大孔吸附树脂对大豆皂苷的吸附研究

比较了5种大孔吸附树脂对大豆皂苷的吸附等温线、吸附容量、解吸率和吸附动力学。发现ZTC-1树脂对大豆皂苷吸附量大、解吸容易、吸附速度快，是一种良好的大豆皂苷吸附荆，AB-8树脂次之．选择ZTC-l树脂纯化大豆皂苷粗提液，得到大豆皂苷产品纯度为78．2％(干物质)，回收率为93．1％．     

Flow visualization of interactions among large coherent structures in an axisymmetric jet

Interactions between large coherent structures are visualized with both schlieren photography in two air jets and dye photography in a water jet. The density difference needed for the schlieren technique is provided by an electrically heated wire ring surrounding the jet. External forcing with either single axisymmetric, single non-symmetric, combined axisymmetric or combined non-symmetric modes was applied. It was found that forcing the jet with a pair of different spinning modes leads to azimuthal distortions of the mean flow. This observation confirms and explains existing hotwire data. Simultaneous excitation with two axisymmetric modes may produce structures of higher modes or even cause structurally undistinguishable development. Streamwise structures are observed both in the unforced jet and in the axisymmetrically forced jet. They do not seem to be caused by a Görtier instability from the concave curvature of the conventional nozzle, since they were also found in a jet flow from a specially designed nozzle with only convex contraction surface.Supported in part by the National Science Foundation under Grant No. MSM 8900086 and by the Deutsche Forschungsgemeinschaft DFG, Fi178/34-1     

An empirical model for stagnation pressure gain in rotating detonation combustors

This work investigates the stagnation pressure gain in rotating detonation combustors (RDC) and its dependency on the geometry and mass flux of the combustor. Using a Kiel probe to directly measure stagnation pressure in the high-enthalpy exhaust stream, results are presented for a systematic variation of these parameters. The best-performing configuration achieved a pressure gain of ?8%. A comparison with thrust-based equivalent available pressure data from literature shows that the Kiel probe measurements are in good agreement. It is observed that pressure gain increases with increasing air injector area, decreasing outlet throat area, increasing combustor mass flux, and is seen to be dependent on the operating mode. The data are then used to obtain an empirical model that describes pressure gain as a function of the three variables of injector area ratio, outlet area ratio, and combustor mass flux. The model is compared with measurements in this combustor and others, and is used to predict the pressure gain boundaries and to assess design corridors that potentially achieve positive pressure gain.     

On the JWKB solution of the uniformly lengthening pendulum via change of independent variable in the Bessel’s equation

Common recipe for the lengthening pendulum (LP) involves some change of variables to give a relationship with the Bessel’s equation. In this work, conventional semiclassical JWKB solution (named after Jeffreys, Wentzel, Kramers and Brillouin) of the LP is being obtained by first transforming the related Bessel’s equation into the normal form ‘via the suggested change of independent variable’. JWKB approximation of the first-order Bessel functions (ν=1) of both types along with their zeros are being obtained analytically with a very good accuracy as a result of the appropriately chosen associated initial values and they are extended to the neighbouring orders (ν=0 and 2) by the recursion relations. The required initial values are also being studied and a quantization rule regarding the experimental LP parameters is being determined. Although common numerical methods given in the literature require adiabatic LP systems where the lengthening rate is slow, JWKB solution presented here can safely be used for higher lengthening rates and a criterion for its validity is determined by the JWKB applicability criterion given in the literature. As a result, the semiclassical JWKB method which is normally used for the quantum mechanical and optical waveguide systems is applied to the classical LP system successfully.     

Vortex-enhanced mixing through active and passive flow control methods

This study aims to understand the underlying physics of vortex-enhanced mixing through active and passive flow control methods. To find a best flow control method that enhances turbulent mixing through the generation of streamwise vortices, an experimental investigation was carried out to compare active and passive flow control methods of an incompressible axisymmetric jet. For active flow control, the lip of the circular jet was equipped with a single small flap deflected away from the jet stream at an angle of 30° to the jet axis. The flap incorporated a flow control slot through which steady and oscillatory suction were implemented. The active flow control methods require power input to the suction devices. For passive flow control, the lip of the circular jet was equipped with a single small delta tab deflected into the jet stream at an angle of 30° to the jet axis. The chord lengths of the flap and delta tab were one-sixth of the jet diameter. The momentum of jet increased in the case of active flow control by entraining the ambient fluid, whereas momentum decreased in the case of passive flow control. The effect of steady suction saturated for volumetric suction coefficient values greater than 0.82 %. The strength of streamwise vortices generated by the flap were greater than those generated by the delta tab. Steady suction produced positive pressures just downstream of the flow control slot in the central portion of the flap and negative pressures at the flap edges. Oscillatory suction was highly dependent on dimensionless frequency (F ⁺) based on the distance from the flow control slot to the flap trailing edge; the pressures on the central portion of the flap increased for F ⁺ ≤ 0.11 and then decreased for greater F ⁺; finally attained negative pressures at F ⁺ = 0.44. The increase in jet momentum and turbulence intensity, combined with the induced streamwise vorticity, makes steady suction a potential concept for increasing propulsion efficiency through vortex-enhanced mixing. The flow control methods modify the jet flow, which in turn would alter the jet noise spectra.     

Stabilization mechanisms of longitudinal pulsations in rotating detonation combustors

This work investigates the stabilization mechanisms of two types of longitudinal pulsations in rotating detonation combustors. The first type is linked to operating modes with two counter-rotating waves in combustors with open outlets and appears as a minor peak in the pressure spectrum. The second type is observed as pulsed operation of the combustor when the outlet is restricted. Different combustor lengths are studied and the susceptibility to these longitudinal pulsations is investigated. Pressure measurements along the length of the combustor and around the perimeter are used to identify the operating mode and to describe the propagation and stabilization mechanisms of the two longitudinal modes. The results show that both modes are linked to the longitudinal acoustic resonance of the combustor. The length-to-perimeter ratio and the mass flux are identified as the driving parameters for the existence of these longitudinal modes. The first mode is shown to be an acoustic resonance supported by the intersections of counter-rotating waves. The second mode is controlled by the reflection of an explosion induced shock wave propagating through a high velocity bulk flow.     

Autoignition in stratified mixtures for pressure gain combustion

The reliable generation of quasi-homogeneous autoignition inside a combustor fed by a continuous air flow would represent a milestone in realizing pressure gain combustion in gas turbines. In this work, the ignition distribution inside a stratified fuel–air mixture is analyzed. The ability of precise and reproducible injection of a desired fuel profile inside a convecting air flow is verified by applying tunable diode laser absorption spectroscopy in non-reacting measurements. High-speed, static pressure sensors and ionization probes allow for simultaneous detection of the flame and pressure rise at several axial positions in reactive measurements with dimethyl ether as fuel. A second, exchangeable combustion tube enables optical observation of OH* intensity in combination with pressure measurements. Experiments with three arbitrary fuel profiles show a set of ignition distributions that vary in shape, homogeneity, and the number of simultaneous autoignition events. Although the measurements show notable variation, a significant and reproducible influence of the fuel injection on the ignition distribution is observed. Results show that uniform autoignition leads to a coupling of the reaction front with the pressure rise and, therefore, induces a greater aerodynamic constraint than non-uniform ignition distributions, which are dominated by propagating deflagration fronts.     

Active control of combustion instability using fuel flow modulation

Phase-shift control was applied to an atmospheric premix combustor test rig equipped with a swirl-stabilized burner by modulating the pilot fuel flow. The employed closed loop control circuit incorporated condenser microphones recording the pressure oscillations inside the combustion chamber and valves controlling the fuel mass flow. The microphone signals were processed and command signals were sent to the valves. The rms of the pressure oscillations was reduced by up to 12 dB, the peak amplitude by up to 20 dB. (© 2008 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim)