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

摘要

The conceptual design of a hydrogen-fueled detonation ramjet (DR) of a new type for a cruising flight speed of Mach 2 at sea level is developed using multivariant three-dimensional (3D) numerical simulations of the operation process. The possibility of arranging the continuous-detonation (rotating or longitudinally pulsating) combustion of hydrogen in an expanding annular combustor of the DR is proved for the first time. 3D numerical simulations of the operation process in the DR for flight conditions with a Mach number M ranging from 1.1 to 2.7 are performed. The calculated effective thrust of such a DR is shown to become positive at M = 1.3, i.e., the startup Mach number for such a DR can be lower than M = 2.0, which is typical for ramjets operating on continuous-deflagration combustion. A DR demonstrator is designed and manufactured. Its test fires are performed in a pulsed wind tunnel (WT) at free air jet Mach numbers M = 2.0 and M = 1.5. The most important result of test fires is the experimental proof of the possibility of arranging stable continuous-detonation combustion of hydrogen in the DR of the developed design at both Mach numbers. (c) 2020 Elsevier Masson SAS. All rights reserved.