WO2005073667A1 - Appareil inductif et procede de mesure de volume mort d'extremites d'aubes de compresseur dans une turbine a gaz - Google Patents

Appareil inductif et procede de mesure de volume mort d'extremites d'aubes de compresseur dans une turbine a gaz Download PDF

Info

Publication number
WO2005073667A1
WO2005073667A1 PCT/US2005/003036 US2005003036W WO2005073667A1 WO 2005073667 A1 WO2005073667 A1 WO 2005073667A1 US 2005003036 W US2005003036 W US 2005003036W WO 2005073667 A1 WO2005073667 A1 WO 2005073667A1
Authority
WO
WIPO (PCT)
Prior art keywords
compressor assembly
inductive proximity
compressor
proximity sensor
blade tips
Prior art date
Application number
PCT/US2005/003036
Other languages
English (en)
Inventor
Yakup Genc
Xiang Zhang
Original Assignee
Siemens Corporate Research, Inc.
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens Corporate Research, Inc. filed Critical Siemens Corporate Research, Inc.
Publication of WO2005073667A1 publication Critical patent/WO2005073667A1/fr

Links

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B7/00—Measuring arrangements characterised by the use of electric or magnetic techniques
    • G01B7/14—Measuring arrangements characterised by the use of electric or magnetic techniques for measuring distance or clearance between spaced objects or spaced apertures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position

Definitions

  • Gas turbine engines typically include a core engine with a compressor for compressing air entering the core engine, a combustor where fuel is mixed with the compressed air and then burned to create a high energy gas stream, and a turbine which extracts energy from the gas stream to drive the compressor.
  • a second turbine or low pressure turbine located downstream from the core engine extracts more energy from the gas stream for driving a fan. The fan provides the main propulsive thrust generated by the engine.
  • the rotating engine components of the turbine and compressor include a number of blades attached to a disc which are surrounded by a stationary shroud.
  • a stationary shroud In order to achieve high engine efficiency in a gas turbine, it is desirable to keep the space or gap between the tips of the blades and the shroud to a minimum. Tight running clearances must be maintained in order to minimize intrastage leakage.
  • Compressor blade tip clearance measurement is part of the blade ring alignment process that is common in the maintenance of gas turbine engines.
  • a well-known procedure for measuring this clearance employs the use of a mechanical tool.
  • the mechanical tool is used to measure the minimum clearance for each row or compressor stage by aligning the compressor blade rings to establish uniform clearances circumferentially.
  • an illustrative tool 100 for ascertaining blade tip clearances generally comprises an elongated body 102, a probe tip 104 and a dial indicator 106.
  • a calibration cap 108 is disposed over the probe tip 104 as shown.
  • FIG. 2 depicts a gas turbine engine generally denoted by the reference numeral 212.
  • the gas turbine engine 212 includes a housing 214 and a shroud 216 that surrounds a compressor assembly 218.
  • a plurality of clearance measurement tools 200 are inserted through corresponding alignment ports 208a, 208b that are axially disposed in the housing 214 and shroud 216, respectively, of the gas turbine engine 212.
  • each compressor stage of assembly 218 includes a plurality of compressor blades 220.
  • Each blade 220 has an outer tip 222 that comes into contact with probe tip 204 of tool 200.
  • the tool is calibrated so that when the probe tip 204 makes contact with the outer tip 222 of the blade 220, the clearance between the outer tip 222 and the engine shroud 216 can be read on the dial indicator 206.
  • This current measurement process suffers from several inherent drawbacks: (1) the need to physically align all of the tools with the corresponding stages of the compressor can be rather tedious; and (2) slight errors in operating the tools can cause physical damage to the blade tips.
  • Non-contact clearance measuring systems are also known in the art.
  • U.S. Patent No. 3,992,627 to Stewart discloses the use of x-rays to measure clearances in gas turbine engines.
  • a technical publication by Drinkuth et al entitled “Laser Proximity Probes for the Measurement of Turbine Blade Tip Clearances," Instrumentation Society of America, 20 th Annual Instrumentation Symposium, May 21-23, 1974 (“Drinkuth”), discloses the use of a laser triangulation system to measure blade tip clearance in a gas turbine engine.
  • a reflected laser beam is output onto a coherent fiber bundle which transmits the laser spot position to a vidicon.
  • the televised spot is displayed on a television monitor and viewed directly by operating personnel.
  • the spot images from all the blades are superimposed to provide an average spot position and therefore, an average clearance of the rotating blades.
  • an apparatus for measuring the clearance between the blade tips of the compressor blades of a rotatable compressor assembly and the housing in which the compressor assembly is mounted in a gas turbine engine.
  • the apparatus comprises: an inductive proximity sensor disposed in the housing and positioned in close proximity to but not touching the blade tips of the compressor blades of the compressor assembly, the inductive proximity sensor being adapted to generate a magnetic field and to sense changes in the magnetic field as the compressor assembly is rotated and the blade tips are sequentially brought into close proximity to the inductive proximity sensor; the inductive proximity sensor being mounted in one or more alignment ports defined in the housing of the gas turbine engine, the alignment ports being disposed axially and corresponding to different stages of the compressor assembly; and a device for displaying the clearance between the inductive proximity sensor and the blade tips of the compressor blades of the rotatable compressor assembly, which displays the electrical analog voltage corresponding to the separation between the inductive proximity sensor and the blade tips of the compressor blades of the rotatable compressor assembly as a function of the changes in the magnetic field.
  • a method for measuring the clearance between the blade tips of the compressor blades of a rotatable compressor assembly and the housing in which the compressor assembly is mounted in a gas turbine engine.
  • the method generally comprises the steps of: positioning an inductive proximity sensor in close proximity to but not touching the blade tips of the compressor blades of the compressor assembly; generating a magnetic field with the inductive proximity sensor in close proximity to the blade tips of compressor assembly; rotating the compressor assembly; sensing changes in the magnetic field as the compressor assembly is rotated and the blade tips are sequentially brought into close proximity to the inductive proximity sensor; and displaying the clearance between the inductive proximity sensor and the blade tips of the compressor blades of the rotatable compressor assembly.
  • the displaying step comprises displaying the electrical analog voltage corresponding to the separation between the inductive proximity sensor and the blade tips of the compressor blades of the rotatable compressor assembly as a function of the changes in the magnetic field.
  • a plurality of inductive proximity sensors may be disposed in a corresponding plurality of axially located alignment ports to facilitate aligning the axis of the rotating compressor assembly relative to the engine housing.
  • the inductive proximity sensor may be calibrated by: using a mechanical tool to measure the smallest clearance between the blade tips and the housing; setting the clearance between the inductive proximity sensor and the blade tip to a plurality of different values; recording the output voltages for each set clearance; and utilizing these recorded output voltage values to fit an inductive sensor output voltage curve.
  • FIG. 1 is a schematic diagram of a prior art mechanical tool used to measure blade tip clearances
  • FIG. 2 is a schematic depicting several compressor stages in a gas turbine engine and the mechanical tool shown in FIG. 1 mounted in a plurality of alignment ports to measure the compressor blade tip clearances at several axial locations
  • FIG. 3 is a schematic depicting several compressor stages in a gas turbine engine and inductive proximity sensors in accordance with the present invention disposed in a plurality of axial locations
  • FIG. 4 is an enlarged detail view of an inductive proximity sensor mounted in the gas turbine engine of FIG. 3; [0014] FIG. 5.
  • FIG. 6 is a graph showing how the analog output voltage from the sensor can be used to depict blade tip clearances for individual compressor blades as the compressor assembly is rotated; and [0016] FIG. 7 is a detail view of an alternative embodiment in accordance with the invention utilizing a laser sensor.
  • a gas turbine engine 312 includes a housing 314 and a shroud 316 that surrounds a compressor assembly 318.
  • the compressor assembly is comprised of a plurality of axial flow stages attached to each other. These stages have slightly different outer diameters and are ground to these diameters in sequence.
  • Each rotor assembly is comprised of a disk having a circumferential slot containing a multiplicity of titanium alloy compressor blades, such as, for example, Ti-6A1-4V, Ti-8Al-lV-lMo, Ti-6Al-2Sn-4Zr-2Mo and Ti-6Al-2Sn-4Zr-6Mo and the like.
  • the gas turbine engine 312 is further provided with a plurality of alignment ports 308a, 308b that are axially disposed in the housing 314 and shroud 316, respectively, of the gas turbine engine 312.
  • the alignment ports 308a, 308b are located in axial positions corresponding to rows 7, 11, 13 and 15 of the compressor stages, but these ports could be disposed at other locations as well.
  • each compressor stage of assembly 318 includes a plurality of compressor blades 320.
  • Each blade 320 has an outer tip 322 that is to be radially positioned at a particular distance from the internal surface of the shroud 316.
  • Nominal blade clearance is typically 2.3mm (0.09in) with a potential range of 0 - 4.6mm (0.18in).
  • an inductive proximity sensor assembly 324 is disposed in each alignment port 308b located at rows 7, 11, 13 and 15 of the compressor assembly of the gas turbine engine.
  • the inductive proximity sensor assembly 324 communicates with a device 326 for displaying distance as a function of analog output voltage. The distance may be read from a display 328 associated with device 326.
  • the inductive proximity sensor assembly When calibrated with the size and metallic properties of the blade tips, the inductive proximity sensor assembly produces a different level of analog output voltage corresponding to the distance from the tip 322 of the blade 320. Such signals can be sampled and measured at a frequency from IK to 20kHz, thereby enabling a signal processing system to digitize and infer the minimum clearance between a reference point and the tip 322 of blade 320. It will be appreciated by those skilled in the art that by using a multiple number of inductive proximity sensor assemblies 324 in unison, the actual alignment of the axis 319 of the rotating compressor assembly 318 may be measured relative to the shroud 316 or engine casing. These measurements can be utilized by software to ascertain the geometry of the central rotating axis 319 for the compressor assembly 318.
  • FIG. 4 depicts an enlarged detail view of an inductive proximity sensor assembly 424 corresponding to the proximity sensor assembly 324 depicted in FIG. 3.
  • the inductive proximity sensor assembly generally comprises an inductive proximity sensor 428 and a mounting fitting 430 adapted to fit within the alignment port 308b.
  • the fitting 430 is similar to the fitting associated with the prior art mechanical tip clearance measurement device.
  • the inductive proximity sensor 428 produces electrical signals that are dependent on the distance to a nearby piece of metal.
  • the proximity sensor 428 which is referred to as a high frequency oscillation type, generates a magnetic field ahead of the sensor head.
  • the inductive proximity sensor 428 contains a tuned circuit with a capacitor and a sensing coil, whose impedance changes as a metallic target (e.g., the blade tip) is moved within a certain distance thereof.
  • the inductance of the tuned circuit sensing coil is influenced by the initiator.
  • an amplitude of the tuned circuit signal changes.
  • the signal is rectified and converted by a discriminator into an analog output voltage that can be correlated to the distance of the sensed blade tip from the sensor.
  • FIG. 5 is a graph showing how analog output voltage varies as a function of measuring distance for a plurality of different metals, using a sample inductive sensor, such model no. EX-305 from Keyence Corporation of America.
  • FIG. 6 is a graph showing how the analog output voltage from the sensor can be used to depict blade tip clearances for the individual compressor blades as the compressor assembly is rotated. The apex of the curve depicts the region of minimum clearance between the compressor blade tips and the shroud. This can be depicted on the display 328 of device 326 illustrated in FIG. 3.
  • the device 326 can be any apparatus constructed and arranged to display a waveform.
  • the minimum blade clearance can be ascertained after one revolution of the compressor rotor hub.
  • the analog output voltage from an inductive proximity sensor varies with many different working environmental parameters, such as, for example, temperature.
  • the inductive measurement system therefore, has to be calibrated offline for each operative environment.
  • an electronic calibration system can be used to estimate the curve of the output voltage of the sensor relative to the distance between the sensor and blade tip. For the proposed semi-automatic measurement, this calibration can be used together with the existing mechanical tip clearance measurement apparatus depicted in FIG. 1.
  • the mechanical device 100 is used to measure the closest blade tip clearance for any measurement spot. Then, the mechanical device 100 is replaced with the inductive sensor depicted in FIGS. 3 and 4. The clearance between the tip of the inductive sensor and the blade tip is then set to different values, e.g., 0.2mm, 0.4mm, 0.6mm, 0.8mm, 1.0mm, 1.2mm, etc, and the output voltage for each clearance value is recorded. Then, these recorded values are utilized to fit the inductive sensor output voltage curve.
  • This procedure can be implemented with software. In carrying out the foregoing calibration, the user only needs to do the current measurement once and the rest can be handled by a computer semi-automatically. [0021] Referring now to FIG.
  • the laser sensor assembly 724 comprises a laser sensor 728 and fitting 730.
  • An exemplary laser based distance measurement device is model number LC-2430, available from Keyence Corporation of America.
  • the laser sensor 728 communicates with a controller generally denoted by the reference numeral 732 via a cable 734.
  • the laser device is capable of providing measurements from a 30mm range with 0.08 micrometers resolution at a 50kHz sampling rate.
  • the operation of the laser proximity probe is based on a triangulation system where light from a point source is focused from a first small diameter long focal lens on surface 736 as a narrow beam that intersects the blade tip at a given angle, forming a bright spot.
  • the light reflected from this bright spot is imaged through the output lens in the direction of a second angle onto a second lens along surface 738 of the laser sensor 728.
  • the distance from the laser sensor 728 to the blade tips can be displayed on the controller 732.
  • the position of the laser sensor assembly 724 needs to be calibrated relative to the shroud 716 in order to facilitate proper measurement. Once the relationship between laser spot position received by the laser sensor 728 and blade position is established, no further calibration is required.
  • the output spot position is linearly related to blade clearance so that the absolute accuracy of measured blade position is constant over the complete measurable range.
  • the distances between the laser sensor 728 and the tips 722 of the respective compressor blades 720 can be graphed as shown in FIG. 6 based on the output voltages corresponding to the measured distances.
  • the distances integrated over time will provide the desired clearances.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention a trait à un appareil et un procédé pour la mesure du volume mort entre les extrémités d'aubes des aubes de compresseur d'un ensemble de compresseur rotatif et le carter dans lequel l'ensemble de compresseur est monté dans une turbine à gaz. L'appareil comporte un capteur de proximité inductif disposé dans le carter et positionné très proche mais pas en contact avec les extrémités d'aubes des aubes de compresseur de l'ensemble de compresseur. Le capteur de proximité inductif est apte à la génération d'un champ magnétique et à la détection de modifications dans le champ magnétique au fur et à mesure de la rotation de l'ensemble de compresseur et le rapprochement séquentiel des extrémités d'aubes du capteur de proximité inductif. Le capteur de proximité inductif est monté dans un ou des orifices d'alignement définis dans le carter de la turbine à gaz. Un dispositif affiche le volume mort entre le capteur de proximité inductif et les extrémités d'aubes des aubes de compresseur de l'ensemble de compresseur rotatif.
PCT/US2005/003036 2004-01-27 2005-01-27 Appareil inductif et procede de mesure de volume mort d'extremites d'aubes de compresseur dans une turbine a gaz WO2005073667A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US54010304P 2004-01-27 2004-01-27
US60/540,103 2004-01-27

Publications (1)

Publication Number Publication Date
WO2005073667A1 true WO2005073667A1 (fr) 2005-08-11

Family

ID=34826185

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2005/003036 WO2005073667A1 (fr) 2004-01-27 2005-01-27 Appareil inductif et procede de mesure de volume mort d'extremites d'aubes de compresseur dans une turbine a gaz

Country Status (1)

Country Link
WO (1) WO2005073667A1 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2218881A1 (fr) * 2009-02-13 2010-08-18 Siemens Aktiengesellschaft Procédé de calibrage en ligne d'un capteur et système de mesure
CN102721361A (zh) * 2011-03-28 2012-10-10 通用电气公司 用于检查叶片尖部间隙的方法和系统
US20120296593A1 (en) * 2011-05-20 2012-11-22 Tyco Thermal Controls Llc System and method for determining position of rotating blades having variable thickness
EP2698502A1 (fr) 2012-08-13 2014-02-19 Alstom Technology Ltd Procédé de mesure du jeu à froid des extrémités d'aubes d'une turbomachine et agencement de mesures du jeu des extrémités pour l'exécution de ce procédé
EP2728331A1 (fr) * 2012-10-31 2014-05-07 General Electric Company Procédés et systèmes de surveillance de la condition de lames
CN107655396A (zh) * 2017-08-17 2018-02-02 韶关学院 一种轮毂轴承轴向负游隙的接触式在线检测装置
US10209361B2 (en) 2014-01-28 2019-02-19 Third Dimension Software Limited Positioning device for an optical triangulation sensor
CN113959391A (zh) * 2021-09-27 2022-01-21 中国航发沈阳发动机研究所 一种发动机双层机匣内参数测量结构

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE859372C (de) * 1951-06-24 1954-04-08 Duesseldorf Stadtwerke Messeinrichtung zur Bestimmung des radialen Schaufelspieles von Kreiselmaschinen, insbesondere Dampfturbinen
US4071820A (en) * 1976-04-05 1978-01-31 Alton Corporation Measurement system
US4326804A (en) * 1980-02-11 1982-04-27 General Electric Company Apparatus and method for optical clearance determination
US4967153A (en) * 1986-09-08 1990-10-30 Langley Lawrence W Eddy current turbomachinery blade timing system
US5942893A (en) * 1996-07-16 1999-08-24 General Dynamics Advanced Technology Systems Shielded eddy current sensor for enhanced sensitivity
US20030222640A1 (en) * 2002-05-31 2003-12-04 Siemens Westinghouse Power Corporation Turbine blade clearance on-line measurement system

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE859372C (de) * 1951-06-24 1954-04-08 Duesseldorf Stadtwerke Messeinrichtung zur Bestimmung des radialen Schaufelspieles von Kreiselmaschinen, insbesondere Dampfturbinen
US4071820A (en) * 1976-04-05 1978-01-31 Alton Corporation Measurement system
US4326804A (en) * 1980-02-11 1982-04-27 General Electric Company Apparatus and method for optical clearance determination
US4967153A (en) * 1986-09-08 1990-10-30 Langley Lawrence W Eddy current turbomachinery blade timing system
US5942893A (en) * 1996-07-16 1999-08-24 General Dynamics Advanced Technology Systems Shielded eddy current sensor for enhanced sensitivity
US20030222640A1 (en) * 2002-05-31 2003-12-04 Siemens Westinghouse Power Corporation Turbine blade clearance on-line measurement system

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2218881A1 (fr) * 2009-02-13 2010-08-18 Siemens Aktiengesellschaft Procédé de calibrage en ligne d'un capteur et système de mesure
CN102721361A (zh) * 2011-03-28 2012-10-10 通用电气公司 用于检查叶片尖部间隙的方法和系统
US20120296593A1 (en) * 2011-05-20 2012-11-22 Tyco Thermal Controls Llc System and method for determining position of rotating blades having variable thickness
EP2698502A1 (fr) 2012-08-13 2014-02-19 Alstom Technology Ltd Procédé de mesure du jeu à froid des extrémités d'aubes d'une turbomachine et agencement de mesures du jeu des extrémités pour l'exécution de ce procédé
EP2728331A1 (fr) * 2012-10-31 2014-05-07 General Electric Company Procédés et systèmes de surveillance de la condition de lames
US9250153B2 (en) 2012-10-31 2016-02-02 General Electric Company Methods and systems for monitoring health of blades
US10209361B2 (en) 2014-01-28 2019-02-19 Third Dimension Software Limited Positioning device for an optical triangulation sensor
CN107655396A (zh) * 2017-08-17 2018-02-02 韶关学院 一种轮毂轴承轴向负游隙的接触式在线检测装置
CN107655396B (zh) * 2017-08-17 2023-07-28 韶关学院 一种轮毂轴承轴向负游隙的接触式在线检测装置
CN113959391A (zh) * 2021-09-27 2022-01-21 中国航发沈阳发动机研究所 一种发动机双层机匣内参数测量结构
CN113959391B (zh) * 2021-09-27 2024-03-22 中国航发沈阳发动机研究所 一种发动机双层机匣内参数测量结构

Similar Documents

Publication Publication Date Title
WO2005073667A1 (fr) Appareil inductif et procede de mesure de volume mort d'extremites d'aubes de compresseur dans une turbine a gaz
US9530209B2 (en) Method of determining the location of tip timing sensors during operation
US7836772B2 (en) Method and apparatus for tracking a rotating blade tip for blade vibration monitor measurements
EP2162698B1 (fr) Capteurs à courants de foucault
JP4221210B2 (ja) タービンブレード先端間隙を測定する方法及び装置
US7341428B2 (en) Turbine blade for monitoring torsional blade vibration
US7259552B2 (en) Wear monitor for turbo-machine
EP2630339B1 (fr) Système et procédé de diagnostic pour surveiller les conditions de fonctionnement de composants d'une turbomachine
US6912446B2 (en) Systems and methods for automated sensing and machining for repairing airfoils of blades
US8096184B2 (en) Turbine blade for monitoring blade vibration
EP2261614B1 (fr) Mesures combinées de la fréquence et amplitude pour une vibration de pale de turbomachine sans contact
US8591188B2 (en) Displacement sensor system and method of operation
CN105466329A (zh) 一种非接触式发动机涡轮叶尖径向间隙测量方法
EP2578811B1 (fr) Procédé permettant de déterminer la position de lames rotatives d'épaisseur variable.
US20060132147A1 (en) System and method for measuring clearance between two objects
US9341462B2 (en) Sensor for measuring blade tip clearance in gas turbines
EP2236977A1 (fr) Broche de frottement indiquant le temps pour mesure de la clarté transitoire et procédé associé
Lavagnoli et al. High-fidelity rotor gap measurements in a short-duration turbine rig
US20030222638A1 (en) Turbine blade clearance on-line measurement system
Woike et al. Testing of a microwave blade tip clearance sensor at the NASA Glenn Research Center
US8959785B2 (en) Apparatus and method for measuring runout
EP1988359A2 (fr) Dispositif de mesure pour mesurer les paramètres d'une aube de rotor et procédé de mesure à l'aide dudit dispositif
EP2312410A1 (fr) Procédé de surveillance sans contact de turbines, particulièrement les pales individuelles d'une turbine à vapeur ou à gaz dans une station de génération d'électricité et système permettant d'effectuer ce procédé
WO2012091821A1 (fr) Appareil et procédé de mesure de faux-rond
US20090051096A1 (en) Jig

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): AE AG AL AM AT AU AZ BA BB BG BR BW BY BZ CA CH CN CO CR CU CZ DE DK DM DZ EC EE EG ES FI GB GD GE GH GM HR HU ID IL IN IS JP KE KG KP KR KZ LC LK LR LS LT LU LV MA MD MG MK MN MW MX MZ NA NI NO NZ OM PG PH PL PT RO RU SC SD SE SG SK SL SY TJ TM TN TR TT TZ UA UG US UZ VC VN YU ZA ZM ZW

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): BW GH GM KE LS MW MZ NA SD SL SZ TZ UG ZM ZW AM AZ BY KG KZ MD RU TJ TM AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LT LU MC NL PL PT RO SE SI SK TR BF BJ CF CG CI CM GA GN GQ GW ML MR NE SN TD TG

121 Ep: the epo has been informed by wipo that ep was designated in this application
NENP Non-entry into the national phase

Ref country code: DE

WWW Wipo information: withdrawn in national office

Country of ref document: DE

122 Ep: pct application non-entry in european phase