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公开(公告)号：US10400620B2
公开(公告)日：2019-09-03
申请号：US15228664
申请日：2016-08-04
Applicant: United Technologies Corporation
Inventor： Lubomir A. Ribarov , Charles W. Haldeman
Abstract: Controlling BOAS-to-blade-tip clearances by measuring a blade clearance between a first primary BOAS and a blade with a distance measurement device attached to the first primary BOAS, determining if the measured blade clearance of the first primary BOAS is at a value corresponding to a first predetermined blade clearance, measuring a blade clearance of a first secondary BOAS that is circumferentially adjacent the first primary BOAS based on a position of the first primary BOAS when the blade clearance of the first primary BOAS is at the first predetermined blade clearance, determining if the measured blade clearance of the first secondary BOAS is at a value corresponding to the first predetermined blade clearance, and adjusting the position of the first secondary BOAS when the blade clearance of the first secondary BOAS is not at the first predetermined blade clearance with an actuator operably connected to the first secondary BOAS.
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公开(公告)号：US20170211408A1
公开(公告)日：2017-07-27
申请号：US15002724
申请日：2016-01-21
Applicant: United Technologies Corporation
Inventor： Shayan Ahmadian , Charles W. Haldeman , Mark F. Zelesky , Christopher T. Bergman , Sebastian Martinez
Abstract: A turbine section according to an example of the present disclosure includes, among other things, a component including a coating on a substrate, and at least one sensor positioned a distance from the component, the at least one sensor configured to detect radiation emitted from at least one localized region of the coating at a first wavelength and configured to detect radiation emitted from the substrate corresponding to the at least one localized region at a second, different wavelength. The first wavelength and the second wavelength are utilized to determine a heat flux relating to the at least one localized region. A method of measuring a gas turbine engine component is also disclosed.
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公开(公告)号：US20150160097A1
公开(公告)日：2015-06-11
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
CPC classification number: G01J5/0088 , F01D5/284 , F01D5/288 , F01D21/003 , F01D21/12 , F05D2260/80 , G01J5/0022 , G01J5/0066 , G01J2005/0077
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.
Abstract translation: 一种系统包括具有一个或多个检查端口的涡轮机。 LWIR传感器位于涡轮机的检查口中，以感测涡轮机组件发出的热能。 成像装置可以可操作地连接到LWIR传感器，以基于感测的热能将来自LWIR传感器的信号转换成涡轮机组件的热图像。 在一些实施例中，LWIR传感器被配置成对陶瓷涂覆的涡轮叶片进行成像。
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公开(公告)号：US10358936B2
公开(公告)日：2019-07-23
申请号：US15201716
申请日：2016-07-05
Applicant: United Technologies Corporation
Inventor： Bruce Hockaday , Charles W. Haldeman
IPC: F01D19/02 , F01D21/06 , F01D5/12 , F01D11/08 , F01D21/00 , F02C7/26 , G01B21/16 , F01D25/34 , F02C7/262
Abstract: According to an aspect, a bowed rotor sensor system for a gas turbine engine is provided. The bowed rotor sensor system includes a bowed rotor sensor operable to transmit a sensing field in an observation region and receive a signal indicative of a gap between an air seal and a blade tip within the gas turbine engine. The bowed rotor sensor system also includes a controller operable to monitor a plurality of gap data from the bowed rotor sensor indicative of the gap between the air seal and the blade tip of a plurality of blades passing through the observation region and determine a bowed rotor status of the gas turbine engine based on the gap data.
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公开(公告)号：US20180038238A1
公开(公告)日：2018-02-08
申请号：US15228664
申请日：2016-08-04
Applicant: United Technologies Corporation
Inventor： Lubomir A. Ribarov , Charles W. Haldeman
CPC classification number: F01D11/20 , F01D5/12 , F01D11/22 , F01D17/02 , F01D21/003 , F05D2220/32 , F05D2240/11 , F05D2240/307 , F05D2270/44 , F05D2270/62 , F05D2270/66 , F05D2270/80 , F05D2270/821 , Y02T50/671
Abstract: Controlling BOAS-to-blade-tip clearances by measuring a blade clearance between a first primary BOAS and a blade with a distance measurement device attached to the first primary BOAS, determining if the measured blade clearance of the first primary BOAS is at a value corresponding to a first predetermined blade clearance, measuring a blade clearance of a first secondary BOAS that is circumferentially adjacent the first primary BOAS based on a position of the first primary BOAS when the blade clearance of the first primary BOAS is at the first predetermined blade clearance, determining if the measured blade clearance of the first secondary BOAS is at a value corresponding to the first predetermined blade clearance, and adjusting the position of the first secondary BOAS when the blade clearance of the first secondary BOAS is not at the first predetermined blade clearance with an actuator operably connected to the first secondary BOAS.
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Patent Agency Ranking
公开(公告)号：US20180010480A1
公开(公告)日：2018-01-11
申请号：US15201716
申请日：2016-07-05
Applicant: United Technologies Corporation
Inventor： Bruce Hockaday , Charles W. Haldeman
CPC classification number: F01D21/06 , F01D5/12 , F01D11/08 , F01D19/02 , F01D21/003 , F01D25/34 , F02C7/26 , F02C7/262 , F05D2220/32 , F05D2260/85 , F05D2270/304 , F05D2270/804 , G01B21/16
Abstract: According to an aspect, a bowed rotor sensor system for a gas turbine engine is provided. The bowed rotor sensor system includes a bowed rotor sensor operable to transmit a sensing field in an observation region and receive a signal indicative of a gap between an air seal and a blade tip within the gas turbine engine. The bowed rotor sensor system also includes a controller operable to monitor a plurality of gap data from the bowed rotor sensor indicative of the gap between the air seal and the blade tip of a plurality of blades passing through the observation region and determine a bowed rotor status of the gas turbine engine based on the gap data.
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公开(公告)号：US20170254761A1
公开(公告)日：2017-09-07
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: G01N21/94 , G01M15/14 , G01N21/954
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.
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公开(公告)号：US10815817B2
公开(公告)日：2020-10-27
申请号：US15002724
申请日：2016-01-21
Applicant: United Technologies Corporation
Inventor： Shayan Ahmadian , Charles W. Haldeman , Mark F. Zelesky , Christopher T. Bergman , Sebastian Martinez
Abstract: A turbine section according to an example of the present disclosure includes, among other things, a component including a coating on a substrate, and at least one sensor positioned a distance from the component, the at least one sensor configured to detect radiation emitted from at least one localized region of the coating at a first wavelength and configured to detect radiation emitted from the substrate corresponding to the at least one localized region at a second, different wavelength. The first wavelength and the second wavelength are utilized to determine a heat flux relating to the at least one localized region. A method of measuring a gas turbine engine component is also disclosed.
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公开(公告)号：US09832396B2
公开(公告)日：2017-11-28
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
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.
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公开(公告)号：US09706140B2
公开(公告)日：2017-07-11
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
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.
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