某燃气轮机压气机叶尖间隙的分析

设计合理的燃气轮机的叶尖间隙,一直是业内人士非常关注的问题.针对中国某改进型燃气轮机的压气机,在综合考虑材料热膨胀的影响、离心载荷作用下的径向应变、叶片轮盘和机匣的材料代用、轴承的游隙、以及弹性支撑等影响因素共同作用的前提下,通过对机组稳态和过渡态运行工况的叶尖间隙计算,最后给出了改进型压气机动/静转子间的安装间隙.     

Failure Analysis of Steam Turbine Rotor Disk

This article presents an investigation into causes of failure of rotor disk of an 8.25-MW capacity steam turbine, which failed catastrophically. Four pieces of the rotor disk detached from the tenth-stage disk of the turbine rotor during this failure. Visual inspection, chemical analysis, macro- and microscopic analysis of the failed rotor disk, analysis of the operational data, and the history of the rotor operation indicated that the failure could be attributed to stress concentrations at macropores and regions of segregation in the disk. Stress corrosion cracking (SCC) subsequently took place in the regions of stress concentration because the steam in the turbine contained chloride and potassium. The SCC produced a network of cracks associated with the macro- and microporosities. It was recommended that the disk fabrication processes ensure a high-quality microstructure and that operational monitoring of the composition of steam be initiated to ensure that the chlorides and potassium concentrations are maintained below a specified level.     

Failure Analysis of High-Pressure Compressor Blade in an Aero Gas Turbine Engine

Failure of high-pressure compressor rotor blade in an aero gas turbine engine is analyzed to determine its root cause. Forensic and metallurgical investigations are carried out on the blade and failed parts. The failure of the platform ladder is found to the first in the chain of events that led to the compressor blade failure. The mode of failure in the blade is found to be fatigue and has originated from the damaged region on the leading edge caused by dislodgement of platform ladder. The failure has caused extensive damages in high-pressure compressor module and also in downstream turbine blades as a secondary effect.     

Numerical Simulation and Technological Parameter Optimization for Quenching Process of a Gas Turbine Compressor Disk Based on Metallo-Thermo-Mechanics

Thermal, mechanical and microstructural phenomena are involved in the process of steel quenching. Based on the coupled metallo-thermo-mechanics theory, a calculation model has been developed in this study to simulate the quenching process of a gas turbine compressor disk by finite element method. The thermal physical and mechanical properties were treated as a functions of temperature. Moreover, a series of subroutines were developed on the MARC software platform. Consequently, simulated results on temperature, internal stress and distortion during the quenching were illustrated. With the aid of the simulated results, an optimum quenching scheme was proposed. The quenching process simulated in this study appears to be a promising tool in design of heat-treatment processing parameters for gas turbine compressor disks.     

Fatigue Failure of LP Compressor Blade in an Aero Gas Turbine Engine

Failure of low-pressure compressor rotor blade in an aero gas turbine engine is analyzed to determine its root cause. Forensic and metallurgical investigations are carried out on the blade failed. The failure of the first stage rotor blade is found to be the first in the chain of events that led to the engine failure. The mode of failure in the blade is found to be fatigue and has originated from the mounting lug fillet region due to high stress concentrations. The failure has caused extensive damages in low-pressure compressor module and also in downstream modules as a secondary effect. Remedial measures are also suggested to prevent such failures.     

Finite Element Approach for Failure Analysis of a Gas Turbine Blade

Journal of Failure Analysis and Prevention - In the present work, a case study on the gas turbine blade is undertaken for failure analysis through finite element approach. The analysis is carried...     

Failure Investigation of a Gas Turbine Inlet Weatherhood

Analytical and experimental methods have been used to investigate fatigue failures in the weatherhood protecting the air inlet to an offshore gas turbine power generation unit. A simple method for modelling transverse vibration of the leading edge is described, and the results are compared with experimental measurements made on a prototype installation. Calculation of the stresses induced at the critical locations, where cracking has been observed, suggests the failure should be attributed to aerodynamic excitation of the leading edge.     

Failure Analysis and Remedy Procedure for Cracking of Fuel Nozzles in a Gas Turbine

A common failure in a certain type of gas turbine, observed during the first periodic inspection, is radial cracks in the tip plate of gas fuel nozzles. Here, each gas turbine has 18 nozzles. In all nozzles and in all similar units, these cracks of lengths ranging from 1 mm to a maximum of 14.5 mm are observed. As prescribed by the manufacturer, the defective part must be removed and replaced by welding and machining of a new one. But this problem is repeated and observed in the next periodic visits, and in all units. Depending on the number of nozzles in each gas turbine unit and the number of units in total, these repairs are very expensive and time-consuming. In this paper, the failure is analyzed and the causes of the cracks in the nozzles are investigated. Studies show that the main causes of nozzle failure are residual stresses caused by welding and thermal stresses caused by the start-up and shutdown processes. According to results, a solution has been proposed to release these residual and thermal stresses. After the implementation of this method in 1998, no more failure has been reported by the repair team, which proves the effectiveness of this solution. Since this paper has been prepared based on technical reports from the years between 1996 and 1998, the cited references of this paper are these technical reports.     

Failure Analysis of Nozzle Guide Vane of a Low Pressure Turbine in an Aero Gas Turbine Engine

Failure of low pressure turbine nozzle guide vane (NGV) in an aero gas turbine engine is analyzed to determine its root cause. Forensic and metallurgical investigations are carried out on the NGV failed as well as the failed components of the downstream modules. Failure in the cooling system in the NGV due to crack in the sealing plate was found to be the cause of NGV getting burnt. This failure has caused extensive damages in low pressure turbine modules. Remedial measures are also suggested to prevent such failures.     

烟气轮机涡轮盘和叶片用WASPALOY合金研究

对烟气轮机涡轮盘和叶片用WASPALOY合金从合金成分特点、相析出规律、冶炼、加工和力学性能等方面进行了综述和讨论，重点介绍了该合金针对烟气轮机使用环境的合金设计特点及析出相特征，为烟气轮机用涡轮盘和叶片材料的发展给出研究方向。     

压缩机连杆断裂失效分析

某炼油厂焦化装置富气压缩机连杆发生断裂。采用化学成分分析、金相检验、力学性能测试和断口分析等方法对断裂连杆进行了分析。结果表明,在交变栽荷的作用下,连杆的小头孔内应力集中处产生微裂纹并成为裂纹源,然后发生裂纹扩展,最终导致连杆小头处发生疲劳断裂。     

Failure Prevention of Gas Turbine Blades Through Pack Aluminization

Pack aluminization of low-pressure turbine blade of an aero gas turbine engine has been carried out following a well-defined systematic procedure. The process parameters are first optimized on dummy blades, and optimized process is followed for the actual blades for evaluation and testing. Visual and binocular examination followed by metallurgical evaluation has been carried out to validate the process and to establish the adequacy and correctness of the coating. The coated blades are then evaluated through component-level test and engine-level test followed by field evaluation trials for performance and durability. The results of engine-level tests and inspection post-accelerated mission test cycles ensure that the blades with aluminide coating can withstand severe engine operating cycles without any damage or failure which otherwise would have experienced. The failure-free operation for an equivalent TBO life and post-AMT condition of blades are an indication of enhanced life of aluminide blades and prevention of failure of the turbine blades through pack aluminization.     

Analysis of Low-Pressure Turbine Nozzle Guide Vane Failure in an Aero Gas Turbine Engine: A Computational Approach

Journal of Failure Analysis and Prevention - Failure of low-pressure turbine nozzle guide vane (NGV) in an aero gas turbine engine is analyzed using computational approach. Breakage in the cooling...     

锅炉SNCR脱硝水冷壁管泄漏失效分析

采用宏微观分析、力学性能试验、化学成分分析、金相检验以及能谱、X射线衍射分析等方法,对某锅炉SNCR脱硝水冷壁管泄漏原因进行了分析。结果表明:该水冷壁管泄漏系在尿素腐蚀介质作用下产生的局部腐蚀穿孔所致;从脱硝喷枪泄漏的尿素液滴滴落在高温水冷壁管上和水冷壁管鳍片焊趾处的拉应力分别为水冷壁管的腐蚀泄漏提供了介质条件、温度条件和应力条件。     

压缩机十字头销断裂失效分析及预防

通过故障件材料的化学成分，宏观，微观断口，力学性能及受力状况分析，确定了甘压缩机十字头销疲劳断裂的模式、找到了造成断裂的主要原因，提出了防止断裂的有效措施。     

JT9D—7R4G2型发动机八级压气机盘及叶片失效原因分析

通过对失效的第八级压气机盘和叶片观察和金相分析，探讨了该失效件断裂的原因。结果表明，微动磨损引起疲劳断裂。