入口旋流角对排气扩压段气动性能影响的数值研究

为了研究入口气流旋流角对带支撑结构轴流排气扩压段气动性能的影响,以某型燃气轮机排气扩压段为研究对象,采用数值计算的方法,对单独排气段模型及排气段和涡轮末级动叶耦合模型分别进行数值模拟。采用总压保持系数和静压恢复系数作为衡量排气扩压段气动性能的主要参数。排气段单独模拟的结果显示,当旋流角从0°变化至-32°,总压保持系数下降4%,且在-20°以后开始呈现突然的快速下降趋势;而静压恢复系数先上升后降低,在-16°时达到最大值。另外,通过耦合模型与单独排气段模型的数值计算对比,发现当排气段入口旋流角和质量流量相同时,计算结果较为一致。以上结果说明,入口旋流角是影响排气扩压段流动性能的关键因素之一,进行排气段结构设计时要充分考虑旋流角对内部流动的影响。而且,单独排气段数值模拟在相同质量流量和旋流角度条件下,可近似达到耦合模拟的精度,提高设计效率。     

某MW级燃机变几何动力涡轮动_静叶栅与排气道的流动分析

某MW级燃机末端的变几何动力涡轮动/静叶栅与非对称排气道之间的流场会相互作用,使用商用CFD软件CFX研究了不同导叶安装角下、二者之间的耦合流场.在导叶设计安装角下的流场分析表明:排气道的非周向对称性主要影响动力透平的动叶流场,导致动叶不同叶片载荷出现周向差异,同时动叶出口气流角分布也会出现强烈的周向不均匀性.导叶旋转7°后,导叶进口正冲角增大导致吸力面大范围分离;动叶进口呈现负攻角,压力面的分离程度增大;同时排气道内旋涡程度加剧,这导致了导叶安装角改变后动力涡轮的效率和功率出现明显下降.     

带有冷气掺混的三级透平气动性能数值研究

借助NUMECA数值仿真软件,以某型燃气轮机的三级透平作为计算模型,对其在冷却气体掺混前后的流场进行了数值模拟。考虑到工质物性的影响,采用了变比热高温燃气作为计算工质。同时,针对燃气轮机透平进口的变工况问题,选取不同的透平进口总压值进行数值计算。结果表明,冷却气体的加入使得级损失增大,每列叶片流道出口速度或相对速度减小,下游叶片进口气流角减小;在三级透平冷气掺混时改变进口总压值,每列叶片流道的进口气流角几乎不变,除第三级动叶的激波损失与尾迹损失增大外,其余叶片流道的能量损失变化不明显。     

高负荷涡轮扇形叶栅变攻角气动试验研究

为了探究不同出口马赫数、进口攻角对涡轮叶栅气动性能的影响,本文在进口气流偏离轴向23°的条件下,试验出口马赫数分别为0.7、0.8、0.9,并在出口马赫数为0.8的条件下,攻角分别为0、±7.5°与±15°,对某型涡轮扇形静叶栅进行了吹风试验。试验结果表明:随着出口马赫数的增加,叶片载荷增大,出口总压损失增加,出口气流角减小;随着进口气流攻角从负到正的变化,叶片前缘压力载荷增加,出口气流角增加,总压损失先减小再增大,且攻角为0时,总压损失最小。     

来流条件对排汽缸内非轴对称流动的影响

研究了大功率汽轮机低压缸排汽在不同气流角及不同总压分布下的流场,以模型为对象进行了三维流场的数值模拟.结果表明:排汽缸入口较大的旋流角会恶化排汽缸性能,而总压沿径向变化梯度为负时则有利于改善排汽缸气动性能.基于这一结果提出了通过改变总压分布抑制由于来流方向对排汽缸性能产生的负面影响的方法.     

透平末级动叶顶部间隙变化对排气扩压器 气动性能的影响

文章采用数值分析方法研究了透平末级动叶顶部间隙变化对排气扩压器气动性能的影响.结果显示随着叶顶间隙相对值从0%逐渐增大至1.5%,排气扩压器进口气流角和总压逐渐增大,排气扩压器静压恢复性能先提升,然后逐渐下降.     

椭球形轮毂端盖对透平排气扩散器性能的影响

排气扩散器是透平的重要组成部分。以某型号F级燃气轮机为例,通过数值模拟的方法,探究椭球形轮毂端盖对透平排气扩散器性能的影响。研究结果表明:一定轴向长度的椭球形轮毂端盖能显著地抑制轮毂下游的流动分离,减少排气扩散器的总压损失;当改型排气扩散器椭球形轮毂端盖的轴向长度与轮毂直径之比为1时,排气扩散器的总压损失系数相比原型减少约10.75%,静压恢复系数相比原型增加约2.18%;在大流量工况时,与原型相比,改型排气扩散器的性能也有一定程度的提升。该研究对透平的效率提高和升级改造具有重要意义。     

槽道出口位置对高负荷扩压叶栅性能的影响

针对高负荷扩压叶栅攻角范围小、吸力面流动易分离的特点,采用在叶片上从压力面向吸力面开槽的方法控制局部流动,设计了一种收敛转折型的槽道结构,并通过数值模拟方法研究了不同开槽位置对叶栅性能的影响,计算结果表明:正攻角工况,叶片开槽处理可以有效吹除吸力面分离气流,从而增大静压升,降低总压损失,扩大稳定工作范围;对于大攻角分离情况,最佳开槽位置位于叶型中部附近。     

透平弯扭导叶在部分负荷下气动性能的研究

应用数值计算的方法，研究透平导叶弯扭联合方案在部分负荷下，叶栅内的流动性能。计算方法基于时均N—S方程，湍流模型为Baldwin—Lomax模型。结果包括总压损失系数、出口气流角等参数在流场中的分布。结果表明，弯扭导叶在部分负荷工况下运行时，流动性能稳定，同样能改善整个流场结构。     

高负荷风扇末级静叶气动特性试验研究

为了研究高负荷风扇末级静叶的气动性能,通过在静子叶栅前加装导流叶片,来模拟多级风扇中动叶出口气流参数,通过旋转导叶改变静叶进口气流角,分析不同进口气流角和进口马赫数条件下的静叶气动特性。研究表明:本研究设计的导流叶片可以为静叶提供接近动叶出口条件的来流参数,从而开展静叶试验研究。该静叶为大折转角扩压叶栅,随马赫数增加,总压恢复系数减小。随转角增大,静叶压力面流动随导叶转角增加明显改善,分离范围减小;吸力面存在较大范围的分离,转角增加对分离范围影响不大。     

Numerical investigation of the effects of ITD length on low pressure nozzle

The advantage of high efficiency,low SFC (Specific Fuel Consumption),ultra-high bypass ratio turbofan engine attracts more and more attention in modem commercial engine.The intermediate turbine duct (ITD),which connects high pressure turbine (HPT) with low pressure turbine (LPT),has a critical impact on the overall performance of turbine by guiding flow coming from HPT to LPT without too much loss.Therefore,it becomes more and more urgent to master the technique of designing aggressive,even super-aggressive ITD.Much more concerns have been concentrated on the duct.However,in order to further improve turbine,LPT nozzle is arranged into ITD to shorten low pressure axle.With such design concept,it is obvious that LPT nozzle flow field is easily influenced by upstream duct structure,but receives much less interests on the contrary.In this paper,numerical method is used to investigate the effects of length of ITD with upstream swirl blades on LPT nozzle.Nine models with the same swirl and nozzle blades,while the length of ITD is the only parameter to be changed,will be discussed.Finally,several conclusions and advices for designers are summarized.After changing axial length of ducts,inlet and outlet flow field of nozzle differs,correspondingly.On the other hand,the shearing stress on nozzle blade (suction and pressure) surface presents individual feature under various inlet flow.In addition to that,"Clocking-like effect" is described in this paper,which will contribute much to the pressure loss and should be paid enough attention.     

A novel radial self-rectifying air turbine for use in wave energy converters

The flow through the air turbine of an oscillating water column (OWC) wave energy converter is reciprocating and is random and highly variable. It is not surprising that the time-averaged efficiency of the air turbine is substantially lower than that of a conventional turbine working in nearly steady conditions. A new type of radial-flow self-rectifying turbine (named here biradial turbine) is described in the paper. The two inlet/outlet openings of the rotor are axially offset from each other and face radially the surrounding space. The turbine is symmetrical with respect to a plane perpendicular to its axis of rotation. The rotor blades are surrounded by a pair of radial-flow guide-vane rows. Each guide vane row is connected to the rotor by an axisymmetric duct whose walls are flat discs. A two-dimensional flow method is used first as a preliminary design tool for the turbine geometry. More detailed numerical results are then obtained with the aid of a commercial three-dimensional real-fluid CFD code, which allows a more refined geometry optimization to be carried out, and yields results for flow details through the turbine and for the turbine overall performance under several operating conditions.     

Investigations on an Axial Flow Fan Stage subjected to Circumferential Inlet Flow Distortion and Swirl

INTRODUCTIONInletfiowdistortionisatermusedtodenotethewriationofflowpropertiesasafunctionofthespa-tialcoordinatesandtime.Thenonuniformityoc-cursinconunonflowpropertiessuchastotalpressure,staticpressure'velocity,temperature,flowangleandgasconstituency.Swirlisthetermusedtodescribetherotationoffiowinrelationtotherotationoftheforor.Swirlmaybegeneratedasaconsequenceofsec-ondaryflowsinducedduetoflowcurvaturesorduetothepresenceofInletGuideVanes(IGV).DistortionandSwirl(inducedduetocurvatureoffl…     

Numerical investigation of the effects of rising angle on intermediate turbine duct and nearby turbines

In order to improve the efficiency,ultra-high bypass ratio engine attracts more and more attention because of its huge advantage,which has larger diameter low pressure turbine (LPT).This trend will lead to aggressive (high diffusion) intermediate turbine duct (ITD) design.It is necessary to guide the flow leaving high pressure turbine (HPT) to LPT at a larger diameter without any severe loss generating separation or flow disturbances.In this paper,eight ITDs with upstream swirl vanes and downstream LPT nozzle are investigated with the aid of numerical method.These models are modified from a unique ITD prototype,which comes from a real engine.Key parameters like area ratio,inlet height,and non-dimensional length of the ITDs are kept unchanged,while the rising angle (radial offset) is the only changed parameter which ranges from 8 degrees to 45 degrees.In this paper,the effects of rising angle (RA) on ITD,as well as nearby turbines,will be analyzed in detail.According to the investigation results,RA could be as large as 40 degrees in such model of this paper to escape separation;When RA increases,local inlet flow field of LPT nozzle appears to be with apparent variation;while a positive result is that outlet flow field could be kept almost unchanged through modifying blade profile.On the other hand,it seems optimistic that the overall total pressure loss could be kept nearly equivalent among different RA cases.And a valuable conclusion is that outer wall curvature is more important for pressure loss,which advises a clear direction for optimizing ITD.     

Analysis of gas turbine operating parameters with inlet fogging and wet compression processes

Inlet fogging has been widely noticed in recent years as a method of gas turbine air inlet cooling for increasing the power output in gas turbines and combined cycle power plants. The effects of evaporative cooling on gas turbine performance were studied in this paper. Evaporative cooling process occurs in both compressor inlet duct (inlet fogging) and inside the compressor (wet compression). By predicting the reduction in compressor discharge air temperature, the modeling results were compared with the corresponding results reported in literature and an acceptable difference percent point was found in this comparison. Then, the effects of both evaporative cooling in inlet duct, and wet compression in compressor, on the power output, turbine exhaust temperature, and cycle efficiency of 16 models of gas turbines categorized in four A–D classes of power output, were investigated. The results of this analysis for saturated inlet fogging as well as 1% and 2% overspray are reported and the prediction equations for the amount of actual increased net power output of various gas turbine nominal power output are proposed. Furthermore the change in values of physical parameters and moving the compressor operating point towards the surge line in compressor map was investigated in inlet fogging and wet compression processes.     

Influences of inflow condition on non-axisymmetric flows in turbine exhaust hoods

The complex 3D flow in a steam turbine exhaust hood model with different inlet swirl and inlet total pressure radial distributions has been simulated by employing CFX-5 and analyzed in this paper. It＇s found that the inlet tangential flow angle at hub has a negative effect on the exhaust hood performance, while a negative gradient of inlet total pressure radial distribution has a positive impact on the hood performances. It＇s also numerically con- firmed that a proper distribution of total pressure at hood inlet can successfully eliminate the negative effects caused by the inappropriate inlet swirl distribution and improve the hood aerodynamic performance.     

非定常脉冲爆震来流下涡轮气动特征仿真研究

脉冲爆震涡轮发动机是未来涡轮发动机的一种有潜力的发展方向。为了厘清具有强非定常性的脉冲爆震来流下涡轮的气动性能及流动特征,为脉冲爆震涡轮发动机涡轮的设计提供技术支撑,采用非定常进口总压与总温边界条件对某单级燃气涡轮开展了瞬态数值仿真计算分析。研究结果表明：由于进口来流的强非定常性,涡轮内部流动在爆震周期的前段时间并未完全建立起流动平衡,故进出口的流量不守恒;焓降功率与扭矩功率、焓降效率与扭矩效率不相等;在一个爆震周期内,动叶进口气流攻角的变化幅度达到40°,出口绝对气流角的变化幅度达到50°。在一个爆震周期中,只有约1/4的时间段涡轮的气动状态接近设计点,故一个爆震周期中涡轮的综合功率较低。     

Aerodynamic simulations of offshore floating wind turbine in platform‐induced pitching motion

Forfloating offshore wind turbines, rotors are under coupled motions of rotating and platform‐induced motions because of hydrodynamics impacts. Notably, the coupled motion of platform pitching and rotor rotating induces unsteadiness and nonlinear aerodynamics in turbine operations; thus having a strong effect on the rotor performances including thrust and power generation. The present work aims at developing a computational fluid dynamics model for simulations of rotor under floating platform induced motions. The rotor motion is realized using arbitrary mesh interface, and wind flows are modelled by incompressible Navier‐Stokes flow solver appended by the k  ? ω shear stress transport turbulence model to resolve turbulence quantities. In order to investigate the fully coupled motion of floating wind turbine, the six degree of freedom solid body motion solver is extended to couple with multiple motions, especially for the motion of rotor coupled with the prescribed surge‐heave‐pitch motion of floating platform. The detailed methodology of multiple motion coupling is also described and discussed in this work. Both steady and unsteady simulations of offshore floating wind turbine are considered in the present work. The steady aerodynamic simulation of offshore floating wind turbine is implemented by the multiple reference frames approach and for the transient simulation, the rotor motion is realized using arbitrary mesh interface. A rigorous benchmark of the present numerical model is performed by comparing to the reported literatures. The detailed elemental thrust and power comparisons of wind turbine are carried out by comparing with the results from FAST developed by National Renewable Energy Laboratory and various existing numerical data with good agreement. The proposed approach is then applied for simulations of National Renewable Energy Laboratory 5MW turbine in coupled platform motion at various wind speeds under a typical load case scenario. Transient effect of flows over turbines rotor is captured with good prediction of turbine performance as compared with existing data from FAST. Copyright © 2016 John Wiley & Sons, Ltd.     

Design and performance evaluation of a pump-as-turbine micro-hydro test facility with incorporated inlet flow control

In the context of micro-hydro power schemes the initial cost of conventional Francis turbine units is often prohibitive. As such there is growing interest in pump-as-turbine (PAT) technology offering a more cost effective, yet still highly efficient, power generating alternative, finding uses in remote area power supply and energy recovery systems. However, the implementation of a PAT is highly problematic in terms of predicting the installed best operating point coupled with poor off-design performance due to the fixed geometry and absence of inlet flow control. In the current work a micro-hydro test facility and turbine unit is developed utilising a commercially available pump impeller together with a customised housing for incorporation of inlet flow control. Working initially from established PAT theory, this paper presents the design and performance testing of a hydraulic turbine unit suitable for use in rural micro-hydro, and energy recovery installations. Maximum efficiency of the unit was found to be 79%, marginally higher than that of the parent pump, while the off-design efficiency offered considerable improvement over previously published data of traditional PAT systems. The design provides a cost effective power generator in comparison to small scale Francis turbines, while providing a greater operational range than traditional PAT units.