公开(公告)号：US20140356166A1

公开(公告)日：2014-12-04

申请号：US14290071

申请日：2014-05-29

Applicant: SNECMA

Inventor： Andre Leroux

IPC: G01B7/14 ,  G01R27/26 ,  F04C28/28

CPC classification number: G01B7/14 ,  F04C28/28 ,  G01B7/08 ,  G01R27/2605

Abstract: A capacitive sensor for measuring the clearance between the apex of the vanes of a rotor and the inner surface of an abradable coating covering the inner surface of a turbomachine casing, the clearance measuring capacitive sensor including a first electrode the material of which is abradable so as to get worn upon contacting an apex of a vane, the material of the first electrode having a degree of wear substantially identical to the degree of wear of the material of the abradable coating.

Abstract translation: 一种用于测量转子叶片的顶点与覆盖涡轮机壳体的内表面的可磨损涂层的内表面之间的间隙的电容式传感器，该间隙测量电容式传感器包括第一电极，该第一电极的材料是可磨损的， 在与叶片的顶点接触时磨损，第一电极的材料具有与耐磨涂层的材料的磨损程度基本相同的磨损程度。

公开(公告)号：US09926937B2

公开(公告)日：2018-03-27

申请号：US14386393

申请日：2013-03-19

Applicant: SNECMA

Inventor： David Tourin ,  Pierre Ferdinand ,  Valerio Gerez ,  Andre Leroux

IPC: F04D27/00 ,  F01D5/28 ,  F01D17/02 ,  F01D21/00 ,  F04D29/32 ,  G01M5/00 ,  F04D19/00 ,  G01B11/16 ,  G01D5/353

CPC classification number: F04D27/001 ,  F01D5/282 ,  F01D17/02 ,  F01D21/003 ,  F04D19/002 ,  F04D29/324 ,  F05D2260/80 ,  F05D2270/804 ,  F05D2300/603 ,  G01B11/18 ,  G01D5/353 ,  G01M5/0016 ,  G01M5/0033 ,  G01M5/0091 ,  Y02T50/672

Abstract: A system for detecting deformation of a fan for an aeroengine, the fan including a rotor including plural blades made of composite material including woven fibers. At least one of the fibers in each of the blades is an optical fiber including at least one portion defining a Bragg grating. The system further includes a transceiver connected to the optical fiber and configured to send an optical signal into the optical fiber and to receive an optical signal in response from the optical fiber, and a detector module connected to the transceiver to detect deformation of the fan when the received optical signal presents correlation with a predetermined signature of a damped impact on a blade at a determined speed of rotation. This deformation may be the result of a foreign object impacting against a blade of the fan or may follow from variation in an internal defect.

公开(公告)号：US09915518B2

公开(公告)日：2018-03-13

申请号：US14290071

申请日：2014-05-29

Applicant: SNECMA

Inventor： Andre Leroux

IPC: G01B7/14 ,  G01B7/06 ,  F04C28/28 ,  G01R27/26

CPC classification number: G01B7/14 ,  F04C28/28 ,  G01B7/08 ,  G01R27/2605

Abstract: A capacitive sensor for measuring the clearance between the apex of the vanes of a rotor and the inner surface of an abradable coating covering the inner surface of a turbomachine casing, the clearance measuring capacitive sensor including a first electrode the material of which is abradable so as to get worn upon contacting an apex of a vane, the material of the first electrode having a degree of wear substantially identical to the degree of wear of the material of the abradable coating.

公开(公告)号：US09518894B2

公开(公告)日：2016-12-13

申请号：US13888715

申请日：2013-05-07

Applicant: SNECMA

Inventor： Andre Leroux ,  Serge Del Arco ,  Olivier Follerot ,  Michel Herbault ,  Philippe Armand Hugbart ,  Fabien Pouchard ,  Etienne Tulie

IPC: G01M15/14 ,  G01H1/00 ,  G01H9/00 ,  G01M7/00 ,  G01B11/14 ,  F01D21/00 ,  G01N21/17

CPC classification number: G01M15/14 ,  F01D21/003 ,  G01B11/14 ,  G01H1/006 ,  G01H9/006 ,  G01M7/00 ,  G01N21/1702 ,  G01N2021/1706 ,  G01N2201/08

Abstract: A device for measuring vibration amplitudes of the blade tips in a turbomachine is provided. The device includes a support mounted in an orifice of a casing of a turbomachine, in which are housed two optical guides for the emission and reception of a light signal exiting inside the casing across from the tips of the blades of a turbine wheel Each optical guide includes an optical fiber connected by a mechanical connector to a needle of which the core is made of a material able to transmit a light signal and which is resistant to temperatures less than or equal to 1100° C. and which exits at its distal end in the casing across from the blade tips.

Abstract translation: 提供了一种用于测量涡轮机中的叶片尖端的振幅的装置。 该装置包括安装在涡轮机壳体的孔口中的支撑件，其中容纳有两个光导件，用于发射和接收从涡轮机叶片的叶片顶端离开的壳体内的光信号。每个光导 包括通过机械连接器连接到针的光纤，芯的芯由能够透射光信号的材料制成，并且其耐受小于或等于1100℃的温度，并且在其远端处出口 套管横跨刀片尖端。

公开(公告)号：US09366599B2

公开(公告)日：2016-06-14

申请号：US13767056

申请日：2013-02-14

Applicant: SNECMA

Inventor： Andre Leroux

IPC: G01L1/00 ,  G01L3/00 ,  G01L5/00 ,  G01M15/14 ,  G01B21/32 ,  F01D17/06 ,  F01D21/00 ,  G01M5/00 ,  G01M99/00 ,  G01H1/00

CPC classification number: G01M15/14 ,  F01D17/06 ,  F01D21/003 ,  G01B21/32 ,  G01H1/006 ,  G01M5/0016 ,  G01M5/0041 ,  G01M99/004 ,  Y02T50/672

Abstract: A method for measuring the deformation of a turbo-machine blade including: a step of positioning at least one accelerometer onto a local point of the turbo-machine blade; a first step of measuring the centrifugal force, by the accelerometer, at the local point of the turbo-machine blade along the given measurement direction at a first predetermined speed; a second step of measuring the centrifugal, at a second predetermined speed; a step of determining the angular displacement of the measurement direction of the accelerometer relative to the centrifugal direction as a function of the first acceleration measurement and the second acceleration measurement, said angular displacement corresponding to an angular deformation of the local point of the turbo-machine blade.

Abstract translation: 一种用于测量涡轮机叶片的变形的方法，包括：将至少一个加速度计定位在涡轮机叶片的局部点上的步骤; 第一步骤，通过加速度计在涡轮机叶片的局部点处沿着给定的测量方向以第一预定速度测量离心力; 第二步骤，以第二预定速度测量离心; 确定加速度计相对于离心方向的测量方向的角位移作为第一加速度测量和第二加速度测量的函数的步骤，所述角位移对应于涡轮机的局部点的角变形 刀。

公开(公告)号：US20150098819A1

公开(公告)日：2015-04-09

申请号：US14386393

申请日：2013-03-19

Applicant: SNECMA

Inventor： David Tourin ,  Pierre Ferdinand ,  Valerio Gerez ,  Andre Leroux

IPC: F04D27/00 ,  G01B11/16 ,  G01D5/353 ,  F04D19/00

CPC classification number: F04D27/001 ,  F01D5/282 ,  F01D17/02 ,  F01D21/003 ,  F04D19/002 ,  F04D29/324 ,  F05D2260/80 ,  F05D2270/804 ,  F05D2300/603 ,  G01B11/18 ,  G01D5/353 ,  G01M5/0016 ,  G01M5/0033 ,  G01M5/0091 ,  Y02T50/672

Abstract: A system for detecting deformation of a fan for an aeroengine, the fan including a rotor including plural blades made of composite material including woven fibers. At least one of the fibers in each of the blades is an optical fiber including at least one portion defining a Bragg grating. The system further includes a transceiver connected to the optical fiber and configured to send an optical signal into the optical fiber and to receive an optical signal in response from the optical fiber, and a detector module connected to the transceiver to detect deformation of the fan when the received optical signal presents correlation with a predetermined signature of a damped impact on a blade at a determined speed of rotation. This deformation may be the result of a foreign object impacting against a blade of the fan or may follow from variation in an internal defect.

Abstract translation: 一种用于检测航空发动机的风扇的变形的系统，所述风扇包括由包括机织纤维的复合材料制成的多个叶片的转子。 每个叶片中的至少一个纤维是包括限定布拉格光栅的至少一个部分的光纤。 该系统还包括连接到光纤的收发器，其被配置为将光信号发送到光纤中并且响应于光纤接收光信号;以及检测器模块，连接到收发器以检测风扇的变形， 所接收的光信号以确定的旋转速度呈现与叶片上的阻尼冲击的预定特征的相关性。 这种变形可能是异物撞击风扇叶片的结果，或者可能跟随内部缺陷的变化。