Search

A setup for studying the physicochemical properties of superheavy elements in experiments involving gas transport systems is described. The setup is composed of four detecting modules with semiconductor detectors; systems of data acquisition, storage, and processing; a cooling system for semiconductor detectors; and a vacuum system. In each detecting module, there are two oppositely located four-strip semiconductor detectors. The detecting system is capable of detecting with a high efficiency α particles and spontaneous fission fragments produced in decays of superheavy elements.

Summary form only given. Plasma assistance is a promising way for combustion improvement, especially for NOx reduction by burning leaner premixed hydrocarbons or for flame stabilization under unfavorable conditions (supersonic combustion or, small volume combustion where the chemical time is close to the fuel residence time). Thus, we conceived a combustion test bench where we could study the effect of a coaxial dielectric barrier discharge on a lifted non-premixed methane flame. For this study, we are especially interested in the effect of the discharge on the detachment height of the flame up to blow-out. There, we could achieve the anchoring of the flame (detachment height = 5-10 mm against 50-60 mm without plasma) on a plasma channel going out from the burner exit. Electrical investigations demonstrated that only 1 W applied to the discharge at the nozzle of the burner was necessary to this anchoring. Coupling electrical and optical measurements revealed the pulsed nature of the light emission of the plasma while spectroscopic study of OH, CH and N2* exhibits a 10 mm overlap between the plasma and the flame. Finally, fast camera movie of the flame anchoring zone was also achieved using narrow band filters for the selection of OH, CH and N2

The paper presents the results of the ducted combustion test program on the supersonic mixing and combustion enhancement in scramjet combustor using aerated by gas (hydrogen or air) liquid kerosene (effervescent) jets injected through elliptic nozzles from tube-micropylons and fin-pylons. Kerosene jets were injected into two-dimensional diverging-area supersonic combustor in two ways: 1) through nozzles in tube-micropyl ons at an angle of 45 degrees relative to the mainstream air flow direction and 2) through the nozzles located at the base of fin-pylons. In the latter case co-flow injection was used. Tests were conducted at entrance Mach number M=2.5 and total temperature in the range Tt=1650-1800K. The tests results with using elliptic nozzles were compared to baseline results with circular nozzles. The axial static pressure distributions on the combustor walls and calculated pressure-area integrals showed that the effervescent kerosene sprays performed better for elliptic nozzles than for round nozzles at injection from tubemicropylons. Injection from fin-pylons did not show noticeable difference in combustion efficiency for elliptic and round nozzles.