那些千奇百怪的太阳能建筑

正世界之大无奇不有,只要人类不停止思考,就能创造出各种奇妙的事物。今天,小编就和大家一起领略世界各地的太阳能建筑之魅!虽然有的已经真正纳入城市的版图,有的还尚处于设计稿中,但无论怎样,未来的房屋等建筑无论从外形设计还是能源管理系统设计也许都会超乎你的想象。     

发明与专利

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Introduction to patents简

正2014-01.Method for producing a cast blade for a gas turbine Patent No.:US8382433Date of Patent:2013-02-26Inventors:Brian Kenneth Wardle,et al Assignee:Alstom Technology Ltd[Switzerland]The present invention describes a method for casting a blade for a gas turbine.The blade includes an elongated airfoil which extends in the blade's longitudinal direction,merges into a blade root at the lower end,has a shroud segment at the blade tip and is pervaded by a single     

Multi-point design optimization of hydrofoil for marine current turbine

The comprehensive performance of the marine current turbine is an important issue in the ocean energy development. Its key is the performance of the hydrofoil, which is used to form the turbine blade. A multi-point optimization method of the hydrofoil is proposed in this paper. In this method, the Bezier curve is used to parameterize the hydrofoil. The geometrical parameters are used as variables while the lift-drag ratio and the cavitation performance of the hydrofoil are used as the objective functions. The NSGA-II algorithm is chosen as the optimization algorithm. In order to resolve the difficulty of this high-dimensional multi-objective optimi- zation problem, the conception of the distance metric in the metric space is introduced to unify the lift-drag ratio and the cavitation performance under different working conditions. And then, the above optimization method is applied in the NACA63-815 hydro- foil＇s optimal design under three typical conditions. Finally, the results from the performance comparison of the original and optimi- zed hydrofoils obtained by using the CFD simulation are analyzed in detail. It is indicated that the optimized hydrofoils enjoy a better hydrodynamic performance than the original ones under the three conditions. The feasibility and the theoretical validity of this optimization method are confirmed by the results.     

Effects of nozzle-strut integrated design concepton on the subsonic turbine stage flowfield

In order to shorten aero-engine axial length,substituting the traditional long chord thick strut design accompanied with the traditional low pressure（LP） stage nozzle,LP turbine is integrated with intermediate turbine duct（ITD）.In the current paper,five vanes of the first stage LP turbine nozzle is replaced with loaded struts for supporting the engine shaft,and providing oil pipes circumferentially which fulfilled the areo-engine structure requirement.However,their bulky geometric size represents a more effective obstacle to flow from high pressure（HP） turbine rotor.These five struts give obvious influence for not only the LP turbine nozzle but also the flowfield within the ITD,and hence cause higher loss.Numerical investigation has been undertaken to observe the influence of the Nozzle-Strut integrated design concept on the flowfield within the ITD and the nearby nozzle blades.According to the computational results,three main conclusions are finally obtained.Firstly,a noticeable low speed area is formed near the strut＇s leading edge,which is no doubt caused by the potential flow effects.Secondly,more severe radial migration of boundary layer flow adjacent to the strut＇s pressure side have been found near the nozzle＇s trailing edge.Such boundary layer migration is obvious,especially close to the shroud domain.Meanwhile,radial pressure gradient aggravates this phenomenon.Thirdly,velocity distribution along the strut＇s pressure side on nozzle＇s suction surface differs,which means loading variation of the nozzle.And it will no doubt cause nonuniform flowfield faced by the downstream rotor blade.     

试论航空发动机涡轮机匣传热分析技术

涡轮机匣主要是航空发动机以涡轮段结构的连接位置作为载体,承担机械负荷、气体压力、热负荷,其所发挥的主要作用是承力。而且,涡轮机匣内部流动通道是航空发动机空气系统的重要组成部分,其主要任务是给冷却空气提供气流运动的有效通道。另外,还需要对涡轮叶尖的运作间隙进行全面控制,并引进冷气,以此进行机匣冷却,从而保证机匣的整体强度与使用寿命。作为冷气通道的主要结构,空气系统在计算时,还应对机匣各部分内的通道流动换热特性做进一步的充分了解,并且机匣的温度分布与叶尖间隙控制之间密切相关,在进行机匣温度计算的时候,还需充分了解换热特性。通过数值仿真与实验系统深入探究了涡轮机匣传热特性,并进一步分析了高压涡轮机匣传热分析技术。     

太阳能电站中涡轮机的设计

太阳能电站设备中,涡轮机是利用集热棚内气流动能的主要设备,对提高整个太阳能电站的效率有着极为重要的作用。针对塔囱电站中不同叶片数的涡轮进行计算,对每种情况计算的多种结果进行比较分析,最终选出每种叶片数对应的最佳情况,再综合比较不同叶片数之间的优劣,选出对应于100 kW太阳能塔囱电站最实用的涡轮机,从而提出一套计算太阳能涡轮的计算方法,解决太阳能电站中涡轮机的设计问题。通过对太阳能热气流电站的涡轮机进行优化研究,提高这种太阳能电站的整体效率,使其具有更强的竞争力。     

Impact of Stagger Angle Nonuniformity on Turbine Aerodynamic Performance

The assembling error may lead to variation in stagger angles, which would affect the aerodynamic performance of the turbine. To investigate this underlying effect, two parallel numerical experiments on two turbines with the same profile, but uniform and nonuniform vane stagger angle respectively, were conducted in both steady and un- steady methods. The results indicate that certain changes in the detailed flow field of the turbine occur when the stagger angles are nonuniform, further, the blade loading distribution of the vane and rotor become markedly dif- ferent from that in uniform vane stagger angle situation. Then these consequences caused by nonuniformity men- tioned above enhance the unsteadiness of the flow, finally, the aerodynamic performance changes dramatically. It also shows that, compared with steady simulation, the unsteady numerical simulation is necessary in this investigation     

Influences of Incidence Angle on 2D-Flow and Secondary Flow Structure in Ultra-Highly Loaded Turbine Cascade简

An increase of turbine blade loading can reduce the numbers of blade and stage of gas turbines. However, an in- crease of blade loading makes the secondary flow much stronger because of the steep pitch-wise pressure gradient in the cascade passage, and consequently deteriorates the turbine efficiency. In this study, the computations were performed for the flow in an ultra-highly loaded turbine cascade with high turning angle in order to clarify the ef- fects of the incidence angle on the two dimensional flow and the secondary flow in the cascade passage, which cause the profile loss and the secondary loss, respectively. The computed results showed good agreement with the experimental surface oil flow visualizations and the blade surface static pressure at mid-span of the blade. The profile loss was strongly increased by the increase of incidence angle especially in the positive range. Moreover, the positive incidences not only strengthened the horseshoe vortex and the passage vortex but also induced a new vortex on the end-wall. Moreover, the newly formed vortex influenced the formation of the pressure side leg of horseshoe vortex.