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101. 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。

102. 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。

103. 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。

104. 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。

105. 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。

106. 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。

107. 发明申请

US20150168228A1 MULTI FUNCTIONAL SENSOR SYSTEM FOR GAS TURBINE COMBUSTION MONITORING AND CONTROL 有权
标题翻译：用于气体涡轮机燃烧监测和控制的多功能传感器系统
公开(公告)号：US20150168228A1
公开(公告)日：2015-06-18
申请号：US14109992
申请日：2013-12-18
申请人： Upul P. DeSilva
发明人： Upul P. DeSilva
IPC分类号： G01K11/22 , G01K11/24 , G01M15/14
CPC分类号： G01K11/22 , F23N5/10 , F23N5/16 , F23N2023/00 , F23N2025/08 , F23N2041/20 , F23R3/44 , G01K11/24 , G01M15/14
摘要： Thermoacoustic sensors, such as dynamic pressure sensors, in the combustor measure vibratory responses of the combustor. An integrated monitoring and control system controller correlates sensor readings with 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 optionally determines absolute active path temperatures within the combustor with acoustic pyrometry transmission and time-of-flight analysis techniques. In some embodiments all of the monitoring functions are performed with a commonly shared array of thermoacoustic sensors that function as both combustion dynamics thermoacoustic vibration/wave receivers and acoustic transmitters. The monitored combustion properties are used for controlling gas turbine combustion.
摘要翻译：燃烧器中的热声传感器，例如动态压力传感器测量燃烧器的振动响应。综合监测和控制系统控制器将传感器读数与燃烧热声性质相关联，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; 并且可选地使用声学高温测量传输和飞行时间分析技术来确定燃烧室内的绝对主动路径温度。在一些实施例中，所有的监视功能都用共同共享的热声传感器阵列执行，这些热声传感器用作燃烧动力学热声振动/波接收器和声发射器。监测的燃烧特性用于控制燃气轮机燃烧。

108. 发明申请

US20150168139A1 METHOD AND APPARATUS FOR DETERMINING GAS TURBINE DAMPENING CONE INNER DIAMETER 有权
标题翻译：用于确定气体涡轮减震内锥直径的方法和装置
公开(公告)号：US20150168139A1
公开(公告)日：2015-06-18
申请号：US14105251
申请日：2013-12-13
申请人： Praveen J. Matlapudi
发明人： Praveen J. Matlapudi
IPC分类号： G01B21/14 , G01M15/14
CPC分类号： G01B21/14 , F01D5/10 , F01D25/285 , G01B5/12 , G01M15/14
摘要： Gas turbine engine generally ring-shaped dampening cone inner diameters, including those having spherical or other convex inner diameter surface profiles, are determined with a fixture including a displacement indicator having an axis of displacement in alignment with a locating pin. The dampening cone inner diameter surface is placed in contact with the locating pin on one side and a displacement point on the other side, so that the dampening cone inner diameter surface circumscribes a contact surface formed on the locating pin and the displacement point. The indicator displacement is correlated with the dampening cone inner diameter.
摘要翻译：包括具有球形或其它凸形内径表面轮廓的那些通常为环形阻尼锥体内径的燃气涡轮发动机由包括具有与定位销对准的位移轴线的位移指示器的夹具来确定。阻尼锥内径表面与一侧的定位销和另一侧的位移点接触，使润滑锥体内径表面限制形成在定位销和位移点上的接触面。指标位移与阻尼锥内径相关。

109. 发明申请

US20150159867A1 System and Method for Assessing Combustor Health During Operation 审中-公开
标题翻译：运行期间燃烧器健康评估系统和方法
公开(公告)号：US20150159867A1
公开(公告)日：2015-06-11
申请号：US14097549
申请日：2013-12-05
申请人： General Electric Company
发明人： Romano Patrick , Matthew Francis Lemmon , Subrat Nanda , Jonathan David White
IPC分类号： F23M11/00 , G01M15/14 , F23N1/00
CPC分类号： F23M11/00 , F23N1/00 , F23N2025/04 , F23N2041/20 , G01M15/14
摘要： A system for assessing combustor health during operation of the combustor includes a combustor, a sensor configured to sense combustion dynamics pressure data from the combustor, and a computing device that is in communication with the sensor and configured to receive the combustion dynamics pressure data from the sensor. The computing device is programed to extract a feature from the combustion dynamics pressure data and generate feature values for the feature over a period of time. The computing device is also programmed to generate a cumulative form of the feature that is based on the feature values over a time series and to compare the cumulative form to a historical cumulative form.
摘要翻译：用于在燃烧器运行期间评估燃烧器健康的系统包括燃烧器，被配置为感测来自燃烧器的燃烧动力学压力数据的传感器，以及与传感器连通并被配置为从燃烧器接收来自燃烧器的燃烧动态压力数据的计算装置传感器。编程计算设备以从燃烧动态压力数据中提取特征并且在一段时间内生成特征的特征值。计算设备还被编程为生成基于时间序列上的特征值的特征的累积形式，并将累积形式与历史累积形式进行比较。

110. 发明授权

US09032785B1 Method for making measurements of the post-combustion residence time in a gas turbine engine 有权
标题翻译：用于测量燃气涡轮发动机中的燃烧后停留时间的方法
公开(公告)号：US09032785B1
公开(公告)日：2015-05-19
申请号：US13534870
申请日：2012-06-27
申请人： Jeffrey H Miles
发明人： Jeffrey H Miles
IPC分类号： F01D21/04 , G01M15/14 , F01D21/00
CPC分类号： G01M15/14 , F01D21/003 , F23N5/00 , F23N2025/06 , F23N2041/20
摘要： A system and method of measuring a residence time in a gas-turbine engine is provided, whereby the method includes placing pressure sensors at a combustor entrance and at a turbine exit of the gas-turbine engine and measuring a combustor pressure at the combustor entrance and a turbine exit pressure at the turbine exit. The method further includes computing cross-spectrum functions between a combustor pressure sensor signal from the measured combustor pressure and a turbine exit pressure sensor signal from the measured turbine exit pressure, applying a linear curve fit to the cross-spectrum functions, and computing a post-combustion residence time from the linear curve fit.
摘要翻译：提供了一种测量燃气涡轮发动机中的停留时间的系统和方法，由此该方法包括将压力传感器放置在燃气轮机的燃烧器入口和涡轮机出口处并测量燃烧室入口处的燃烧器压力，涡轮机出口处的涡轮机出口压力。该方法还包括计算来自测量的燃烧器压力的燃烧器压力传感器信号与来自测量的涡轮机出口压力的涡轮机出口压力传感器信号之间的交叉频谱功能，对交叉频谱功能应用线性曲线拟合，以及计算柱 - 燃烧停留时间从线性曲线拟合。

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