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91. 发明授权

US09176024B2 Systems and methods for monitoring rotary equipment 有权
标题翻译：用于监测旋转设备的系统和方法
公开(公告)号：US09176024B2
公开(公告)日：2015-11-03
申请号：US14061650
申请日：2013-10-23
申请人： General Electric Company
发明人： Raymond Verle Jensen , Charles Terrance Hatch , Sean Kelly Summers
IPC分类号： G01M15/14 , G01L3/12 , G01L3/10 , G01L3/14 , G01M1/16 , G01P3/49
CPC分类号： G01M15/14 , F01D17/02 , F01D17/20 , F05D2220/31 , F05D2220/72 , G01H1/003 , G01H3/00 , G01H11/00 , G01L3/101 , G01L3/109 , G01L3/12 , G01L3/1435 , G01M1/16 , G01P3/49 , Y02T50/671
摘要： A system includes a first unitary measurement strip configured to be secured about a rotational component at a first axial location. The first unitary measurement strip includes a first set of one or more windows, each window of the first set of one or more windows is configured to correspond to a first respective tangential location of the rotational component at the first axial location, and each window of the first set of one or more windows is configured to be detectable via a first sensor.
摘要翻译：系统包括第一单元测量条，其被配置为在第一轴向位置处围绕旋转部件固定。第一单一测量条带包括第一组一个或多个窗口，一个或多个窗口的第一组的每个窗口被配置为对应于第一轴向位置处的旋转部件的第一相应切向位置，并且每个窗口第一组一个或多个窗口被配置成可以通过第一传感器检测。

92. 发明授权

US09157878B2 System and method for detecting aberrations in a conduit 有权
标题翻译：用于检测导管中的像差的系统和方法
公开(公告)号：US09157878B2
公开(公告)日：2015-10-13
申请号：US13648806
申请日：2012-10-10
申请人： THERMAL WAVE IMAGING, INC.
发明人： Steven M. Shepard
IPC分类号： G01N25/72 , G01N19/08 , G01M15/14
CPC分类号： G01N25/72 , G01M15/14 , G01N19/08
摘要： A system for detecting aberrations within a workpiece having a conduit with an input end and an output end is disclosed. The system comprises a fluid delivery device arranged proximate to input end of conduit to pass fluid into input end of the conduit, the fluid delivery device having one or more fluid controllers that control one or more conditions of the fluid passed thereby, a sensor having an input and an output, the input arranged proximate to output end of conduit to measure one or more conditions of the fluid experienced by input, a workpiece exciter situated to excite workpiece and a processor having an input connected to the output of sensor, the processor having a correlator to correlate any changed of the one or more conditions of the fluid experienced by input of sensor with an excitement of workpiece by sensor.
摘要翻译：公开了一种用于检测具有具有输入端和输出端的导管的工件内的像差的系统。该系统包括靠近导管的输入端设置的流体输送装置，以将流体传送到导管的输入端，流体输送装置具有一个或多个流体控制器，其控制通过的流体的一个或多个条件，输入端和输出端，所述输入端布置在导管的输出端附近，以测量由输入经受的流体的一个或多个条件，位于激发工件的工件激励器和具有连接到传感器的输出的输入的处理器，所述处理器具有相关器，用于将由传感器输入所经历的流体的一个或多个条件与传感器的工件兴奋相关联。

93. 发明申请

US20150268131A1 METHOD AND A DEVICE FOR NORMALIZING VALUES OF OPERATING PARAMETERS OF AN AEROENGINE 有权
标题翻译：方法和装置，用于标准化运行参数的值
公开(公告)号：US20150268131A1
公开(公告)日：2015-09-24
申请号：US14478286
申请日：2014-09-05
申请人： SNECMA
发明人： Aurelie GOUBY
IPC分类号： G01M15/14 , G07C3/02
CPC分类号： G01M15/14 , G05B23/0221 , G07C3/02
摘要： The normalization method comprises: normalizing a current value of each operating parameter relative to exogenous variables with the help of a first regression model defined on a space generated by the exogenous variables; associating the vector formed by the normalized current values of the parameters with at least one vector class of a set of predefined classes; using at least one second regression model defined on the space generated by the exogenous variables for said at least one class associated with the vector to construct for each parameter a third regression model onto said space; and normalizing the normalized current value of each parameter relative to the exogenous variables with the help of the third regression model.
摘要翻译：归一化方法包括：借助于由外生变量产生的空间定义的第一回归模型，对相对于外生变量的每个操作参数的当前值进行归一化; 将由参数的归一化电流值形成的矢量与一组预定义类别的至少一个矢量类相关联; 使用至少一个第二回归模型，所述至少一个第二回归模型在由所述至少一个与所述向量相关联的类别的所述外部变量生成的空间上定义，以对每个参数构建所述空间上的第三回归模型并借助于第三回归模型，使每个参数相对于外生变量的归一化电流值进行归一化。

94. 发明申请

US20150260557A1 NONINTRUSIVE PERFORMANCE MEASUREMENT OF A GAS TURBINE ENGINE IN REAL TIME 有权
标题翻译：实时发动机涡轮发动机的不间断性能测量
公开(公告)号：US20150260557A1
公开(公告)日：2015-09-17
申请号：US14341950
申请日：2014-07-28
申请人： Siemens Energy, Inc.
发明人： Upul P. DeSilva , Heiko Claussen
IPC分类号： G01F1/66 , G01F1/86 , G01M15/14
CPC分类号： G01F1/66 , G01F25/0007 , G01M15/14
摘要： Performance of a gas turbine engine is monitored by computing a mass flow rate through the engine. Acoustic time-of-flight measurements are taken between acoustic transmitters and receivers in the flow path of the engine. The measurements are processed to determine average speeds of sound and gas flow velocities along those lines-of-sound. A volumetric flow rate in the flow path is computed using the gas flow velocities together with a representation of the flow path geometry. A gas density in the flow path is computed using the speeds of sound and a measured static pressure. The mass flow rate is calculated from the gas density and the volumetric flow rate.
摘要翻译：通过计算通过发动机的质量流量来监测燃气涡轮发动机的性能。在发动机的流路中的声发射器和接收器之间进行飞行时间的测量。对这些测量进行处理，以确定沿声线的声音和气体流速的平均速度。使用气流速度以及流路几何形状的表示来计算流路中的体积流量。使用声速和测量静态压力计算流路中的气体密度。质量流量由气体密度和体积流量计算。

95. 发明授权

US09134198B2 Method and device for detecting a rotational separation adversely affecting a turbine engine compressor 有权
标题翻译：用于检测不利地影响涡轮发动机压缩机的旋转分离的方法和装置
公开(公告)号：US09134198B2
公开(公告)日：2015-09-15
申请号：US13808992
申请日：2011-07-04
申请人： Cedrik Djelassi
发明人： Cedrik Djelassi
IPC分类号： G01M15/14 , F01D17/02 , F01D21/02 , F02C9/16 , F04D27/00
CPC分类号： G01M15/14 , F01D17/02 , F01D21/02 , F02C9/16 , F04D27/001 , F05D2260/80 , F05D2270/10 , F05D2270/303 , F05D2270/304 , F05D2270/707
摘要： A method and device detecting a rotating stall affecting a turbine engine compressor. The detection method includes: detecting an abnormal acceleration of the engine or an operating line of the compressor that is characteristic of a failure of the engine; storing a reference temperature measured at an outlet from a turbine of the engine at an instant of detection; comparing a determined temperature threshold with the difference between a current temperature at the outlet of the turbine as measured after detection and the reference temperature; and identifying that a rotating stall is present in event of the threshold being exceeded.
摘要翻译：一种检测影响涡轮发动机压缩机的旋转档位的方法和装置。检测方法包括：检测发动机的异常加速度或发动机故障特征的压缩机的运转线; 在检测时刻存储在发动机的涡轮机的出口处测量的参考温度; 将确定的温度阈值与检测后测量的涡轮机出口处的当前温度与参考温度之间的差进行比较; 并且在超过阈值的情况下识别存在旋转失速。

96. 发明申请

US20150253221A1 FAULT DETECTION DEVICE AND FAULT DETECTION METHOD 有权
标题翻译：故障检测装置和故障检测方法
公开(公告)号：US20150253221A1
公开(公告)日：2015-09-10
申请号：US14432275
申请日：2013-09-24
申请人： HINO MOTORS, LTD.
发明人： Hitoshi Nakano
IPC分类号： G01M15/14 , F02B37/16 , G01F1/86
CPC分类号： G01M15/14 , F02B37/16 , F02B37/18 , F02B39/16 , F02D41/0007 , F02D41/18 , F02D41/221 , F02D2200/0402 , F02D2200/0406 , F02D2200/0414 , G01F1/86 , Y02T10/144 , Y02T10/40
摘要： A fault detection device includes a wastegate valve, a control unit, a working gas amount computation section, and a determination section. The control unit obtains a rotational speed of an engine, a boost pressure, and an intake air temperature. The working gas amount computation section computes a computed value of a mass flow rate of working gas in the engine by using the rotational speed, the boost pressure, and the intake air temperature. The determination section determines that the wastegate valve has a fault when the computed value is not a normal value.
摘要翻译：故障检测装置包括废气门阀，控制单元，工作气体量计算部件和判定部件。控制单元获得发动机的转速，增压压力和进气温度。工作气体量计算部使用旋转速度，增压压力和进气温度来计算发动机的工作气体的质量流量的计算值。当计算值不是正常值时，确定部分确定废气门阀具有故障。

97. 发明申请

US20150211380A1 TURBINE ENGINE COMPRISING A MEANS FOR MEASURING THE SPEED AND TORQUE OF A SHAFT OF THE TURBINE ENGINE AND METHOD FOR MONITORING SAID SHAFT 有权
标题翻译：涡轮发动机包括用于测量涡轮发动机轴的转速和扭矩的手段和用于监测上述轴的方法
公开(公告)号：US20150211380A1
公开(公告)日：2015-07-30
申请号：US14426147
申请日：2013-09-05
申请人： SNECMA
发明人： Augustin Curlier , Olivier Belmonte , Gilles Le Gouellec
IPC分类号： F01D21/00 , F01D1/18 , F01D25/24
CPC分类号： F01D21/003 , F01D1/18 , F01D25/24 , F02K3/025 , F05D2260/80 , F05D2270/304 , F05D2270/335 , F05D2270/809 , G01L3/105 , G01M15/14 , G01P3/488 , Y02T50/671
摘要： Turbine engine (1), in particular for an aircraft, comprising at least one axial shaft (2) rotatably mounted in a casing (3) of the turbine engine (1), the turbine engine (1) comprising an annular reference part (10) comprising short (11) and long (12) longitudinal reference teeth, first means for detecting the passage of the short (11) and long (12) reference teeth so as to measure the speed of the shaft (2) of the turbine engine (1) about its axis (X), an annular measurement part (20) comprising longitudinal measurement teeth (21); and second means for detecting the passage of the long reference teeth (12) and the measurement teeth (21) so as to measure the torque of the shaft (2, 102) of the turbine engine (1).
摘要翻译：涡轮发动机（1），特别是用于飞行器，包括可旋转地安装在涡轮发动机（1）的壳体（3）中的至少一个轴向轴（2），所述涡轮发动机（1）包括环形参考部分）包括短（11）和长（12）纵向参考齿，第一装置用于检测短（11）和长（12）基准齿的通过，以便测量涡轮发动机的轴（2）的速度（1）围绕其轴线（X），包括纵向测量齿（21）的环形测量部分（20）; 以及用于检测长参考齿（12）和测量齿（21）的通过以便测量涡轮发动机（1）的轴（2,102）的扭矩的第二装置。

98. 发明申请

US20150199805A1 METHOD OF DETERMINING THE LOCATION OF TIP TIMING SENSORS DURING OPERATION 有权
标题翻译：确定操作期间定时传感器位置的方法
公开(公告)号：US20150199805A1
公开(公告)日：2015-07-16
申请号：US14155606
申请日：2014-01-15
申请人： Siemens Energy, Inc.
发明人： Clifford Hatcher, JR. , Joseph M. Brindisi
IPC分类号： G06T7/00 , H04N7/18 , G01M15/14 , G04F13/02 , G01B11/26 , G01B11/14
CPC分类号： G06T7/004 , F01D21/003 , G01B11/16 , G01B11/26 , G01H1/006 , G01H3/00 , G01H9/004 , G01M15/14 , G04F13/02 , G06T7/70 , H04N7/18
摘要： A combination probe is positioned at a location in a stationary portion of a turbo machine that defines a gas flow path and is configured to detect a moving portion of the turbo machine within the gas flow path. The combination probe includes a tip timing sensor configured to sense when the moving portion is located proximate to the location of the probe, and an optical component configured to have a field of view that includes the moving portion when the moving portion is located proximate to the location of the probe. There is also an image capture device coupled to the optical component to capture an image of the field of view. The image can be used to determine the particular blade tip location within the field of view which is also the blade tip location sensed by the tip timing sensor.
摘要翻译：组合探针定位在限定气体流动路径的涡轮机的固定部分中的位置，并且构造成检测涡轮机在气体流动路径内的移动部分。组合探针包括尖端定时传感器，其被配置为感测移动部分何时位于探头的位置附近，以及光学部件，被配置为当移动部分位于接近于探针的位置时具有包括移动部分的视场探头位置。还存在耦合到光学部件以捕获视场图像的图像捕获装置。图像可以用于确定视场内的特定叶片尖端位置，其也是由尖端定时传感器感测的叶片尖端位置。

99. 发明申请

US20150168262A1 SINGLE CRYSTAL TURBINE BLADE LIFING PROCESS AND SYSTEM 审中-公开
标题翻译：单晶涡轮叶片生产过程和系统
公开(公告)号：US20150168262A1
公开(公告)日：2015-06-18
申请号：US14081923
申请日：2013-11-15
申请人： Solar Turbines Incorporated
发明人： Richard James Green , Jonathan Paul Douglas
IPC分类号： G01M15/14
CPC分类号： G01M15/14 , F01D5/28 , F05D2260/82 , F05D2300/607
摘要： A system and methods for lifing a single crystal turbine blade of a gas turbine engine is disclosed. The system and methods determine the anisotropic strain of the single crystal turbine blade caused by fatigue and creep by resolving the shear stresses on each of the primary slip systems of the single crystal turbine blade. The system and methods use a ductility exhaustion method to combine the anisotropic fatigue and creep strains to determine the operating life of the single crystal turbine blade.
摘要翻译：公开了一种用于升高燃气涡轮发动机的单晶涡轮叶片的系统和方法。该系统和方法通过解决单晶涡轮叶片的每个主滑动系统上的剪切应力来确定由疲劳和蠕变引起的单晶涡轮叶片的各向异性应变。该系统和方法采用延性耗尽方法组合各向异性疲劳和蠕变应变，以确定单晶轮机叶片的使用寿命。

100. 发明申请

US20150168229A1 ACTIVE TEMPERATURE MONITORING IN GAS TURBINE COMBUSTORS 有权
标题翻译：气体涡轮机主动温度监测
公开(公告)号：US20150168229A1
公开(公告)日：2015-06-18
申请号：US14132001
申请日：2013-12-18
申请人： Upul P. DeSilva
发明人： Upul P. DeSilva
IPC分类号： G01K11/24 , F02C3/04 , G01M15/14
CPC分类号： G01K11/24 , F01D17/085 , F02C3/04 , F05D2260/80 , F05D2270/09 , F05D2270/303 , G01F1/667 , G01K7/42 , G01K11/26 , G01K13/02 , G01K2013/024 , G01M15/14
摘要： Acoustic pyrometry-based active temperature monitoring of gas turbine combustors, including industrial gas turbine (IGT) combustors is incorporated into the combustion monitoring and control system by addition of an acoustic transmitter or acoustic transceiver that transmits a sound wave in a line-of-sight with a plurality of thermoacoustic sensors, such as dynamic pressure sensors. Sound transmission time-of-flight is measured by the controller and correlated with path temperature along the line-of-sight. Path(s) of acoustic transmission serve as absolute temperature measurement that optionally is used for calibrating dominant mode passive bulk temperature measurement. In an integrated thermoacoustic pressure-based sensor and monitoring/control system embodiment, the controller correlates performance of an combustion thermoacoustic properties in order to identify combustion anomalies by wavelet or Fourier analysis techniques, determine bulk temperature characteristics within the combustor with dominant mode frequency analysis techniques and determines absolute active path temperatures within the combustor with acoustic transmission and time-of-flight analysis techniques.
摘要翻译：包括工业燃气轮机（IGT）燃烧器在内的燃气轮机燃烧器的基于高温测量的主动温度监测通过添加在视线中传输声波的声发射器或声收发器而被并入到燃烧监测和控制系统中具有多个热声传感器，例如动态压力传感器。声音传输的飞行时间由控制器测量，并与视线的路径温度相关。声学传播的路径用作绝对温度测量，可选地用于校准主模式被动体温度测量。在基于集成热声压力的传感器和监控/控制系统实施例中，控制器将燃烧热声特性的性能相关联，以通过小波或傅里叶分析技术识别燃烧异常，以主模式频率分析技术确定燃烧室内的体温特性并利用声学传播和飞行时间分析技术确定燃烧室内的绝对主动路径温度。

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