Review on the Recent Development of Multi-mode Combined Detonation Engine

Abstract

In the next few decades, the development of hypersonic aircrafts will be the priority of national defense strategy of many countries, and the significance of the propulsion system applied on the aircraft is self-evident. Hypersonic aircrafts require propulsion devices that can be used independently in a wide range of Mach numbers and flight envelop, however, there have been no such propulsion systems up to now. The multi-mode combined detonation engine, which consists of four modes, is a novel propulsion concept proposed at the beginning of this century for potential application on hypersonic cruise or space access. The multi-mode combined detonation engine is a promising propulsion system which can be used independently in a wide range of Mach numbers and flight envelop. Recently, many countries attach much importance to the research of multi-mode combined detonation engine and great progress has been achieved. This paper attempts to provide an overview of the recent advances in the multi-mode combined detonation engine, and the major progress for each mode is detailed introduced. Nevertheless, there is still a need to pay more attention to the existing problems in the future.

An effectiveness analysis of the pulsed resonant fuel combustion in the processes of steel­casting ladle drying and warming

“…Given this, using the pulsed fuel combustion is of interest [9], including mechanical engineering [10][11][12] and rocket engineering [13], which could significantly reduce the fuel underburning and increase the intensity of heat output from combustion products, which indicates the prospects and demand for a given direction. However, all the studies carried out do not concern the drying and warming of steel-casting ladles.…”

“…is the content (shares of units) of combustible components (the multipliers correspond to the combustion heat of combustion components); 9) the losses of heat due to the heat transmission through the lining of a ladle (through a working layer, reinforcement row, thermal insulation, and casing): (11) where δ і is the thickness of the corresponding i-th layer of the lining, m; λ і is the thermal conductivity factor of a material of the i-th layer of the ladle lining at an average temperature per cycle of drying or warming, W/m•K; α os is the heat output ratio from the outer surface of the ladle casing, W/m 2 •K; c sur t is the average, per cycle of drying or warming, the surface temperature of the ladle casing, °C; t ama is the temperature of the ambient air, °C; F is the average value of the area of the surface of the ladle lining (between the inner and outer surfaces), m 2 ; τ is the cycle duration of ladle drying or warming, h; 10) the losses of heat due to the heat transfer through the cover:…”

“…4). These losses are determined from the difference between the heat input Q com (1) and the sum of heat consumption Q w (2), Q r (3), Q in (4), Q cas (5), Q out (9), Q ch (10) and Q htll (11).…”

Review on Recent Advances in Pulse Detonation Engines

“…They conducted a study to investigate the thrust, fuel flow, air flow, and temperature over the range of operating conditions. Recently many countries give much importance to research of multimode combined detonation engine in hypersonic aircrafts propulsion system [4]. Kailasanath [5] studied a review on practical implementation on pulse detonation engine and deflagration to detonation transition was also studied in obstacle geometry.…”