燃气轮机压气机喘振事故分析

本文是《烧重油燃气轮机积垢的影响和清洗效果的分析》一文的续篇。主要叙述所发生的压气机喘振现象，并对造成喘振的原因进行了分析。     

燃气轮机压气机喘振故障分析与防喘方法研究

本文围绕如何提高燃气轮机压气机的稳定性,防止喘振的发生问题,对喘振的特征、形成机理进行了详细的分析,总结归纳出导致喘振的因素,并提出了相应的防喘方法和解决措施,为燃气轮机的安全运行提供技术参考和借鉴。     

燃气轮机压气机喘振及其控制算法

压气机是燃气轮机的三大部件之一,它运行的安全、高效对燃气轮机性能至关重要。本文扼要地介绍了压气机喘振的影响因素,分析了压气机的性能曲线和喘振线;在此基础上针对压气机某一种喘振控制策略,分析其各种控制设定曲线和控制算法。通过以上两方面的介绍,希望对燃气轮机压气机的喘振防治有所帮助。     

燃气轮机压气机喘振监测方法研究

压气机喘振是一种对燃气轮机安全运行具有严重破坏作用的不稳定流动。在研究某燃气轮机控制系统的过程中发现,其控制逻辑中没有针对压气机喘振的控制策略。为了保证燃气轮机安全运行,避免发生喘振对燃气轮机造成破坏,在现有测点基础上研究了在燃气轮机控制系统中增加压气机喘振监测的方法。     

MS6001燃气轮机的压气机清洗

本文突出实际，介绍华能重庆燃电厂ＭＳ６００１型燃机的压气机清洗系统，压气机离线和在线清洗方法，清洗频率及效果。     

轴流式压气机喘振特性的某些规律

综合了几型压气机的试验结果,总结出喘振边界的某些规律。利用这些规律不仅可以减少试验的次数。还可以计算出喘振边界上有关的参数。     

MS1002D型燃气轮机油系统故障分析及处理

本文介绍了ＭＳ１００２Ｄ型燃气轮机液压系统出现的故障现象、原因分析及排除情况，可供电厂运行人员参考．     

M701F燃气轮机压气机入口可变导叶机构原理研究

文章就压气机特性分析了IGV的功用、原理，介绍了M701F型燃机可变导叶机构的结构与控制。     

MS6001型燃气轮机的压气机一级动叶断裂分析

本文通过对ＭＳ６００１型燃气轮机的压气机一级动叶断裂的原因进行多方面的分析，总结事故教训和提出反事故对策，以供其他电厂同类机组维护时借鉴．     

MS6001型燃气轮机压气机一级动叶片断裂分析

该文通过对ＭＳ６００１型燃气轮机压气机一级动叶片断裂的事故原因进行了多方面的分析，并总结了事故教训和提出防止事故的对策，以供其它电厂同类机组维护时借鉴。图３参３     

GT13D型燃气轮机喘振与热挂故障的分析

描述了我厂机组发生喘振、热悬挂故障的过程，进而对故障原因和反事故措施等作了讨论分析与阐述。     

Investigation of surge behavior in a micro centrifugal compressor

This paper reports the experimental and theoretical study of the surge occurred in prototyping an ultra micro centrifugal compressor. As the first step, the 10 times size model of an ultra micro centrifugal compressor having the 40 mm outer diameter was designed and manufactured. The detailed experimental investigations for the transient behavior of surge with several different values of B parameter were carried out. The experimental results during the surge were compared with those obtained by the non-linear lumped parameter theory in order to validate the effectiveness of the theoretical surge model for the micro centrifugal compressor. As a result, the quite different behavior of the surge appeared for the different values of B both in the experiment and in the analysis.     

MS6001B型燃气轮机的雾化空气系统的改造

分析了新港热电厂燃气轮机雾化空气系统主雾化空气压缩机花键联轴器扭断和辅助雾化空气压缩机驱动皮带屡屡跑偏的两起故障的原因及事后对雾化空气系统的分析和改造。     

MS6001和MS9001系列燃气轮机改烧天然气的基本情况介绍

扼要介绍了烧天然气的MS6001,MS9001系列燃气轮机的基本情况,同时介绍了将烧油的燃气轮机改成烧天然气所需要增加的设备。     

Coexisting phenomena of surge and rotating stall in an axial flow compressor

The unsteady inner flow structure of a single-stage axial flow compressor under the coexisting conditions of surge and rotating stall was experimentally investigated via detailed measurements of the unsteady characteristics and the internal flow velocity fluctuations. The main relevant feature of the tested compressor is a shock tube with a capacity tank connected in series to the compressor outlet through slits and a concentric duplex pipe： surge and rotating stall can both be generated by connecting the shock tube. Research attention is focused on the unsteady behavior of a rotating stall during the surge cycle. The size of the rotating stall cell during the recovery process of an irregular surge cycle was experimentally determined by the circumferential flow velocity fluctuations ahead of the rotor blade. The results suggested that the size of the rotating stall cell at the switching point of the performance curve between large and small cycles is considered to be the key parameter in determining the following surge cycle. In addition, the surge cycle is largely influenced by the unsteady behavior of the rotating stall cell.     

Unsteady behavior of surge and rotating stall in an axial flow compressor

Unsteady behaviors as well as unsteady cascade flow fields of a single-stage axial flow compressor were experimentally investigated by detail measurements of unsteady performance characteristics and casing wall pressure and internal flow velocity fluctuations. The main feature of the test compressor is a capacity tank connected directly to the compressor outlet in series through slits and a concentric duplex pipe, and also jet nozzles in order to inject compressed air toward the rotor tip region. Research attention is focused on the post-stall characteristics of surge and rotating stall which occur simultaneously. When the compressor was connected to the capacity tank, surge was generated with rotating stall in accordance with the capacitance increment of whole compressor system. The surge behavior changed irregularly with throttling valve installed behind the compressor, and several types of surge cycles were observed. In addition, the surge cycle changed by jet injection to the rotor tip region. The results suggested that the blockages of the cascade flow which were generated by a stall cell play an important role in deciding the surge behaviors.     

GT13D燃气轮机起动过程的常见故障及处理方法

对ABB公司GT13D燃机发电机组起动过程作了简要介绍,就起动过程中遇到的故障及相应的检查和处理方法进行了总结介绍,并根据保护逻辑关系,对其他一些可能存在的故障及应当采取的处理方法也进行了一些分析。     

Unsteady flow field under surge and rotating stall in a three-stage axial flow compressor

The unsteady flow structure between rotor blade-to-blade passages in a three-stage axial flow compressor is experimentally investigated by detailed measurements of unsteady performance characteristics,casing wall pressure fluctuations and their wavelet analyses.The main feature of the test compressor is a capacity tank facility connected in series to the compressor outlet in order to supply compression and/or expansion waves from downstream of the compressor.Research attention is focused on the post-stall characteristics of the surge and rotating stall which occur simultaneously.The influence of the compressor operating point on the unsteady performance curve shows that the surge cycle changes irregularly depending on the steady-state resistance characteristics,and the results of the wavelet analyses of the wall pressure fluctuations suggest that the surge cycle may selectively be determined by the rotating stall cell structure within the rotor cascade.     

Noise reduction and surge margin improvement using tapered diffuser vane in a centrifugal compressor

Improvement of surge margin and reduction of interaction tone noise radiated from a centrifugal compressor with a vaned diffuser is discussed from experiments and CFD analyses. Two types of one-side tapered diffuser vanes, which are shroud- and hub-side tapered vanes, were used in the experiments. The height of the leading edge of the tapered vanes varied from 100% to 10%. Both types of tapered vanes are effective for the reduction of the inter- action tone noise radiated from the compressor, because of the smaller interaction area between impel- ler-discharge flow and diffuser vane surface. Especially, the hub-side tapered diffuser vane suppresses the evolution of the leading-edge vortex, which causes reverse-flow in the diffuser passage. Furthermore, the hub-side tapered diffuser vane, which has an optimized diffuser leading edge shape, can improve the compressor pressure-rise characteristics at low-flow operation and can enlarge the surge margin.     

An experimental description of the flow in a centrifugal compressor from alternate stall to surge

The present paper gives the experimental results obtained in a centrifugal compressor stage designed and built by SAFRAN Helicopter Engines.The compressor is composed of inlet guide vanes,a backswept splittered unshrouded impeller,a splittered vaned radial diffuser and axial outlet guide vanes.Previous numerical simulations revealed a particular S-shape pressure rise characteristic at partial rotation speed and predicted an alternate flow pattern in the vaned radial diffuser at low mass flow rate.This alternate flow pattern involves two adjacent vane passages.One passage exhibits very low momentum and a low pressure recovery,whereas the adjacent passage has very high momentum in the passage inlet and diffuses efficiently.Experimental measurements confirm the S-shape of the pressure rise characteristic even if the stability limit experimentally occurs at higher mass flow than numerically predicted.At low mass flow the alternate stall pattern is confirmed thanks to the data obtained by high-frequency pressure sensors.As the compressor is throttled the path to instability has been registered and a first scenario of the surge inception is given.The compressor first experiences a steady alternate stall in the diffuser.As the mass flow decreases,the alternate stall amplifies and triggers the mild surge in the vaned diffuser.An unsteady behavior results from the interaction of the alternate stall and the mild surge.Finally,when the pressure gradient becomes too strong,the alternate stall blows away and the compressor enters into deep surge.