反动式汽轮机通流部分CAD系统

根据上海汽轮机厂引进型汽轮机的设计要求，开发了反动式汽轮机通流部分ＣＡＤ系统。该系统采用控制模块和菜单管理方式，自动化水平高，标准化和通用性好，实现了通流部分气动热力设计、强度振动计算和动叶、隔板施工图自动绘制的三位一体化。实际应用结果表明，提高设计工效约１０倍，缩短了新产品开发周期，优化设计还可提高机组通流部分效率。     

新一代F级联合循环汽轮机通流设计特点

为适应市场需求,提升产品竞争力,上海汽轮机厂设计开发了新一代F级一拖一单轴轴排联合循环汽轮机。主要从机组布置形式及模块、各缸通流部分设计、1 220mm末级长叶片、推力计算特点等方面总结和分析了该机型在通流部分的技术特点。全新的通流设计开发使该机型性能优良、功能丰富、可靠性和运行灵活性高,机组推出后将具有广阔的市场前景。     

末级长叶片几何参数对汽轮机流场气动特性的影响

简要介绍了标准的准三维流动方法以及在汽轮机低压缸通流设计中的典型应用实例,探讨了末级长叶片的叶高、动静叶片喉节比、静叶扭曲规律、静叶倾角、动静叶轴向间距等几何参数对热力气动特性的影响,计算结果可作为低压缸通流部分优化设计的参考.     

可控涡设计环形叶栅的试验研究

可控涡技术目前在大型汽轮机通流部分的优化设计和技术改造中得到日益重视和应用。该文介绍了３种可控涡设计形叶栅与直叶环形叶栅对比试验的结果,并对各种可控涡设计环形叶栅降低损失的机理进行了分析。     

汽轮机高效叶型开发气动性能试验研究

通过开发高效的叶型提高汽轮机通流效率是汽轮机通流设计中最重要的手段之一,为提高汽轮机机组经济性,东方汽轮机有限公司开发一种高效叶型,为了解该叶型的气动性能,对该叶型开展了系统的气动性能试验研究,首先通过平面叶栅、环形叶栅试验得到叶栅详细的损失特性、通流能力等气动性能参数,最后通过多级空气透平试验验证叶型的通流效率,所获得的试验数据和分析结论为高效通流设计中叶型的合理选取提供了重要的基础理论和试验数据支撑。通过与原有叶型的对比结果表明,通流设计中采用新开发的高效叶型,通流效率得到明显的提升,有效提高了汽轮机机组的经济性。     

改善汽轮机通流部分性能的现代化技术

综述了改善汽轮机通流部分性能的现代化技术;平面叶栅的最优化、弯扭静叶和弯扭动叶、排汽缸的正交试验与计算流体力学的结合、收敛－扩张叶型、刷子汽封等。     

一例200MW机组通流部分的磨损事故

通过对某机组通流部分磨损事故的分析，提出了对国产２００ＭＷ机组１３－１９级隔板进行加固，要求调节系统稳定运行并认真对待机组事故串轴测量。     

汽轮机通流部分的改进

叙述了在最近几年世界各国发表的汽轮机通流部分（汽轮机叶栅，级，排汽缸，水份分离）研究与改进的若干结果。     

轴流透平机械通流部分泄漏流动及控制技术研究进展

综述了轴流透平机械通流部分泄漏流动及控制技术的研究进展,首先详细介绍了轴流透平机械特别是汽轮机通流部分的泄漏流动特性及其对通流效率的影响,接着介绍了透平机械动叶顶部间隙泄漏流动特性及其对透平级气动性能的影响的研究,讨论了考虑间隙泄漏流动对某四级工业汽轮机气动性能的影响,研究了某汽轮机高压缸平衡孔对透平级气动性能的影响及其作用机制。论文简介了透平机械流动控制技术及其研究进展,最后给出了对透平机械泄漏流动及控制技术的研究展望。     

基于特征通流面积的汽轮机变工况性能分析

阐述了基于留格尔公式提出的特征通流面积概念的定义及计算方法,在IAPWS-IF97公式基础上,利用Vis-ual Basic 6.0平台初步开发了汽轮机组通流部分特征通流面积计算软件,并以国产600MW超临界机组为研究对象,对机组变工况下级组的特征通流面积进行了计算和分析。研究结果表明:汽轮机级组的特征通流面积在通流部分尺寸不发生变化时,其值保持不变,并且变工况下其计算精度能满足工程要求,可以作为机组通流能力及通流部分故障诊断的准则参数,为机组通流部分的状态监测与故障的精确诊断提供依据。     

Control of LP Turbine Rotor Blade Underloading Using Stator Blade Compound Lean at Root

IntroductionLP turbines operate over some range of flow regimeson both sides of the nominal operating conditions. Acharacteristic feature of LP tUrbines are strong radial gradients of pressure, Mach number and flow angle, especially downstream of the stator, Where these gradientsdetechne inlet now conditions for the moving bladerow. The changing swirl velocity and swirl angle spanwise require considerable twist of the rotor blades. Forlow loads, low pressures at the inlet to the rotor at th…     

某轴流式压气机气动不稳定的相关积分分析

研究了某轴流式压气机节流试验中的气动不稳定问题。运用非线性的相关积分方法对压气机机匣壁面沿程静压信号进行了分析。结果表明,压气机静叶通道机匣壁面给定点静压信号的相关积分值随着发动机工作状态的不同有规律的发生变化,反映了对应位置的流动分离状况;压气机沿程各级静叶通道机匣壁面静压的相关积分值可以反映不同工况时压气机各级叶尖的流动匹配情况;压气机第一级静子机匣壁面静压信号的相关积分值可以反映中低转速工况下放气带开关状态对转子端壁流态的影响。研究还表明,压气机静子机匣壁面沿程静压信号的相关积分分析是进行压气机气动稳定性监控诊断的一种有效手段。     

Experimental analysis of the aerodynamic performance of an innovative low pressure turbine rotor

In the present work the aerodynamic performances of an innovative rotor blade row have been experimentally investigated. Measurements have been carried out in a large scale low speed single stage cold flow facility at a Reynolds number typical of aeroengine cruise, under nominal and off-design conditions. The time-mean blade aerodynamic loadings have been measured at three radial positions along the blade height through a pressure transducer installed inside the hollow shaft, by delivering the signal to the stationary frame with a slip ring. The time mean aerodynamic flow fields upstream and downstream of the rotor have been measured by means of a five-hole probe to investigate the losses associated with the rotor. The investigations in the single stage research turbine allow the reproduction of both wake-boundary layer interaction as well as vortex-vortex interaction. The detail of the present results clearly highlights the strong dissipative effects induced by the blade tip vortex and by the momentum defect as well as the turbulence production, which is generated during the migration of the stator wake in the rotor passage. Phase-locked hot-wire investigations have been also performed to analyze the time-varying flow during the wake passing period. In particular the interaction between stator and rotor structures has been investigated also under off-design conditions to further explain the mechanisms contributing to the loss generation for the different conditions.     

1200mm末级超长叶片全三维工程设计的数值研究

采用汽轮机全三维粘性流场计算程序,通过优化匹配静、动叶和合理选择流道内的各项气动参数,成功地完成了全速机组超长1200mm末级叶片的工程设计。对设计结果的数值验证表明,后加载的弯扭静叶片使得流道内的流动均匀加速,从而减小叶型与二次流损失,并为动叶提供优化设计方案。在动叶下半部分采用后部加载叶型,在上半部分采用专门设计的超音速叶型,可降低激波及激波与边界层相互作用损失。     

Numerical and Experimental Modelling of Gas Flow and Heat Transfer in the Air Gap of an Electric Machine. Part Ⅱ： Grooved Surfaces

The study deals with the cooling of a high-speed electric machine through an air gap with numerical and experimental methods. The rotation speed of the test machine is between 5000-40000 r/min and the machine is cooled by a forced gas flow through the air gap. In the previous part of the research the friction coefficient was measured for smooth and grooved stator cases with a smooth rotor. The heat transfer coefficient was recently calculated by a numerical method and measured for a smooth stator-rotor combination. In this report the cases with axial groove slots at the stator and/or rotor surfaces are studied. Numerical flow simulations and measurements have been done for the test machine dimensions at a large velocity range. At constant mass flow rate the heat transfer coefficients by the numerical method attain bigger values with groove slots on the stator or rotor surfaces. The results by the numerical method have been confirmed with measurements. The RdF-sensor was glued to the stator and rotor surfaces to measure the heat flux through the surface, as well as the temperature.     

透平叶片弯、扭、掠联合造型规律及其气动性能研究

为研究静叶弯、扭、掠联合造型对流场结构的影响,以某高压透平首级叶片为研究对象,借助计算流体力学与正交优化方法,基于动静叶最佳匹配原则（即对于每种静叶构型,动叶都进行了相应的扭转规律变化,使得动静叶气动性能处于最佳匹配状态）,研究了静叶不同复合构型方式对流场结构的影响。结果表明：在合理的静叶弯曲规律下,静叶扭转改型对透平性能有较大影响,掠改型对透平性能影响有限;在一定的扭转规律下,对静叶进行掠改型对轮周效率的影响较小,仅后掠改型会提高透平的轮周效率;对弯扭掠静叶匹配扭动叶进行联合优化,得到的最佳透平的轮周效率为87.12%,与原始透平相比,轮周效率提高了2.09%。     

Local convective heat exchanges from a rotor facing a stator

The local convective heat transfer from a rotor with a 310 mm outer radius is studied experimentally at a distance of 3 mm from a coaxial crown-shaped stator with a 176 mm inner radius and a 284 mm outer radius. The experimental technique is based on the use of a thermally thick rotor heated from behind by infrared radiation. The local heat flux distribution from the rotor surface is identified by resolving the Laplace equation by finite difference method using the experimental temperature distribution as boundary conditions. The tests are carried out with the single rotor and the stator/rotor system for local rotational Reynolds numbers ranging from 2.0·10⁴ to 1.47·10⁶ and thus sweeping across the laminar, transition and turbulent flow regimes. The local and mean Nusselt numbers for the single disc are compared with those obtained experimentally for the stator/rotor system. The flow structure in the space between the rotor and the stator is analysed by Particule Image Velocimetry.     

Clocking Effect in a Two-Stage Compressor with Different Inter-Blade-Row Gaps

A multi-stage axial compressor has inherently unsteady flow fields because of the following main reasons: (1) relative positions between rotor and stator airfoil; (2) the buildup of converted wakes lead to complex wake/wake and wake/airfoil interactions. The distributions of the potential flows and wakes in the flow passage are depended on the relative positions of blade rows in axial and circumference direction, so variations in the relative axial positions (axial gap) and circumferential positions (clocking effect) of stators or rotors can change these distributions, leading to different compressor efficiency. The current study presents the experimental/numerical result of a low-speed axial compressor, considering the combined effects of stator clocking and variation of axial gaps. Testing was conducted in Two-Stage Axial Compressor Facility in Harbin Institute of Technology. In the test, time averaged data were collected. The results of experimental and time accurate flow calculation for 2 axial gaps, 8 clocking positions for each gap are compared. It is shown that clocking determines the degree of interaction of a stator with the wake of another upstream stator for different gaps between the blade rows.     

Aerodynamic Characteristic Research on Final Stage Stator of a Highly Loaded Fan

Due to corner separation and other complex three-dimensional flows existing in the highly loaded stator, which influences the fan performance significantly, highly loaded stator blades of a transonic fan with a maximum camber angle of 57° were studied in this paper and sector cascade experiment was adopted. In order to get the stator aerodynamic parameters as realistic as possible and conduct the experiment without the existence of rotor, an adjustable guide vane was designed to simulate the velocity magnitude and direction of the stator inlet flow. Results show that the adjustable guide vane can simulate the rotor outlet velocity direction and magnitude in most span range. The deviation angle is positive and the maximum value is nearly 21° because the severe separation is at 27% span. Corner separation exists on both pressure side and suction side and the location of separation initiation is determined. Finally, the stator blades were redesigned with some suction slots on the suction side. Experiment results show that the suction slots change the flow field structure, increase the capability of flow turning, and decrease the flow loss.     

Impact of clocking on the aero-thermodynamics of a second stator tested in a one and a half stage HP turbine

This paper focuses on the experimental investigation of the time-averaged and time-accurate aero- thermodynamics of a second stator tested in a 1.5 stage high-pressure turbine. The effect of clocking on aerodynamic and heat transfer are investigated. Tests are performed under engine representative conditions in the VKI compression tube CT3. The test program includes four different clocking positions, i.e. relative pitch-wise positions between the fh-st and the second stator. Probes located upstream and downstream of the second stator provide the thermodynamic conditions of the flow field. On the second stator airfoil, measurements are taken around the blade profile at 15, 50 and 85% span with pressure sensors and thin-film gauges. Both time-averaged and time-resolved aspects of the flow field are addressed. Regarding the time-averaged results, clocking effects are mainly observed within the leading edge region of the second stator, the largest effects being observed at 15% span. The surface static pressure distribution is changed locally, hence affecting the overall airfoil performance. For one clocking position, the thermal load of the airfoil is noticeably reduced. Pressure fluctuations are attributed to the passage of the up- stream transonic rotor and its associated pressure gradients. The pattern of these fluctuations changes noticeably as a function of docking. The time-resolved variations of heat flux and static pressure are analyzed together showing that the major effect is due to a potential interaction. The time-resolved pressure distribution integrated along the second stator surface yields the unsteady forces on the vane. The magnitude of the unsteady force is very dependent on the clocking position.