Energy transfer between Cr3+ and Ni2+ in transparent silicate glass ceramics containing Cr3+/Ni2+ co-doped ZnAl2O4 nanocrystals

The emission intensity of Ni2+ at 1200 nm in transparent ZnO-Al2O3-SiO2 glass ceramics containing ZnAl2O4 nanocrystals is improved approximately 8 times by Cr3+ codoping with 532 nm excitation. This enhanced emission could be attributed to an efficient energy transfer from Cr3+ to Ni2+, which is confirmed by time-resolved emission spectra. The energy transfer efficiency is estimated to be 57% and the energy transfer mechanism is also discussed. (C) 2008 Optical Society of America.

Enhanced near-infrared emission from Ni2+ in Cr3+ Ni2+ codoped transparent glass ceramics

Transparent Li2O-Ga2O3-SiO2 glass ceramics containing Cr3+/Ni2+ codoped LiGa5O8 nanocrystals were synthesized. The steady state emission spectra indicated that the near-infrared emission intensity of Ni2+ at 1300 nm in Cr3+/Ni2+ codoped glass ceramics was enhanced up to about 7.3 times compared with that in Ni2+ single-doped glass ceramics with 532 nm excitation. This enhancement in emission intensity was due to efficient energy transfer from Cr3+ to Ni2+, which was confirmed by time-resolved emission spectra. The energy transfer efficiency was estimated to be 85% and the energy transfer mechanism was discussed. (C) 2008 American Institute of Physics.

Effect of surface plasmon resonance in TiO2/Au thin films on the fluorescence of self-assembled CdTe QDs structure

23rd Congress of the International Comission for Optics (ICO 23)

BISTABLE PERFORMANCE OF CLOSELY COUPLED TWIN STRIPE LASERS.

Results are given for bistable effects in closely coupled twin stripe lasers. These devices use controlled adjustment of asymmetric transverse optical gain to obtain bistability. Various bistable effects have been observed. Initially the authors reported a large light/current hysteresis loop obtained as the drive current to the laser was raised and lowered. Information concerning the bistable mechanisms was then obtained by applying small current pulses into each stripe. It was thus found that bistability was involved with the switching from one stable laser waveguiding mechanism to another. More recently the experimental measurement system has been much improved. Through the use of computer control of motorised micromovements and computer controlled data management, time resolved near and far field, and charge carrier concentration distribution measurements have been more accurately carried out. The paper will outline briefly this system, and report on how it has helped to reveal new mechanisms of bistability in twin stripe lasers.

REGROWTH RATES OF AMORPHOUS LAYERS IN SILICON-ON-SAPPHIRE FILMS.

The rate and direction of regrowth of amorphous layers, created by self-implantation, in silicon-on-sapphire (SOS) have been studied using time resolved reflectivity (TRR) experiments performed simultaneously at two wavelengths. Regrowth of an amorphous layer towards the surface was observed in specimens implanted with 3 multiplied by (times) 10**1**5Si** plus /cm**2 at 50keV and regrowth of a buried amorphous layer, from a surface seed towards the sapphire, was observed in specimens implanted with 1 multiplied by (times) 10**1**5Si** plus /cm**2 at 175keV. Rapid isothermal heating to regrow the layers was performed in an electron beam annealing system. The combination of 514. 5nm and 632. 8nm wavelengths was found to be particularly useful for TRR studies since the high absorption in amorphous silicon, at the shorter wavelength, means that the TRR trace is not complicated by reflection from the silicon-sapphire interface until regrowth is nearly complete.

Unsteady transition in an axial-flow turbine. Part 1. Measurements on the turbine rotor

Previously published measurements in a low-speed, single-stage, axial-flow turbine have been reanalyzed in the light of more recent understanding. The measurements include time-resolved hot-wire traverses and surface hot film gage measurements at the midspan of the rotor suction surface with three different rotor-stator spacings. This paper investigates the suction surface boundary layer transition process, using surface-distance time plots and boundary layer cross sections to demonstrate the unsteady and two-dimensional nature of the process.

细胞色素b6f蛋白复合体中叶绿素 a的性质和功能研究

细胞色素b6f蛋白复合体（Cytochrome b6f complex, Cyt b6f）是光合膜上参与光合作用原初反应过程的主要膜蛋白超分子复合体之一。莱茵衣藻和嗜热蓝细菌的Cyt b6f三维晶体结构均显示，每Cyt b6f单体分子含有1分子Chlorophyll a (Chl a )，充分肯定了Chl a 是Cyt b6f天然成分的观点(Kurisu et al，2003;Stroebel et al，2003)。研究表明不同来源的Cyt b6f中Chla单线激发态寿命(或荧光寿命)并不一样，多数的研究结果认为Cyt b6f中Chla单线激发态寿命只有200ps左右，但是也有Cyt b6f中Chla单线激发态寿命为～600ps的报道;而甲醇中游离Chl a 的单线激发态寿命为4ns左右。针对Cyt b6f中Chla单线激发态寿命快速淬灭的现象，Dashdorj 等(2005)根据晶体结构推测Cyt b6f中Chla单线激发态和邻近的Cyt b6亚基上Tyr105残基发生电子交换传递，从而快速淬灭Chla单线激发态，减少了三线态Chl a和单线态氧的产生，并且认为这是Cyt b6f保护自身不受单线态氧破坏的一种机制，但是这一推测缺乏有力的证据。另外，Cyt b6f中Chla的功能仍然未知。本文以菠菜Cyt b6f为对象，结合多种实验手段，测定了菠菜Cyt b6f中Chl a单线激发态寿命，并对复合体中Chl a 单线激发态淬灭的机理进行了深入研究。此外，我们还对复合体中Chl a 可能的功能进行了初步地探讨。获得了如下的结果： 1．针对不同来源的Cyt b6f中Chla单线激发态寿命（或荧光寿命）测定结果不同的报道，仔细分析了其中的原因，发现除了样品来源的差异外，使用不同的去垢剂可能是一个不可忽视的因素。在实验中，不同的研究者分别采用了十二烷基麦芽糖苷（n-Dodecyl β-D-maltoside，DDM，）和八烷基葡萄糖苷（n-Octyl β-D-glucopyranoside，β－OG)作为溶解样品的去垢剂。因此，本文借助稳态吸收和稳态荧光光谱、瞬态光散射技术，CD光谱和亚皮秒时间分辨吸收光谱等技术，分别研究了这两种去垢剂对Cyt b6f结构和功能的不同影响。结果表明，DDM去垢剂能使Cyt b6f处于较好的分散体系中，其中血红素和Chl a分子处于特定的蛋白环境中，不会导致Cyt b6f变性;而β－OG去垢剂会使Cyt b6f产生聚合现象，其中的血红素和Chl a与蛋白环境的相互作用减弱，和DDM相比其电子传递活性显著降低，Chl a单线激发态寿命延长，Chl a更容易被光破坏。通过这一工作，我们优化和确定了Cyt b6f的溶解条件，为下面的研究工作打下了良好的基础。 2．利用Tyr的特异性修饰剂p-Nitrobenzenesulfonyl Fluoride（NBSF）对Cyt b6f样品进行特性修饰，经原子吸收谱、荧光谱、CD谱、质谱等方法对修饰后的样品进行鉴定，并结合时间分辨飞秒吸收光谱技术，测得修饰后的样品在660nm激发下Chl a 单线激发态寿命延长，从而在实验上提供了Tyr与淬灭Chla单线激发态有关的证据。但是对Cyt b6f 中Chl a瞬态吸收图谱仔细研究表明，菠菜Cyt b6f 中Chl a单线激发态快速淬灭过程中并没有发现Tyr与Chl a 之间发生电子传递时所形成的Chla•¯。以上结果表明，Cyt b6f 中Chl a单线激发态快速的淬灭确实和邻近的Tyr105有关，但是与Dashdorj 等提出的Chla单线激发态和Tyr105残基发生了电子交换传递从而淬灭Chla单线激发态这一想法不符，关于这一问题值得进一步深入研究。 3．红光和绿光对Cyt b6f 照射，Cyt f可以被还原，并且红光比绿光更容易使Cyt f 还原，暗示Cyt f 的还原与Chl a 的关系密切，有可能是Chl a 被激发后，其被激发的电子传给Cyt f。对这一现象的进一步研究表明，Cyt b6f在光照条件下，Cyt f 的还原与体系内C10－PQ库的氧化还原状况相关，氧化型的C10－PQ可能介导电子从Chla传向Cyt f。由于在体内质体醌库的氧化还原状态往往决定Cyt b6f 的氧化还原状态，而通过对Cyt b6f不同氧化和还原状态的吸收谱和荧光谱的研究表明，氧化态和还原态的Cyt b6f 中，Chl a 与蛋白的结合状态是有差异的。这些差异可能暗示着Chl a 分子在行使其功能时与复合体的氧化还原状态是有关系的。通过以上的结果，对Cyt b6f中Chl a 可能的功能进行了假设。 4．此外，我们还发现Cyt b6f具有明显的过氧化物酶活性。在0.1 mmol/L乙酸钠缓冲液，pH3.6，25℃，[H2O2] <40mmol/L的条件下，其催化反应的速度常数为kobs＝26±1.2M•s-1;对H2O2的Km 值为50mmol/L，对guaiacol的Km 值为2mmol/L;反应的最适pH为3.6，最适离子强度为0.1，最适温度为35℃。推测Cyt b6f的这种过氧化物酶活性可能是在胁迫环境下使Cyt b6f中的血红素和Chl a 分子免受H2O2的破坏。

Wake, shock and potential field interactions in a 1.5 stage turbine: Part I: Vane-rotor and rotor-vane interaction

The composition of the time-resolved surface pressure field around a high-pressure rotor blade caused by the presence of neighboring blade rows was studied, with the individual effects of wake, shock and potential field interaction being determined. Two test geometries were considered: first, a high-pressure turbine stage coupled with a swan-necked diffuser exit duct; secondly, the same high-pressure stage but with a vane located in the downstream duct. Both tests were carried out at engine-representative Mach and Reynolds numbers. By comparing the results to time-resolved computational predictions of the flowfield, the accuracy with which the computation predicts blade interaction was determined. It was found that in addition to upstream vane-rotor and rotor-downstream vane interactions, a new interaction mechanism was found resulting from the interaction between the downstream vane's potential field and the upstream vane's trailing edge potential field and shock.

Wake, shock and potential field interactions in a 1.5 stage turbine: Part II: Vane-vane interaction and discussion of results

The composition of the time-resolved surface pressure field around a high-pressure rotor blade caused by the presence of neighboring blade rows was studied, with the individual effects of wake, shock and potential field interaction being determined. Two test geometries were considered: first, a high-pressure turbine stage coupled with a swan-necked diffuser exit duct; secondly, the same high-pressure stage but with a vane located in the downstream duct. Both tests were carried out at engine-representative Mach and Reynolds numbers. By comparing the results to time-resolved computational predictions of the flowfield, the accuracy with which the computation predicts blade interaction was determined. Evidence was obtained that for a large downstream vane, the flow conditions in the rotor passage, at any instant in time, are close to being steady state.

The development of turbine exit flow in a swan-necked inter-stage diffuser

This paper describes both the migration and dissipation of flow phenomena downstream of a transonic high-pressure turbine stage. The geometry of the HP stage exit duct considered is a swan-necked diffuser similar to those likely to be used in future engine designs. The paper contains results both from an experimental programme in a turbine test facility and from numerical predictions. Experimental data was acquired using three fast-response aerodynamic probes capable of measuring Mach number, whirl angle, pitch angle, total pressure and static pressure. The probes were used to make time-resolved area traverses at two axial locations downstream of the rotor trailing edge. A 3D time-unsteady viscous Navier-Stokes solver was used for the numerical predictions. The unsteady exit flow from a turbine stage is formed from rotordependent phenomena (such as the rotor wake, the rotor trailing edge recompression shock, the tip-leakage flow and the hub secondary flow) and vane-rotor interaction dependant phenomena. This paper describes the time-resolved behaviour and three-dimensional migration paths of both of these phenomena as they convect downstream. It is shown that the inlet flow to a downstream vane is dominated by two corotating vortices, the first caused by the rotor tip-leakage flow and the second by the rotor hub secondary flow. At the inlet plane of the downstream vane the wake is extremely weak and the radial pressure gradient is shown to have caused the majority of the high loss wake fluid to be located between the mid-height of the passage and the casing wall. The structure of the flow indicates that between a high pressure stage and a downstream vane simple two-dimensional blade row interaction does not occur. The results presented in this paper indicate that the presence of an upstream stage is likely to significantly alter the structure of the secondary flow within a downstream vane. The paper also shows that vane-rotor interaction within the upstream stage causes a 10° circumferential variation in the inlet flow angle of the 2nd stage vane.

The effect of an upstream turbine on a low-aspect ratio vane

The interaction between a high-pressure rotor and a downstream vane is dominated by vortex-blade interaction. Each rotor blade passing period two co-rotating vortex pairs, the tip-leakage and upper passage vortex and the lower passage and trailing shed vortex, impinge on, and are cut by, the vane leading edge. In addition to the streamwise vortex the tip-leakage flow also contains a large velocity deficit. This causes the interaction of the tip-leakage flow with a downstream vane to differ from typical vortex blade interaction. This paper investigates the effect these interaction mechanisms have on a downstream vane. The test geometry considered was a low aspect ratio second stage vane located within a S-shaped diffuser with large radius change mounted downstream of a shroudless high-pressure turbine stage. Experimental measurements were conducted at engine-representative Mach and Reynolds numbers, and data was acquired using a fast-response aerodynamic probe upstream and downstream of the vane. Time-resolved numerical simulations were undertaken with and without a rotor tip gap in order to investigate the relative magnitude of the interaction mechanisms. The presence of the upstream stage is shown to significantly change the structure of the secondary flow in the vane and to cause a small drop in its performance.

The effects of a trip wire and unsteadiness on a high speed highly loaded low-pressure turbine blade

This paper presents the effect of a single spanwise 2D wire upon the downstream position of boundary layer transition under steady and unsteady inflow conditions. The study is carried out on a high turning, high-speed, low pressure turbine (LPT) profile designed to take account of the unsteady flow conditions. The experiments were carried out in a transonic cascade wind tunnel to which a rotating bar system had been added. The range of Reynolds and Mach numbers studied includes realistic LPT engine conditions and extends up to the transonic regime. Losses are measured to quantify the influence of the roughness with and without wake passing. Time resolved measurements such as hot wire boundary layer surveys and surface unsteady pressure are used to explain the state of the boundary layer. The results suggest that the effect of roughness on boundary layer transition is a stability governed phenomena, even at high Mach numbers. The combination of the effect of the roughness elements with the inviscid Kelvin-Helmholtz instability responsible for the rolling up of the separated shear layer (Stieger [1]) is also examined. Wake traverses using pneumatic probes downstream of the cascade reveal that the use of roughness elements reduces the profile losses up to exit Mach numbers of 0.8. This occurs with both steady and unsteady inflow conditions.

The effect of work processes on the casing heat transfer of a transonic turbine

This paper considers the effect of the rotor tip on the casing heat load of a transonic axial flow turbine. The aim of the research is to understand the dominant causes of casing heat-transfer. Experimental measurements were conducted at engine-representative Mach number, Reynolds number and stage inlet to casing wall temperature ratio. Time-resolved heat-transfer coefficient and gas recovery temperature on the casing were measured using an array of heat-transfer gauges. Time-resolved static pressure on the casing wall was measured using Kulite pressure transducers. Time-resolved numerical simulations were undertaken to aid understanding of the mechanism responsible for casing heat load. The results show that between 35% and 60% axial chord the rotor tip-leakage flow is responsible for more than 50% of casing heat transfer. The effects of both gas recovery temperature and heat transfer coefficient were investigated separately and it is shown that an increased stagnation temperature in the rotor tip gap dominates casing heat-transfer. In the tip gap the stagnation temperature is shown to rise above that found at stage inlet (combustor exit) by as much as 35% of stage total temperature drop. The rise in stagnation temperature is caused by an isentropic work input to the tip-leakage fluid by the rotor. The size of this mechanism is investigated by computationally tracking fluid path-lines through the rotor tip gap to understand the unsteady work processes that occur. Copyright © 2005 by ASME.

Compressor wake/leading-edge interactions at off design incidences

In this paper, the effects of wake/leading-edge interactions were studied at off-design conditions. Measurements were performed on the stator-blade suction surface at midspan. The leading-edge flow-field was investigated using hotwire micro-traverses, hotfilm surface shear-stress sensors and pressure micro-tappings. The trailing-edge flow-field was investigated using hotwire boundary-layer traverses. Unsteady CFD calculations were also performed to aid the interpretation of the results. At low flow coefficients, the time-averaged momentum thickness of the leading-edge boundary layer was found to rise as the flow coefficient was reduced. The time-resolved momentum-thickness rose due to the interaction of the incoming rotor wake. As the flow coefficient was reduced, the incoming wakes increased in pitch-wise extent, velocity deficit and turbulence intensity. This increased both the time-resolved rise in the momentum thickness and the turbulent spot production within the wake affected boundary-layer. Close to stall, a drop in the leading-edge momentum thickness was observed in-between wake events. This was associated with the formation of a leading-edge separation bubble in-between wake events. The wake interaction with the bubble gave rise to a shedding phenomenon, which produced large length scale disturbances in the surface shear stress. Copyright © 2008 by ASME.

Applications of the dynamic mode decomposition

The decomposition of experimental data into dynamic modes using a data-based algorithm is applied to Schlieren snapshots of a helium jet and to time-resolved PIV-measurements of an unforced and harmonically forced jet. The algorithm relies on the reconstruction of a low-dimensional inter-snapshot map from the available flow field data. The spectral decomposition of this map results in an eigenvalue and eigenvector representation (referred to as dynamic modes) of the underlying fluid behavior contained in the processed flow fields. This dynamic mode decomposition allows the breakdown of a fluid process into dynamically revelant and coherent structures and thus aids in the characterization and quantification of physical mechanisms in fluid flow. © 2010 Springer-Verlag.