公开(公告)号：US20120200698A1

公开(公告)日：2012-08-09

申请号：US13023774

申请日：2011-02-09

申请人： Erwan Baleine ,  Danny M. Sheldon

发明人： Erwan Baleine ,  Danny M. Sheldon

IPC分类号： H04N7/18

CPC分类号： H04N7/18 ,  G01J5/00 ,  G01J5/0022 ,  G01J5/0088 ,  G01J5/02 ,  G01J5/025 ,  G01J5/08 ,  G01J5/0806 ,  G01J2005/0048 ,  G01J2005/0077 ,  G05B2219/37211 ,  G05B2219/37509

摘要： Method and system for calibrating a thermal radiance map of a turbine component in a combustion environment. At least one spot (18) of material is disposed on a surface of the component. An infrared (IR) imager (14) is arranged so that the spot is within a field of view of the imager to acquire imaging data of the spot. A processor (30) is configured to process the imaging data to generate a sequence of images as a temperature of the combustion environment is increased. A monitor (42, 44) may be coupled to the processor to monitor the sequence of images of to determine an occurrence of a physical change of the spot as the temperature is increased. A calibration module (46) may be configured to assign a first temperature value to the surface of the turbine component when the occurrence of the physical change of the spot is determined.

摘要翻译： 用于在燃烧环境中校准涡轮机部件的热辐射图的方法和系统。 至少一个材料点（18）设置在部件的表面上。 红外线（IR）成像器（14）被布置成使得该点位于成像器的视场内以获取该点的成像数据。 处理器（30）被配置为当燃烧环境的温度增加时，处理成像数据以产生图像序列。 监视器（42,44）可以耦合到处理器以监视图像序列，以确定当温度升高时点的物理变化的发生。 校准模块（46）可以被配置为当确定点的物理变化的发生时，将第一温度值分配给涡轮机部件的表面。

公开(公告)号：US08749629B2

公开(公告)日：2014-06-10

申请号：US13023774

申请日：2011-02-09

申请人： Erwan Baleine ,  Danny M. Sheldon

发明人： Erwan Baleine ,  Danny M. Sheldon

IPC分类号： H04N7/18

CPC分类号： H04N7/18 ,  G01J5/00 ,  G01J5/0022 ,  G01J5/0088 ,  G01J5/02 ,  G01J5/025 ,  G01J5/08 ,  G01J5/0806 ,  G01J2005/0048 ,  G01J2005/0077 ,  G05B2219/37211 ,  G05B2219/37509

摘要： Method and system for calibrating a thermal radiance map of a turbine component in a combustion environment. At least one spot (18) of material is disposed on a surface of the component. An infrared (IR) imager (14) is arranged so that the spot is within a field of view of the imager to acquire imaging data of the spot. A processor (30) is configured to process the imaging data to generate a sequence of images as a temperature of the combustion environment is increased. A monitor (42, 44) may be coupled to the processor to monitor the sequence of images of to determine an occurrence of a physical change of the spot as the temperature is increased. A calibration module (46) may be configured to assign a first temperature value to the surface of the turbine component when the occurrence of the physical change of the spot is determined.

摘要翻译： 用于在燃烧环境中校准涡轮机部件的热辐射图的方法和系统。 至少一个材料点（18）设置在部件的表面上。 红外线（IR）成像器（14）被布置成使得该点位于成像器的视场内以获取该点的成像数据。 处理器（30）被配置为当燃烧环境的温度增加时，处理成像数据以产生图像序列。 监视器（42,44）可以耦合到处理器以监视图像序列，以确定当温度升高时点的物理变化的发生。 校准模块（46）可以被配置为当确定点的物理变化的发生时，将第一温度值分配给涡轮机部件的表面。

公开(公告)号：US20150052980A1

公开(公告)日：2015-02-26

申请号：US13972203

申请日：2013-08-21

申请人： Danny M. Sheldon ,  Kristine A. Kushner ,  Trent Lewis ,  Dane J. Hurt

发明人： Danny M. Sheldon ,  Kristine A. Kushner ,  Trent Lewis ,  Dane J. Hurt

IPC分类号： G01M3/04

CPC分类号： G01M3/025 ,  G01M3/3209 ,  G01M3/3272

摘要： Internally shielded fuel passage orifices in nozzle rocket swirler airfoils are sealed with the pressure test tool. Pinch clamps on the test tool are introduced into the fuel nozzle rocket swirler. The clamps are tightened over the airfoil orifices to plug or otherwise seal them and their fuel passages within the nozzle assembly. The nozzle assembly fuel passages are subsequently pressurized. Pressure is monitored to determine whether the nozzle is properly sealed (i.e., no pressure decay) or whether it has a leak-causing structural defect. Pressure drop in the tested component during the test cycle is indicative of a leak, in the nozzle's fuel passages, caused for example by a structural defect in the component. The test system may also be utilized in conjunction with individual rocket swirlers that are not incorporated within a complete fuel nozzle assembly.

摘要翻译： 喷嘴火箭旋流器翼型中的内部屏蔽燃料通道孔口用压力测试工具密封。 测试工具上的夹紧夹具被引入燃料喷嘴火箭旋流器。 夹紧件紧固在翼型孔上，以将其和喷嘴组件内的燃料通道塞住或以其他方式密封。 喷嘴组件燃料通道随后被加压。 监测压力以确定喷嘴是否被适当地密封（即，没有压力衰减）或者其是否具有导致泄漏的结构缺陷。 在测试循环期间测试组件中的压降表示在喷嘴的燃料通道中由例如组件中的结构缺陷引起的泄漏。 测试系统还可以与不并入整个燃料喷嘴组件中的单个火箭旋流器结合使用。