中温固体氧化物燃料电池的基本性质测量

介绍了固体氧化物燃料电池的工作原理,测量了中温薄膜固体氧化物燃料电池的开路电压、放电曲线及功率曲线,并分析了电池内阻随电流密度的变化.     

Performance characteristics of composite film electrolytes for intermediate-temperature solid oxide fuel cells

This paper reports on the estimated performance of a cell with a three-layer electrolyte, consisting of one gadolinia-doped ceria (GDC) layer, one yttria-stabilised zirconia (YSZ) electronblocking layer and one CGO-YSZ solid solution interlayer, the latter being used to avoid solid-state reaction and interdiffusion between YSZ and GDC, in comparison to a cell with a double-layer YSZ-CGO composite electrolyte. For a constant temperature and overall cell oxygen potential as boundary conditions, the open circuit voltage, the voltage under operating conditions and the oxygen potential profile inside the electrolyte are related to the ionic and electronic transport properties of the materials involved and are calculated as a function of the thickness of the layers involved and the relative positions of the YSZ and GDC layers. Thermodynamic stability of the electrolyte is shown to depend upon the transport properties of the materials and primarily the electronic conductivity of the air-side layers. To determine the particular ionic and electronic contributions for conduction of the materials involved, conductivity was measured as a function of the oxygen partial pressure and temperature, using the standard four point d.c. method. Based on the calculations, performed the conditions are discussed under which a functionally graded composite electrolyte YSZ-CGO can be effective for intermediate-temperature solid oxide fuel cells (SOFCs). Paper presented at the 6th Euroconference on Solid State Ionics, Cetraro, Calabria, Italy, Sept. 12–19, 1999. TMR Grant Holder     

无工质微波推力器推力测量实验

基于经典的电磁学理论, 本文建立了一套新概念空间推进装置-----无工质微波推力器系统, 这套装置可以直接把微波辐射能转换为推力而不需要任何推进介质. 与传统的空间推进装置不同, 该系统可以避免携带庞大的推进剂储箱并消除羽流对航天飞行器的污染. 该系统由集成在一起的圆台微波谐振腔、 微波源和负载组成, 其中微波源产生的微波辐射能被输入到圆台微波谐振腔内并形成纯驻波与电磁压强梯度, 从而沿圆台微波谐振腔轴线方向形成净推力. 本文根据随遇平衡原理, 通过克服推力器本身的自重和刚性阻力, 成功地测量出无工质微波推力器产生的净推力. 结果表明: 基于经典电磁学理论建立的无工质微波推进系统可以产生净推力; 当微波源输出2.45 GHz, 80---2500 W的微波功率时, 推力器产生的推力分布在70---720 mN范围内, 测量总误差小于12%.     

Characteristics of pulse detonation engine versus ramjet characteristics

We discuss the method of comparing pulse detonation engines (PDE) and engines with combustion in subsonic flow (ramjet) by means of their specific impulse used by the “Center of Pulse-Detonation Combustion” (CPDC). We demonstrate that the method used by CPDC to calculate the performance of PDE overstates the value of specific impulse relative to its actual value by a factor of at least two. In contrast, the values of specific impulse for ramjet are understated. As a result, the specific impulse of PDE significantly exceeds that of ramjet or is close to it. We investigate these misleading conclusions, and demonstrate their complete failure.     

New luminescence measurement facilities in retrospective dosimetry

This paper gives a review of recent developments in luminescence measurement facilities on the Risø TL/OSL reader including radio-luminescence (RL), exo-electron and violet stimulation attachments, and a method for characterising and if necessary correcting for beta irradiation source non-uniformity.We first describe improvements to the existing RL option to allow near infra-red detection (NIR) during irradiation by the built-in ⁹⁰Sr/⁹⁰Y beta source. The RL optical signal is collected by a liquid light guide through an F34-901 interference filter and detection is based on a dedicated thermoelectrically cooled NIR sensitive PMT (detection window peak at 855 nm, FWHM 27 nm). Software and electronics have been modified to allow standard TL and OSL measurements in the same sequence as RL measurements. Together with a new bleaching source based on a high-power UV LED (395 nm; 700 mW/cm²), this facility has been used to measure natural doses in feldspar using the decaying NIR RL signal.Secondly, we present a method for mapping radiation field of the built-in ⁹⁰Sr/⁹⁰Y β-source and estimating grain-location specific dose-rates. This is important for the accuracy of single grain results, when radiation field is spatially non-uniform across the sample area. We document the effect of this correction method and further investigate on the effect of lifting the source to achieve a better dose-rate uniformity.Finally we summarise two recently-developed novel facilities to help investigate (i) the time scales involved in OSL processes (time-resolved exo-electron detection) and (ii) extending the age range (violet stimulated signals from deep quartz OSL traps).     

Effect of thermo-hydrodynamic instability on structure and characteristics of filtration combustion wave of solid fuel

Numerical modelling of flame front stability for the inverse wave (with trailing combustion front) of filtration combustion of solid fuel is performed. The problem is treated in terms of dimensionless variables and parameters. It is found that propagation of a plane combustion front becomes unstable under certain conditions. In this case the front spontaneously inclines. The thermo-hydrodynamic mechanism is supposed to be responsible for instability developing. Anisotropic effective mass diffusivity (dispersion) is also taken into account. It turns out that anisotropic diffusivity affects structure and conversion distribution of the inclined combustion front. It is shown that the key parameters determining stability of combustion wave are dimensionless gas flow rate and width of reactor. The range of these parameters corresponding to the stable plane front is determined. It is shown that stability occurs either for small reactor widths (dimensionless values <1), or low gas flow rate (below 0.2). The optimised values of considered dimensionless parameters for maximal productivity are determined.     

Determination of aerodynamic characteristics of turbine vanes with vertical rotation axis

Presented below are the results of tests of turbine vanes with vertical rotation axis aimed at determination of their aerodynamic characteristics. Three types of vanes with the profiles in the form of semicylinder, semiellipse, and semiellipse with stabilizing plane have been tested. The last type of vane has been tested with stationary and rotary stabilizing planes.     

Three-dimensional numerical thrust performance analysis of hydrogen fuel mixture rotating detonation engine with aerospike nozzle

The propulsive performance for an H₂/O₂ and H₂/Air rotating detonation engine (RDE) with conic aerospike nozzle has been estimated using three-dimensional numerical simulation with detailed chemical reaction model. The present paper provides the evaluation of the specific impulse (I_sp), pressure gain and the thrust coefficient for different micro-nozzle stagnation pressures and for two configurations of conic aerospike nozzle, open and choked aerospike. The simulations show that regardless of the nozzle, increase the micro-nozzles stagnation pressure increases the mass flow rate, the pre-detonation gases pressure and consequently the post-detonation pressure. This gain of pressure in the combustion chamber leads to a higher pressure thrust through the nozzle, improving the I_sp. It was also found that the choked nozzle increases the chamber time-averaged static pressure by 50–60% compared with the open nozzle, inducing higher performance for the same reason explained before.     

Two-stage thermochemical conversion of solid fuel in a setup with steam ejection

The paper presents a set of tests with a setup using steam supply into ejector instead of compressed air. Experi-ments measured the gas analysis data — volumetric concentrations O₂, CO, CO₂, C _n H _m , NO _x , H₂ at different propor-tions of air and steam. The data are compared with calculations for thermodynamic equilibrium compositions for the reacting mixture С+Н₂О+air performed by “Terra” computer code including the case of air excess (α ≤ 1). The cal-culations were also compared with available data on gasification output at a high content of ballasting gas. It was demonstrated that in these operation modes, the steam was an inert dilution agent, which did not exclude the outcome of coal gas production with high Н₂/СО and СО/СО₂ ratios corresponding to different modes of gasification.     

Regression of solid polymer fuel strands in opposed-flow combustion with gaseous oxidizer

The combustion of solid fuels is a complex feedback loop, coupling the decomposition of the solid fuel into volatile gases with the gas-phase combustion which is responsible for the heat flux that drives decomposition. This study aims to explore the combustion of a solid fuel, hydroxyl-terminated polybutadiene (HTPB), with different mixtures of oxygen and nitrogen in an opposed-flow burner (OFB) configuration to better understand these coupled processes. An experimental OFB setup is described, which utilizes a nichrome wire and linear variable differential transformer (LVDT) to capture regression rate and shadowgraph imaging to measure flame thickness. Experimental measurements are compared with results from a complimentary one-dimensional opposed-flow combustion model with a pyrolyzing solid fuel boundary condition that conserves mass, species, and energy at the solid-gas interface. The oxidizer mass flux, ratio of oxygen to nitrogen, and separation distance of the fuel and oxidizer are varied to understand their influence on the combustion process and subsequently their effect on the regression rate. In numerical results, fuel regression rate increases when oxygen mole fraction or mass flux increase, or when separation distance decreases. Experimental regression rates and flame thicknesses are compared to simulated results. Though the actual values do not agree exactly, numerical and experimental results are reasonably close and present similar trends. These results demonstrate the utility of simple optical diagnostics in measuring OFB flames and provide a starting point for future opposed-flow combustion model improvements.     

Three-dimensional numerical simulation of the characteristics of a ramjet power plant with a continuous-detonation combustor in supersonic flight

Multi-variant three-dimensional numerical simulations demonstrate the feasibility of the continuous- detonation process in an annular combustor of a ramjet power plant operating on hydrogen as fuel and air as oxidant in conditions of flight at a Mach number of M ₀ = 5.0 and an altitude of 20 km. Conceptual schemes of an axisymmetric power plant, 400 mm in external diameter and 1.3 to 1.5 m in length, with a supersonic intake, divergent annular combustor, and outlet nozzle with a frusto-conical central body are proposed. Calculations of the characteristics of the internal and external flows, with consideration given to the finite rate of turbulent-molecular mixing of the fuel mixture components with each other and with the combustion products, as well as the finite rate of chemical reactions and the viscous interaction of the flow with the bounding surfaces, have shown that, in these flight conditions, the engine of such a power plant has the following performance characteristics: the thrust, 10.7 kN; specific thrust, 0.89 (kN s)/kg; specific impulse, 1210 s; and specific fuel?consumption 0.303 kg/(N h). In this case, the combustor can operate with one detonation wave traveling in the annular channel at an average velocity of 1695 m/s, which corresponds to a detonation wave rotation frequency of 1350 Hz. It is shown that, an operating combustor has regions with subsonic flow of detonation products, but the flow is supersonic throughout its outlet section.     

Raman gain measurement in solid parahydrogen

We report a steady-state Raman gain measurement of the Q(1)(0) transition (v = 1 ? 0, J = 0 ? 0) in solid parahydrogen. We carry out measurements by pumping with a continuous-wave frequency-doubled YAG laser at 532 nm and observing the direct amplification of a probe-laser beam for the first Stokes transition at 683 nm. A large single-pass amplification coefficient of 2.3 +/- 0.2 is obtained at a pump intensity of 46 kW/cm(2), with an interaction length of 1 cm, giving a steady-state Raman gain coefficient of 18 +/- 3 cm/MW.     

One-dimensional modelling of flame propagation in solid composite fuel with different geometrical configurations

In this paper the propagation of combustion waves in solid composite energetic material consisting of fuel and highly thermal conductive inert elements is investigated using a one-dimensional model with a single step reaction mechanism. The analysis is focused on the study of the effect of the geometrical configuration of the composite material on flame speed and dynamics. Spatial averaging over directions transverse to the propagation direction is performed in such a way as to retain the multidimensional nature of the problem. It is shown that the regimes of combustion depend on the geometry of the composite. The largest possible flame speed enhancement is attained in cases when the heat fluxes along the structural elements are not disrupted. For each configuration selected, there exists an optimal choice of the geometric parameters that maximizes the flame velocity.     

Investigations of three-dimensional flow characteristics in a liquid ramjet combustor using the PIV method

Three-dimensional flow characteristics in a liquid fuel ramjet combustor were investigated using the PIV method. The combustor had two rectangular inlets that form a 90-degree angle with each other, with intake angles of 30 degrees. Three guide vanes were installed in each rectangular inlet to improve flow stability. The experiments were performed in a water tunnel test with the same Reynolds number as Mach 0.3 at the inlet. PIV software was developed to measure the characteristics of the flow field in the combustor. Accuracy of the developed PIV program was verified with a rotating disk experiment and standard data. The experimental results showed that the two main streams from the rectangular intakes collided near the plane of symmetry and generated two large longitudinal vortices, which was in agreement with three dimensional computational results. A large and complex threedimensional recirculating flow was measured behind the intakes.     

气溶胶单粒子粒径的实时测量方法研究

介绍了近期研制的一台实时测量大气气溶胶单粒子粒径和化学成分的仪器在如何测量气溶胶单粒子粒径方面的测量原理及特点，并结合激光解吸附电离飞行时间质谱技术，利用该仪器对木屑燃烧产生的烟气气溶胶粒子的实时测量结果. 关键词： 气溶胶粒子 空气动力学粒径测量方法 激光解吸附电离 飞行时间质谱     

Hysteresis in the static aerodynamic characteristics of a curved-profile wing

The effect of profile asymmetry, Reynolds number, and angles of deflection of high-lift devices on the hysteresis loop shape in the dependences of the static aerodynamic forces and moments on angles of attack is studied. These dependences are measured in wind tunnels during testing of rectangular wings of equal thickness but different curvature. The wings have deflectable flaps spanning the wing trailing edge.