Argus reusable launch vehicle concept is a smaller version of the original Argus single-stage-to-orbit launch vehicle design. Like the original Argus, Bantam-Argus uses a Maglifter launch assist system to provide an initial horizontal launch velocity. Bantam-Argus is designed to deliver 300 lb. payloads to low earth orbit and, like the full sized Argus, the baseline Bantam-Argus concept utilizes two liquid oxygen/liquid hydrogen supercharged ejector ramjets as prime motive power. This paper presents the results of an investigation of two alternate propulsion systems for the Bantam-Argus launch vehicle. First, a thermally integrated combined-cycle system consisting of two deeplycooled turbojets and two liquid rocket engines was evaluated. Second, a combination propulsion system utilizing two pulsed detonation rocket engines and two standalone ramjets was evaluated.

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Pulse detonation engine air induction system analysis

Cited by 25 publications

References 2 publications

Rotating Detonation Wave Propulsion: Experimental Challenges, Modeling, and Engine Concepts

Rotating Detonation Wave Propulsion: Experimental Challenges, Modeling, and Engine Concepts

Exergy Analysis of a Hybrid Pulse Detonation Power Device

An evaluation of two alternate propulsion concepts for Bantam-Argus - Deeply-cooled turbojet + rocket and pulsed detonation rocket + ramjet

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