公开(公告)号：EP2390471B1

公开(公告)日：2016-11-02

申请号：EP11167813.2

申请日：2011-05-27

Applicant: General Electric Company

Inventor： Badami, Vivek Venugopal

IPC: F01D21/00 ,  G05B23/02 ,  F04D27/00 ,  F04D27/02

CPC classification number: F01D21/003 ,  F04D27/001 ,  F04D27/0292 ,  F05D2260/80 ,  G05B23/021 ,  G05B23/0221

公开(公告)号：EP2848776A2

公开(公告)日：2015-03-18

申请号：EP14184199.9

申请日：2014-09-10

Applicant: General Electric Company

Inventor： Yu, Lijie ,  Ansari, Adil ,  Badami, Vivek Venugopal ,  Bliss, John Thomas ,  Chadha, Rahul ,  Gupta, Rajan

IPC: F01D21/00 ,  F01D21/14

CPC classification number: F04D27/001 ,  F01D21/00 ,  F01D21/003 ,  F01D21/04 ,  F01D21/10 ,  F01D21/14 ,  F02C9/00 ,  F03D17/00 ,  F04D29/324 ,  F05D2260/80 ,  F05D2260/81 ,  G01B7/14 ,  G01B11/14 ,  G01B21/16 ,  G01D21/00 ,  G06F17/40 ,  G06F19/00

Abstract: A system 2 including: at least one computing device 120 configured to monitor a compressor blade 10 in a turbomachine 5 by: extracting time of arrival (TOA) data about the compressor blade 10 at a defined interval; correlating turbomachine operating conditions with the TOA data; extracting resonance data about the compressor blade 10 during startup or shutdown of the turbomachine 5, and extracting static deflection and tip clearance data about the compressor blade 10 during steady state operation of the turbomachine 5; creating a baseline compressor blade comparison level based upon the extracted resonance data, extracted static deflection and tip clearance data, and correlation between the turbomachine operating conditions and the TOA data; and iteratively extracting updated TOA data and performing the correlating, the extracting of the resonance data, static deflection and tip clearance data using the updated TOA data at the defined interval to create an updated baseline compressor blade comparison level.
Corresponding computer program product with a program code executed by such a computing device.

Abstract translation: 系统2包括：至少一个计算设备120，被配置为通过以下定义的间隔提取关于压缩机叶片10的到达时间（TOA）数据来监测涡轮机5中的压缩机叶片10. 将涡轮机操作条件与TOA数据相关联; 在涡轮机5的启动或关闭期间提取关于压缩机叶片10的共振数据，以及在涡轮机5的稳态操作期间提取关于压缩机叶片10的静态偏转和叶尖间隙数据; 基于提取的共振数据，提取的静态偏转和尖端间隙数据以及涡轮机操作条件和TOA数据之间的相关性来创建基准压缩机叶片比较水平; 并且迭代地提取更新的TOA数据并且以所定义的间隔执行关联，提取共振数据，静态偏转和提前间隙数据，以创建更新的基线压缩机叶片比较水平。 具有由这种计算设备执行的程序代码的相应的计算机程序产品。

公开(公告)号：EP2402563A2

公开(公告)日：2012-01-04

申请号：EP11171242.8

申请日：2011-06-23

Applicant: General Electric Company

Inventor： Rajagopalan, Venkatesh ,  Badami, Vivek Venugopal ,  Prabhu, Rahul Srinivas ,  Behera, Ajay Kumar ,  Bhattacharya, Aninda

IPC: F01D21/00

CPC classification number: F01D21/003 ,  F05D2260/80

Abstract: A method for monitoring the health of one or more blades (12) is presented. The method includes steps of determining (106) a delta TOA corresponding to each of the one or more blades (12) based upon respective actual time of arrival (TOA) of the one or more blades (12), determining (320) a normalized delta TOA corresponding to each of the one or more blades (12) by removing effects of one or more operational data from the delta TOA, and determining (330) a corrected delta TOA corresponding to each of the one or more blades by removing effects of reseating of the one or more blades from the normalized delta TOA.

Abstract translation: 提出了一种用于监测一个或多个叶片（12）的健康状况的方法。 该方法包括以下步骤：基于相应的一个或多个刀片（12）的实际到达时间（TOA）来确定（106）对应于所述一个或多个刀片（12）中的每一个的增量TOA，确定（320）归一化 通过从三角洲TOA中移除一个或多个操作数据的影响，对应于所述一个或多个叶片（12）中的每一个的三角洲TOA，以及通过去除所述一个或多个叶片中的每一个叶片的影响来确定（330） 从归一化的三角洲TOA重新生成一个或多个刀片。

公开(公告)号：EP2402562A2

公开(公告)日：2012-01-04

申请号：EP11171241.0

申请日：2011-06-23

Applicant: General Electric Company

Inventor： Rajagopalan, Venkatesh ,  Badami, Vivek Venugopal ,  Prabhu, Rahul Srinivas ,  Behera, Ajay Kumar ,  Bhattacharya, Aninda

IPC: F01D21/00

CPC classification number: F01D21/003 ,  F05D2260/80 ,  G01H1/006 ,  G01M15/14

Abstract: A method for monitoring the health of a plurality of blades 12 is presented. The method includes the steps of determining 106 delta TOAs corresponding to the plurality of blades 12, determining 404 a standard deviation utilizing the delta TOAs corresponding to the plurality of blades; determining 412 a delta sigma_1 utilizing the standard deviation and an initial standard deviation, determining 414 a normalized delta TOA corresponding to one or more of the plurality of blades utilizing the delta sigma_1, determining 416 a standard deviation of the normalized delta TOA, determining 418 a delta sigma_2 utilizing the standard deviation of the normalized delta TOA and a previous standard deviation of normalized delta TOA, and determining 418 a corrected delta TOA corresponding to the one or more of the plurality of blades based upon the delta sigma_2.

Abstract translation: 提出了一种用于监测多个叶片12的健康状况的方法。 该方法包括以下步骤：确定对应于多个叶片12的106个三角形TOA，使用与多个叶片对应的增量TOA确定404标准偏差; 使用所述标准偏差和初始标准偏差来确定412Δigma_1，使用所述delta sigma_1确定414对应于所述多个叶片中的一个或多个的归一化增量TOA，确定416所述归一化三角洲TOA的标准偏差，确定418a ΔΣ_2利用归一化的三角洲TOA的标准偏差和归一化的三角洲TOA的先前的标准偏差，并且基于ΔΣ_2确定418对应于多个叶片中的一个或多个的校正的ΔAAD。

公开(公告)号：EP2390471A2

公开(公告)日：2011-11-30

申请号：EP11167813.2

申请日：2011-05-27

Applicant: General Electric Company

Inventor： Badami, Vivek Venugopal

IPC: F01D21/00 ,  G05B23/02

CPC classification number: F01D21/003 ,  F04D27/001 ,  F04D27/0292 ,  F05D2260/80 ,  G05B23/021 ,  G05B23/0221

Abstract: In one embodiment, a blade monitoring system (120) includes: at least one computing device configured to monitor a compressor (4) during a load change by performing actions comprising: extracting a dynamic component of a blade time-of-arrival (TOA) deviation signal in response to the load change on the compressor (4); calculating, using the dynamic component, at least one of: a natural frequency of the GT compressor blade (10) during the load change, an overshoot of the GT compressor blade (10) during the load change, a rise time of the compressor blade during the load change, a damping factor of the compressor blade during the load change, or a settling time of the GT compressor blade (10) after the load change; and determining whether the GT compressor blade (10) is damaged based upon the at least one of: the natural frequency, the overshoot, the rise time, the damping factor, or the settling time.

Abstract translation: 在一个实施例中，刀片监控系统（120）包括：至少一个计算设备，被配置为通过执行动作来监视压缩机（4），所述动作包括：提取刀片到达时间（TOA）的动态分量， 响应于压缩机（4）上的负载变化的偏差信号; 计算使用动态分量中的至少一个：负载变化期间GT压缩机叶片（10）的固有频率，负载变化期间GT压缩机叶片（10）的过冲，压缩机叶片（10）的上升时间 在负载变化期间，负载变化时的压缩机叶片的阻尼系数，或负荷变化后的GT压缩机叶片（10）的稳定时间; 以及基于固有频率，过冲，上升时间，阻尼因子或建立时间中的至少一个来确定GT压缩机叶片（10）是否损坏。

公开(公告)号：EP2728331B1

公开(公告)日：2018-05-30

申请号：EP13189169.9

申请日：2013-10-17

Applicant: General Electric Company

Inventor： Prabhu, Rahul Srinivas ,  Balasubramaniam, Mahalakshmi Shunmugam ,  Behera, Ajay Kumar ,  Bhattacharya, Aninda ,  Rajagopalan, Venkatesh ,  D'Souza, Prashanth ,  Badami, Vivek Venugopal

IPC: G01M5/00 ,  G01B7/14

CPC classification number: G01M5/0083 ,  G01B7/14 ,  G01M5/0091

Abstract: A system is disclosed. The system includes a processing subsystem 16 that determines preliminary voltages corresponding to a plurality of blades 12 based upon blade passing signals (BPS) 24, and generates a plurality of clearance values by normalizing the preliminary voltages for effects of one or more operational parameters, wherein the plurality of clearance values are representative of clearance of the plurality of blades 12.

公开(公告)号：EP2423659B1

公开(公告)日：2016-03-23

申请号：EP11176781.0

申请日：2011-08-08

Applicant: General Electric Company

Inventor： Baik, Sanghum ,  Badami, Vivek Venugopal ,  Potdar, Yogesh Kesrinath ,  Loghin, Adrian G. ,  Sheng, Nuo

IPC: G06F17/50 ,  G01M5/00

CPC classification number: G01M5/0016 ,  G01M5/0033 ,  G01M5/0066 ,  G06F17/50 ,  G06F17/5009 ,  G06F17/5018

公开(公告)号：EP2402563B1

公开(公告)日：2016-03-02

申请号：EP11171242.8

申请日：2011-06-23

Applicant: General Electric Company

Inventor： Rajagopalan, Venkatesh ,  Badami, Vivek Venugopal ,  Prabhu, Rahul Srinivas ,  Behera, Ajay Kumar ,  Bhattacharya, Aninda

IPC: F01D21/00

CPC classification number: F01D21/003 ,  F05D2260/80

公开(公告)号：EP2402563A3

公开(公告)日：2012-07-11

申请号：EP11171242.8

申请日：2011-06-23

Applicant: General Electric Company

Inventor： Rajagopalan, Venkatesh ,  Badami, Vivek Venugopal ,  Prabhu, Rahul Srinivas ,  Behera, Ajay Kumar ,  Bhattacharya, Aninda

IPC: F01D21/00

CPC classification number: F01D21/003 ,  F05D2260/80

Abstract: A method for monitoring the health of one or more blades (12) is presented. The method includes steps of determining (106) a delta TOA corresponding to each of the one or more blades (12) based upon respective actual time of arrival (TOA) of the one or more blades (12), determining (320) a normalized delta TOA corresponding to each of the one or more blades (12) by removing effects of one or more operational data from the delta TOA, and determining (330) a corrected delta TOA corresponding to each of the one or more blades by removing effects of reseating of the one or more blades from the normalized delta TOA.

公开(公告)号：EP2423659A1

公开(公告)日：2012-02-29

申请号：EP11176781.0

申请日：2011-08-08

Applicant: General Electric Company

Inventor： Baik, Sanghum ,  Badami, Vivek Venugopal ,  Potdar, Yogesh Kesrinath ,  Loghin, Adrian G. ,  Sheng, Nuo

IPC: G01M5/00

CPC classification number: G01M5/0016 ,  G01M5/0033 ,  G01M5/0066 ,  G06F17/50 ,  G06F17/5009 ,  G06F17/5018

Abstract: Methods, systems and computer program products for assessing residual life of an airfoil, which would experience high cycle fatigue failure under at- or near-resonance vibration condition, are provided. The method includes receiving, at a processing system, at least one vibration response parameter associated with the airfoil. The method processes at least one cracked airfoil finite element model. Processing the cracked airfoil finite element model includes accessing the cracked airfoil finite element model, computing a modal stress intensity factor (SIF) of the cracked airfoil finite element model using fracture mechanics based finite element analysis, and computing a vibratory SIF based, at least in part, on the modal SIF and the at least one vibration response parameter. The method then computes a residual life indicator of the airfoil based, at least in part, on the vibratory SIF.

Abstract translation: 提供了用于评估机翼的剩余寿命的方法，系统和计算机程序产品，其将在共振或近共振的振动条件下经历高循环疲劳失效。 所述方法包括在处理系统处接收与所述翼型相关联的至少一个振动响应参数。 该方法处理至少一个裂纹翼型有限元模型。 加工裂纹翼型有限元模型包括进入破裂翼型有限元模型，利用基于有限元分析的断裂力学计算破裂翼型有限元模型的模态应力强度因子（SIF），并计算振动SIF，至少在 部分，对模态SIF和至少一个振动响应参数。 该方法然后至少部分地基于振动SIF计算翼型件的残余寿命指示符。