公开(公告)号：US20150172566A1

公开(公告)日：2015-06-18

申请号：US14560843

申请日：2014-12-04

Applicant: United Technologies Corporation

Inventor： Charles W. Haldeman ,  Andrew Consiglio ,  Christopher J. Lehane ,  Mark F. Zelesky

IPC: H04N5/33 ,  H04N5/265 ,  G06T7/00

CPC classification number: H04N5/33 ,  G06T5/50 ,  G06T2207/10016 ,  G06T2207/10048 ,  G06T2207/20216 ,  G06T2207/30164 ,  H04N5/265

Abstract: A method for thermally imaging a moving workpiece of a gas turbine engine using long wavelength infrared (LWIR) images of the workpiece captured during operation of the gas turbine engine. The method comprises determining average pixel intensity and pixel variation in intensity for each pixel across the plurality of LWIR images, determining average area intensity and area variation in intensity across a range of areas defined by increasing length scales about a selected pixel, and identifying as a critical length scale a length scale at which area variation in intensity is minimized as a function of length scale, for which the area intensity remains substantially the same as the average pixel intensity of the selected pixel. A composite image is built such that each pixel of the composite image has intensity equal to an average area intensity centered on that pixel, over the critical length scale.

Abstract translation: 一种利用在燃气涡轮发动机运转期间捕获的工件的长波长红外（LWIR）图像对燃气涡轮发动机的移动工件进行热成像的方法。 该方法包括确定多个LWIR图像中的每个像素的平均像素强度和像素变化，确定通过增加关于所选像素的长度尺度所限定的区域范围内的强度的平均面积强度和面积变化，并将其识别为 临界长度刻度，其中强度的区域变化被最小化为长度尺度的函数的长度尺度，其面积强度保持与所选像素的平均像素强度基本相同。 构建合成图像，使得合成图像的每个像素的强度等于关键长度尺度上以该像素为中心的平均面积强度。

公开(公告)号：US20150172565A1

公开(公告)日：2015-06-18

申请号：US14560814

申请日：2014-12-04

Applicant: United Technologies Corporation

Inventor： Charles W. Haldeman ,  Andrew Consiglio ,  Christopher J. Lehane ,  Mark F. Zelesky

IPC: H04N5/33 ,  G06T7/60 ,  G06T11/60

CPC classification number: H04N5/33 ,  G06T5/50 ,  G06T7/33 ,  G06T2207/10016 ,  G06T2207/10048 ,  G06T2207/20221 ,  G06T2207/30164

Abstract: A method for thermally imaging a moving workpiece of a gas turbine engine comprises identifying a plurality of geometric features to construct a composite image. The geometric features include at least one integral thermal feature of the moving workpiece, and at least one artificial feature applied to the workpiece for diagnostic purposes. One of the plurality of geometric features is identified as a master feature, and the remainder of the plurality of geometric features are located relative to the master feature with relative actual coordinates. A pixel location of the master feature is identified or each image, and the remainder of the plurality of geometric features are located relative to the master feature with relative pixel coordinates. Offset, rotation, and scaling of the secondary images are varied to minimize a relative difference between the relative pixel coordinates and the relative actual coordinates. The offset, rotated, and scaled secondary images are combined with the reference image to form a composite image.

Abstract translation: 用于热成像燃气涡轮发动机的移动工件的方法包括识别多个几何特征以构造合成图像。 几何特征包括移动工件的至少一个整体热特征，以及至少一个人造特征，用于诊断目的。 多个几何特征中的一个被识别为主要特征，并且多个几何特征的其余部分相对于具有相对实际坐标的主要特征定位。 识别主要特征的像素位置或每个图像，并且多个几何特征的其余部分相对于具有相对像素坐标的主要特征位置。 改变次级图像的偏移，旋转和缩放以使相对像素坐标和相对实际坐标之间的相对差异最小化。 偏移，旋转和缩放的次级图像与参考图像组合以形成合成图像。

公开(公告)号：US10126175B2

公开(公告)日：2018-11-13

申请号：US14564774

申请日：2014-12-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Charles W. Haldeman ,  Andrew Consiglio ,  Mark F. Zelesky ,  Joel H. Wagner

IPC: G01J5/00 ,  G01K1/00 ,  F01D21/00 ,  F01D5/28 ,  F01D21/12

Abstract: A system includes a turbomachine having one or more inspection ports. An LWIR sensor is positioned in the inspection port of the turbomachine to sense thermal energy emitted by a turbomachine component. An imaging device can be operably connected to the LWIR sensor to convert signals from the LWIR sensor to a thermal image of the turbomachine component based on the sensed thermal energy. In some embodiments, the LWIR sensor configured to image a ceramic coated turbine blade.

公开(公告)号：US09983147B2

公开(公告)日：2018-05-29

申请号：US15057962

申请日：2016-03-01

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Shayan Ahmadian ,  Thomas J. Martin ,  Alexander Staroselsky ,  Charles W. Haldeman

IPC: G01N21/00 ,  G01N21/94 ,  G01M15/14 ,  G01N21/954 ,  G01N25/72 ,  G05B23/02 ,  G01J5/00

CPC classification number: G01N21/94 ,  G01J5/0022 ,  G01M15/14 ,  G01N21/954 ,  G01N25/72 ,  G05B23/024

Abstract: A system and method for prognostic health monitoring of thermal barrier coatings is provided. The system may comprise monitoring a thermal barrier coated gas turbine engine component, and measuring the infrared radiation emitting from the component. The measured thermal radiation data may be analyzed and compared to known material thermal radiation data in order to determine the health of the thermal barrier coating. The compiled comparison results may be compared against a historical statistical study to then determine the overall health of the thermal barrier coating. The system may comprise generating a health monitoring alert in response to the health of the thermal barrier coating indicating an imminent failure.

公开(公告)号：US09116051B2

公开(公告)日：2015-08-25

申请号：US14134603

申请日：2013-12-19

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Charles W. Haldeman

IPC: G01K1/12 ,  G01D11/24 ,  G01K13/02

CPC classification number: G01K1/12 ,  G01D11/245 ,  G01K13/02 ,  G01K2013/024

Abstract: An actively cooled turbine sensor assembly is designed to withstand post-combustion gas-path conditions of gas turbine engines. The housing forms part of a cooling system and includes an elongated tubular structure that may be inserted into the hot flow path. The distal end portion of the sensor assembly is contoured to minimize heat transfer. The housing also includes leading and trailing plenums for flowing cooling air through the housing and out through the distal end portion. Additional side cavities may also be provided for active cooling of the sensor and reducing possible heat conduction paths to the sensor.

Abstract translation: 主动冷却的涡轮传感器组件被设计成能够承受燃气涡轮发动机的燃烧后气体路径状况。 壳体形成冷却系统的一部分并且包括可以插入到热流路中的细长管状结构。 传感器组件的远端部分的轮廓是使热传递最小化。 壳体还包括用于使冷却空气流过壳体并通过远​​端部分流出的前部和后部气室。 还可以提供附加的侧腔，用于主动冷却传感器并减少可能的传导通路。

公开(公告)号：US20140254631A1

公开(公告)日：2014-09-11

申请号：US14134603

申请日：2013-12-19

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Charles W. Haldeman

IPC: G01K1/12 ,  G01D11/24

CPC classification number: G01K1/12 ,  G01D11/245 ,  G01K13/02 ,  G01K2013/024

Abstract: An actively cooled turbine sensor assembly is designed to withstand post-combustion gas-path conditions of gas turbine engines. The housing forms part of a cooling system and includes an elongated tubular structure that may be inserted into the hot flow path. The distal end portion of the sensor assembly is contoured to minimize heat transfer. The housing also includes leading and trailing plenums for flowing cooling air through the housing and out through the distal end portion. Additional side cavities may also be provided for active cooling of the sensor and reducing possible heat conduction paths to the sensor.

Abstract translation: 主动冷却的涡轮传感器组件被设计成能够承受燃气涡轮发动机的燃烧后气体路径状况。 壳体形成冷却系统的一部分并且包括可以插入到热流路中的细长管状结构。 传感器组件的远端部分的轮廓是使热传递最小化。 壳体还包括用于使冷却空气流过壳体并通过远​​端部分流出的前部和后部气室。 还可以提供附加的侧腔，用于主动冷却传感器并减少可能的传导通路。