Hydrogen fueled detonation ramjet: Conceptual design and test fires at Mach 1.5 and 2.0

Иванов, В. С.; Фролов, С. М.; Zangiev, A. E.; Звегинцев, В. И.; Шамшин, И. О.

doi:10.1016/j.ast.2020.106459

Cited by 23 publications

(12 citation statements)

References 26 publications

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“…As a basis for the conceptual design of the DR, we used the design of hydrogen-fueled dual-duct DR demonstrator developed, manufactured, and tested in [31,32] (Figure 12b) for the cruising flight speed of Mach 2 at sea level. The test fires in [31,32] were performed in a pulsed WT at approaching air stream Mach numbers M = 2 and 1.5. The most important result of the test fires was the experimental proof of the possibility of arranging steady-state continuous detonation of hydrogen in the DR at on-design (M = 2) and off-design (M = 1.5) flight speeds.…”

Section: Conceptual Designmentioning

confidence: 99%

“…Also, the startup Mach number of the DR was proved to be at the level of M = 1.5. Figure 12b,c compare the design proposed in [31,32] and the modified design of an ethylene/pyrogas DR demonstrator. In both cases, the DR demonstrator contains a center body with a front cone, rear cone, and the intake with the flow splitter.…”

Section: Conceptual Designmentioning

confidence: 99%

“…In [31,32], the possibility of hydrogen-fueled DR operation at an approaching air stream Mach number as low as M = 1.5 with the positive effective thrust was associated with a combination of two factors. The first is the use of a dual-duct flow path and the second is the arrangement of continuous detonation rather than deflagration of fuel-air mixture.…”

Section: Conceptual Designmentioning

confidence: 99%

“…As compared to the DR design of [31,32], the DR demonstrator of the modified design possesses several basic modifications: (i) The gasdynamic isolator is extended upstream; (ii) The ratio of cross-sections of the combustor and bypass channel is decreased; (iii) Following [10], fuel is supplied to the combustor from the internal rather than external wall; and (iv) The supporting pylons are shifted farer away from the combustor to avoid their influence on the operation process.…”

Section: Conceptual Designmentioning

confidence: 99%

“…The preliminary test fires of the DR of the modified design are performed in the same pulsed WT as in [31,32]. The volume and the maximum air pressure in the WT receiver are 10.4 m 3 and 1.6 MPa, respectively.…”

Section: Preliminary Test Firesmentioning

confidence: 99%

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Polyethylene Pyrolysis Products: Their Detonability in Air and Applicability to Solid-Fuel Detonation Ramjets

et al. 2021

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The detonability of polyethylene pyrolysis products (pyrogas) in mixtures with air is determined for the first time in a standard pulsed detonation tube based on the measured values of deflagration-to-detonation transition run-up time. The pyrogas is continuously produced in a gas generator at decomposition temperatures ranging from 650 to 850 °C. Chromatographic analysis shows that at a high decomposition temperature (850 °C) pyrogas consists mainly of hydrogen, methane, ethylene, and ethane, and has a molecular mass of about 10 g/mol, whereas at a low decomposition temperature (650 °C), it mainly consists of ethylene, ethane, methane, hydrogen, propane, and higher hydrocarbons, and has a molecular mass of 24–27 g/mol. In a pulsed detonation mode, the air mixtures of pyrogas with the fuel-to-air equivalence ratio ranging from 0.6 to 1.6 at normal pressure are shown to exhibit the detonability close to that of the homogeneous air mixtures of ethylene and propylene. On the one hand, this indicates a high explosion hazard of pyrogas, which can be formed, e.g., in industrial and household fires. On the other hand, pyrogas can be considered as a promising fuel for advanced propulsion powerplants utilizing the thermodynamic Zel’dovich cycle with detonative combustion, e.g., solid-fuel detonation ramjets. In view of it, the novel conceptual design of the dual-duct detonation ramjet demonstrator intended for operation on pyrogas at the cruising flight speed of Mach 2 at sea level has been developed. The ramjet demonstrator has been manufactured and preliminarily tested in a pulsed wind tunnel at Mach 1.5 and 2 conditions. In the test fires, a short-term onset of continuous detonation of ethylene was registered at both Mach numbers.

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