Tailoring the local interaction between graphene layers in graphite at the atomic scale and above using scanning tunneling microscopy.

With recent developments in carbon-based electronics, it is imperative to understand the interplay between the morphology and electronic structure in graphene and graphite. We demonstrate controlled and repeatable vertical displacement of the top graphene layer from the substrate mediated by the scanning tunneling microscopy (STM) tip-sample interaction, manifested at the atomic level as well as over superlattices spanning several tens of nanometers. Besides the full-displacement, we observed the first half-displacement of the surface graphene layer, confirming that a reduced coupling rather than a change in lateral layer stacking is responsible for the triangular/honeycomb atomic lattice transition phenomenon, clearing the controversy surrounding it. Furthermore, an atomic scale mechanical stress at a grain boundary in graphite, resulting in the localization of states near the Fermi energy, is revealed through voltage-dependent imaging. A method of producing graphene nanoribbons based on the manipulation capabilities of the STM is also implemented.

白杄花粉管微丝骨架介导信号传导的蛋白质组学研究

在高等植物有性生殖过程中，花粉管作为运输精子到胚珠的载体，它的生长具有高度极性化，并且要依赖于微丝。由于花粉管本身所具的特性，它已经成为研究细胞相互识别、胞内和胞外信号的模式系统。本文为了研究微丝在白杄（Picea meyeri Rehd. et Wils.）花粉管生长中的作用，我们应用不同浓度的微丝聚合抑制剂Latrunculin B (LATB) 处理花粉管，并通过激光共聚焦显微镜观察微丝聚合状态的动态变化。结果发现，在低浓度下的LATB能使花粉管中的微丝严重解聚，且抑制其顶端生长。 我们进一步利用蛋白质组学的手段，分析了白杄花粉管微丝解聚后蛋白质的表达图谱。通过双向电泳分离出500个左右考马斯亮兰染色的蛋白质斑点，经过软件分析发现，其中大部分蛋白质的表达量未发生变化，而只有110个蛋白斑点有较大变化。将这些蛋白斑点从胶上切下酶解后用于质谱鉴定，最终鉴定出35个蛋白，其中有18个为上调蛋白，17个下调蛋白。根据其主要功能，通常可分为碳水化合物代谢、胁迫反应、信号和细胞扩展等几类。我们发现由于微丝解聚引起的能量代谢水平降低，可能与依赖于信号传导的微丝重组过程相关。此外，当LATB浓度增加到50 nM时，与细胞壁多糖合成相关的两个蛋白，如reversibly glycosylated polypeptide和type IIIa membrane protein cp-wap13几乎不表达，这说明当微丝聚合完全被抑制后，依赖于微丝的分泌系统也受到影响，从而引起相应蛋白质变化，最终导致细胞壁成分合成的减少。细胞骨架蛋白actin的下调，进一步说明微丝在花粉管生长过程中起着提供或支持的一种机制，也就是能调节信号介导的花粉管生长，并使其在特定的时期到达特定的部位，从而完成植物的受精作用。

脂筏极化参与活性氧介导的白杄花粉管顶端生长

质膜上存在一种富含甾醇物质的液相有序膜脂微区，被称作脂筏 (lipid rafts或lipid microdomains)。这种小的膜微区可以通过在质膜上的侧向移动，聚集形成较大的片状结构，而与微区相关联的蛋白可以通过脂筏的这种聚合作用而凝聚分布于特定的亚细胞结构上。脂筏区域在真菌和动物质膜上具极性分布，并参与细胞的极性形态建成和运动。最近，通过生物化学研究证实，脂筏也存在于植物细胞，然而迄今为止，脂筏与植物细胞极性生长相关联的直接功能证据尚未见报道。 NADPH氧化酶 (NOX，在植物中又称为 Rboh) 产生的活性氧 (Reactive oxygen species, ROS) 可能是调控植物细胞（包括花粉管、根毛和墨角藻合子等）极性生长的通用信号机制。花粉管作为研究细胞极性控制的一种理想模式系统，已被许多信号转导调控研究所采用。在本研究中，我们使用一种能螯合甾醇类物质的多烯类抗生素filipin破坏脂筏结构，以探讨脂筏极化对ROS介导的白杄花粉管极性生长的作用。 我们首次在白杄 (Picea meyeri) 花粉管上应用一种全新的苯乙烯基染料di-4-ANEPPDHQ，成功地在活体细胞上观察到脂筏在花粉管生长顶端的极性分布模式。通过脂筏和甾醇在质膜上的相似定位清楚表明：在花粉管极性生长过程中，存在富含甾醇类物质的质膜微区在花粉管生长顶端的极化现象。 氮蓝四唑（NBT）的还原和二氯二氢荧光素（H2DCF）的氧化均显示，在活跃生长的花粉管顶端区域存在一个以顶端为基底的陡峭ROS梯度，从而进一步验证了ROS在细胞极性生长过程中的信号作用。此外，我们还发现在生长花粉管的亚顶端位置有另一类性质的活性氧组分存在，该ROS组分与线粒体的能量代谢相关。研究结果首次揭示，在快速生长的花粉管中同时存在两类性质不同的ROS组分。 ROS是一种寿命很短而且容易扩散的分子，NADPH氧化酶产生的ROS信号在细胞伸长位点的准确定位是调控极性生长的必要条件。免疫共定位实验显示，NOX成簇极化分布于花粉管的生长顶端。使用filipin进行甾醇的螯合会破坏膜的异质性，干扰NOX簇在生长顶端的定位，减少了顶端的ROS形成，消弱了胞质Ca2+ 浓度梯度，进而抑制了花粉管的顶端生长。 在纯化质膜的基础上，我们使用Triton去垢剂处理结合Optiprep密度梯度离心，分离纯化了抗去垢剂抽提的质膜微区 (Detergent-resistant microdomains, DRMs)。通过免疫印迹分析证实，NADPH氧化酶部分地存在于DRMs中。非变性胶活性实验证明，该酶需要脂筏定位来保持酶活性。因此我们认为，在正常的细胞极性生长中，脂筏招募并运载NADPH氧化酶到花粉管的生长顶端，并为NOX及其活性亚基的有效互作提供了适宜的微环境，由此保证了NOX蛋白产生ROS的较高酶活性，进而维持花粉管的极性顶端生长。 总之，甾醇螯合对白杄花粉管生长影响的研究，为脂筏极化在花粉管极性生长中的作用提供了证据。基于以上生物化学和细胞生物学的结果，我们针对花粉管中富含甾醇的脂筏微区和NOX功能之间的联系，提出了一种假说模式：(1) 植物细胞质膜上的脂筏为信号分子ROS在特定位点的聚集提供了物理载体；(2) 脂筏的完整性和甾醇依赖性对NOX的定位和活性是必要的，并为花粉管细胞极性产生和维持所必需。上述研究结果表明，脂筏在花粉管顶端的极化，以及作为关键生长因子的NOX在质膜脂筏中的定位，对花粉管的高度极性生长具有重要作用。

Oxygen isotope analysis of corals from the Gulf of California and the Gulf of Panama: application and implications for coral-based paleoclimate reconstructions [abstract]

EXTRACT (SEE PDF FOR FULL ABSTRACT): Coral-based reconstruction of past variability of sea surface conditions is improving our understanding of the tropical ocean-atmosphere system. We present oxygen isotope records from corals collected near the tip of Baja California (Baja) and the Gulf of Panama (Saboga).

General features and productivity of the Wadge Bank trawl fishery

For several years one of the world's few successful tropical trawl fisheries has been carried on off the southern tip of India. Much of it has been under the auspices of the Government of Ceylon. Records covering the entire history of the fishery are remarkably complete and those of the last ten years are unusually detailed. The purpose of this paper is to summarize these records and relate them to information from other sources in such a way as to illustrate the principal features of the fishery and permit comparisons with other fisheries. This should provide a sound basis for clear thinking about the industry's present problems and prospects. This is important because the fishery is expanding.

Stall inception in axial compressors

Detailed measurements have been made of the transient stalling process in an axial compressor stage. The stage is of high hub-casing ratio and stall is initiated in the rotor. If the rotor tip clearance is small stall inception occurs at the hub, but at clearances typical for a multistage compressor the inception is at the tip. The crucial quantity in both cases is the blockage caused by the endwall boundary layer. Prior to stall disturbances rotate around the inlet flow in sympathy with rotating variations in the endwall blockage; these can persist for some time prior to stall, rising and falling in amplitude before the final increase which occurs as the compressor stalls.

Stall inception in axial compressors

Detailed measurements have been made of the transient stalling process in an axial compressor stage. The stage is of high hub-casing ratio and stall is initiated in the rotor. If the rotor tip clearance is small stall inception occurs at the hub, but at clearances typical for a multistage compressor the inception is at the tip. The crucial quantity in both cases is the blockage caused by the endwall boundary layer. Prior to stall, disturbances rotate around the inlet flow in sympathy with rotating variations in the endwall blockage.

Report of the Frame Survey of Lake Albert conducted in May 2012

Lake Albert and Albert Nile are a major source of fisheries resources sustaining the riparian communities in Uganda and the Democratic Republic of Congo (DRC). Like all shared bodies of Uganda Lake Albert and Albert Nile fisheries are faced with immense exploitation pressure one time described as the tragedy of the commons. In Uganda, the lake is shared by five riparian districts namely: Buliisa, Bundibugyo, Hoima, Kibaale and Nebbi. The lake covers a total estimated surface area of 5,270 square kilometers with approximately 60% within Ugandan waters. It is located in the western part of the great rift-valley at an altitude of 618 m above Sea level. The central parts of the lake are characterized by steep escarpments whereas the northern and southern parts lie in a plain of the rift valley. The plains are gently sloping, resulting in shallow swampy inshore waters in many places. The major inflowing rivers are the Semliki and Kafu in the south, and the Victoria Nile at the northern tip. The lake has a diverse fish fauna with a gradient of multi-species fisheries in different parts of the lake. The overall objective of the Frame Survey was to provide information on the facilities and services at landing sites and the composition, magnitude and distribution of fishing effort to guide development and management of the fisheries resources of Lake Albert and Albert Nile. The specific objectives were to provide information on: a) The number of fish landing sites; b) The facilities available at the fish landing sites to service the sector including accessibility; c) The service providers especially fisheries staff at fish landing sites; d) The number of fishers; e) The number and types of fishing crafts and their mode of propulsion; f) The number, types and sizes of fishing gears used on the lake and their mode of operation.

Three-dimensional interactions in the rotor of an axial turbine

This article presents a study of the development of the three-dimensional flowfield within the rotor blades of a low-speed, large-scale axial flow turbine. Measurements have been performed in the rotating and stationary frames of reference. Time-mean data have been obtained using miniature five-hole pneumatic probes, whereas the unsteady development of the flow has been determined using three-axis subminiature hot-wire anemometers. Additional information is provided by the results of blade-surface flow-visualization experiments and surface-mounted hot-film anemometers. The development of the stator exit flow, as it passes through the rotor blades, is described. Unsteady data suggest that the presence of the rotor secondary and tip leakage flows restricts the region of unsteady interaction to near midspan when the stator wakes and secondary flows are adjacent to the suction surface. Surface-mounted hot-film data show that this affects the suction-side laminar-turbulent transition process.

Measurement of forces during the modification of C60 islands

A UHV atomic force microscope with a conducting tip is used to measure the tip-sample conductance as a function of the applied force on well-ordered, monolayer islands of C60 on Cu(111). By imaging the sample before and after each force-distance experiment, it was possible to investigate the forces required for the removal of individual C60 molecules from the islands. The removal of C60 occurs near defects or edges of the C60 islands and requires an applied force of 5-20 nN, which corresponds to applied pressures of order 1 GPa. In addition, it was possible to investigate the strength of the C60 film on the molecular scale. It was found that the mechanical stiffness of a C60 molecule is of order 6 N/m and the islands appear to undergo a reversible yield process at an applied pressure of around 1.2 GPa.

Blade row interaction in a high pressure steam turbine

This paper presents a study of the three-dimensional flow field within the blade rows of a high-pressure axial flow steam turbine stage. Compound lean angles have been employed to achieve relatively low blade loading for hub and tip section and so reduce the secondary losses. The flow field is investigated in a Low-Speed Research Turbine using pneumatic and hot-wire probes downstream of the blade row. Steady and unsteady numerical simulations were performed using structured 3D Navier-Stokes solver to further understand the flow field. Agreement between the simulations and the measurements has been found. The unsteady measurements indicate that there is a significant effect of the stator flow interaction in the downstream rotor blade. The transport of the stator viscous flow through the rotor blade row is described. Unsteady numerical simulations were found to be successful in predicting accurately the flow near the secondary flow interaction regions compared to steady simulations. A method to calculate the unsteady loss generated inside the blade row was developed from the steady numerical simulations. The contribution of various regions in the blade to the unsteady loss generation was evaluated. This method can assist the designer in identifying and optimizing the features of the flow that are responsible for the majority of the unsteady loss production. An analytical model was developed to quantify this effect for the vortex transport inside the downstream blade.

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.

A discrete dislocation analysis of fatigue crack growth

Cyclic loading of a plane strain mode I crack under small scale yielding is analyzed using discrete dislocation dynamics. The dislocations are all of edge character, and are modeled as line singularities in an elastic solid. At each stage of loading, superposition is used to represent the solution in terms of solutions for edge dislocations in a half-space and a non-singular complementary solution that enforces the boundary conditions, which is obtained from a linear elastic, finite element solution. The lattice resistance to dislocation motion, dislocation nucleation, dislocation interaction with obstacles and dislocation annihilation are incorporated into the formulation through a set of constitutive rules. An irreversible relation between the opening traction and the displacement jump across a cohesive surface ahead of the initial crack tip is also specified, which permits crack growth to emerge naturally. It is found that crack growth can occur under cyclic loading conditions even when the peak stress intensity factor is smaller than the stress intensity required for crack growth under monotonic loading conditions; however below a certain threshold value of ΔKI no crack growth was seen.

Heat transfer and aerodynamics of turbine blade tips in a linear cascade

Local measurements of the heat transfer coefficient and pressure coefficient were conducted on the tip and near tip region of a generic turbine blade in a five-blade linear cascade. Two tip clearance gaps were used: 1.6% and 2.8% chord. Data was obtained at a Reynolds number of 2.3 × 10 5 based on exit velocity and chord. Three different tip geometries were investigated: a flat (plain) tip, a suction-side squealer, and a cavity squealer. The experiments reveal that the flow through the plain gap is dominated by flow separation at the pressure-side edge and that the highest levels of heat transfer are located where the flow reattaches on the tip surface. High heat transfer is also measured at locations where the tip-leakage vortex has impinged onto the suction surface of the aerofoil. The experiments are supported by flow visualisation computed using the CFX CFD code which has provided insight into the fluid dynamics within the gap. The suction-side and cavity squealers are shown to reduce the heat transfer in the gap but high levels of heat transfer are associated with locations of impingement, identified using the flow visualisation and aerodynamic data. Film cooling is introduced on the plain tip at locations near the pressure-side edge within the separated region and a net heat flux reduction analysis is used to quantify the performance of the successful cooling design. copyright © 2005 by ASME.