US3861818A - Thrust wear detector - Google Patents

Thrust wear detector Download PDF

Info

Publication number
US3861818A
US3861818A US442507A US44250774A US3861818A US 3861818 A US3861818 A US 3861818A US 442507 A US442507 A US 442507A US 44250774 A US44250774 A US 44250774A US 3861818 A US3861818 A US 3861818A
Authority
US
United States
Prior art keywords
piston
chamber
follower piston
fluid
nozzle
Prior art date
Legal status (The legal status 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 status listed.)
Expired - Lifetime
Application number
US442507A
Other languages
English (en)
Inventor
Markus A Eggenberger
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
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
Priority to US442507A priority Critical patent/US3861818A/en
Application filed by General Electric Co filed Critical General Electric Co
Priority to CA216,874A priority patent/CA1027353A/en
Publication of US3861818A publication Critical patent/US3861818A/en
Application granted granted Critical
Priority to GB2759/75A priority patent/GB1491803A/en
Priority to DE19752503077 priority patent/DE2503077A1/de
Priority to CH103575A priority patent/CH585894A5/xx
Priority to IT19837/75A priority patent/IT1031362B/it
Priority to JP50017531A priority patent/JPS5914640B2/ja
Priority to FR7504694A priority patent/FR2261505B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • 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
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
    • G01B21/16—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring distance of clearance between spaced objects

Definitions

  • CL 415/14 415/118 includes a hydraulically positioned follower piston [51] I00 6 25/26 which is testable against sticking to the detector cas- [58] Field of t x 415/14 H8 131 ing. A calibrated orifice used to blanace the follower piston is accessible for maintenance without disassem- [56] References Cited bly of the wear detector. Movement of the follower piston, indicating bearing wear, is measured directly UNITED STATES PATENTS from the piston and false tripouts due to pressure i 5 switch failure is averted by providing redundant presggen erger.. 3,220,244 11/1965 Donnelly....
  • This invention relates, in general, to protection systems for turbomachines; and, in particular, this invention pertains to a hydraulically positioned device for following the axial movement of a turbomachine rotor.
  • U.S. Pat. No. 2,888,023 to Eggenberger discloses a hydraulic thrust bearing wear indicator including a hydraulically positioned follower piston and integral nozzle portion mounted closely adjacent to the turbomachine rotor. Balance of the follower piston is dependent upon differential piston surface areas, a calibrated orifice therebetween and a constant pressure hydraulic gap between the nozzle and the rotor. A pilot valve is positioned by the follower piston to pass or shut off fluid to a pair of pressure switches connected to an alarm and trip circuit. Movement of the rotor due to thrust bearing wear may either increase or decrease the hydraulic pressure gap causing movement of the follower piston to an equilibrium position or the steady state gap.
  • the pilot valve is also moved and at a predetermined critical movement will cause the pressure switches to close due to a shutoff of fluid pressure causing the activation of the trip and alarm circuit.
  • Bearing wear is measured by switching the trip and alarm circuit to a test circuit and then moving a slidable valve sleeve, surrounding the pilot valve, until one of the ports is shut off. This gives an indication of the remaining permissible thrust bearing wear from which the amount of bearing wear may be calculated.
  • One object of the present invention is to provide an improved thrust wear detector and trip system having increased reliability.
  • Another object of the invention is to provide an improved thrust wear detector in which the axial movement of the follower piston may be tested.
  • Another object of the invention is to provide an improved thrust wear detector wherein the calibrated orifice may be easily maintained.
  • Another object of the invention is to provide an improved thrust wear detector wherein thrust bearing wear is directly determined.
  • Still another object of the invention is to provide an improved thrust wear detector having improved reliability against false tripping due to pressure switch failure.
  • a thrust wear detector is provided with a hydraulically balanced follower piston having a piston nozzle slidable therein.
  • the follower piston and piston nozzle may be moved as a unit in normal operation or they may be moved separately during test operation.
  • a calibrated orifice is positioned externally of the wear detector casing in the fluid supply lines for maintenance and inspection.
  • a linear variable differential transformer is used to directly measure movement of the follower piston, thus giving-direct readings on bearing wear.
  • redundant pressure switches are used for tripping to avert false tripouts due to the failure of any single switch.
  • the drawing shows an elevation section of a thrust wear detector according to the present invention and further shows an electrical schematic diagram of an alarm, trip and test circuit.
  • the drawing also shows external fluid supply piping to the detector.
  • a thrust wear detector 11 and mounting frame I3 is positioned adjacent a turbomachine rotor 15.
  • the axis of the detector is generally perpendicular to the rotor axis as shown, although it is possible to mount the detector so that its axis is parallel to the rotor axis.
  • alarm, trip and test circuit 17 may be mounted elsewhere on the mounting frame.
  • the thrust wear detector includes a stationary casing 19 formed with an axial bore 21 therethrough.
  • a follower piston 23 is slidably mounted within a portion of the casing axial bore and includes a piston collar 25 having opposite piston surfaces 25a and 25b defining balance chambers 27a and 27b, respectively, within the detector casing.
  • the balance chambers 27a and 27b are provided with fluid inlet ports 29a and 29b, respectively.
  • the follower piston includes an axial bore 31 which houses slidable piston nozzle 33 therein.
  • the nozzle is positioned closely adjacent the rotor surface defining a gap therebetween and includes an open end 35 and an enlarged collar 37 slidable within an enlarged portion 39 of the piston axial bore.
  • the enlarged portion 39 of the piston axial bore is divided into a spring housing 39a and an internal test chamber 39b.
  • the internal test chamber is fed with fluid through port 41 in the follower piston and port 290 in the detector casing.
  • the open end 35 of the nozzle is fed with fluid from balance chamber 27B through port 41a in the follower piston.
  • a spring 43 is positioned between the follower piston and detector casing to prevent contact between the nozzle and rotor when fluid to the detector is shut down.
  • Another spring 45 in the spring housing 39a bears against the nozzle collar 37 and follower piston 23 so that the nozzle and follower piston may move as a unit in operating position when fluid is not supplied to chamber 39b.
  • a pilot valve 51 is attached at one end to the follower piston and is positioned axially thereby.
  • the pilot valve is slidable within an axially slidable sleeve 53.
  • the axi ally slidable sleeve is positioned by a micrometer screw 55.
  • the slidable sleeve includes outlet ports 57a and 57b as well as inlet port 59 therebetween.
  • the pilot valve includes lands 61a and 61b which are axially spaced apart at a greater distance than outlet ports 57a and 57b. Therefore, when fluid is delivered through inlet port 59 and pilot valve 51 is centered with respect to outlet ports 57a and 57b, the inlet fluid will flow through both outlet ports.
  • the slidable sleeve allows setting of the alarm and trip points with respect to the normal operating position of the shaft.
  • Movement of the follower piston may be determined and recorded by use of a linear variable differential transformer (LVDT) 63 which is attached directly to the follower piston.
  • the linear variable differential transformer translates the mechanical movement of a rod 63a through a coil into a voltage differential which then may be interpreted to give the amount of bearing wear which has occured. Movement of the follower piston is read directly on an instrument reflecting the position of the LVDT. This construction also allows continuous monitoring of shaft position during alarm, trip point setting using the slidable sleeve.
  • Ports 57a and 57b supply fluid through casing ports 65a and 65b, respectively, to redundant pressure switches 67 and 69. Failure of a single switch will not cause a false trip because both switches in either set must be closed to cause a trip.
  • the electrical circuit 17 connected to the pressure switches has been shown in simplified form for completeness.
  • the fluid supply system 71 includes a main conduit 73 interconnected with a branch pipe 75, a branch pipe 77, a branch pipe 79 and a branch pipe 81.
  • the branch pipe 75 supplies fluid to the pilot valve through casing inlet 83.
  • the branch pipe 77 supplies fluid to first balance chamber 27a.
  • the branch pipe 79 supplies fluid to internal chamber 39b and may be selectively operated for test by valve 85.
  • Valve 85 may be a solenoid operated valve.
  • the branch pipe 81 supplies fluid to I balancing chamber 27b and may be selectively operated through valve 87 which may also be a solenoid valve.
  • Branch pipes 77 and 81 are interconnected by a conduit 89 including a calibrated orifice 91.
  • the connection with branch pipe 81 is made downstream from valve 87 so that fluid may be selectively added to the flow from orifice 91.
  • the thrust bearing wear detector includes ahydraulically balanced follower piston (the general operation of which is described in US. Pat. No. 2,888,023) which includes a slidable piston nozzle as distinguished from an integral nozzle portion of the cited patent.
  • fluid is supplied during normal operation to balance chambers 27a and 27b through pipe branch 77, conduit 89 and ports 29a and 29b.
  • Valve 87 is closed so the operation is similar to the device in the cited patent except for calibrated orifice 91 which is external to the detector casing for easy maintenance.
  • valve 85 may be opened causing only the follower piston to move toward the rotor while the piston nozzle remains stationary. This causes the pilot valve to move covering port 57a, thereby closing pressure switches 69. Thereafter, valve 85 is closed and valve 87 is opened causing an increase in pressure in chamber 27b, thereby moving follower piston 23 and nozzle 33 away from the rotor. This moves pilot valve 51 to cover port 57b, closing pressure switches 67. In this manner both trip positions of the follower piston are fully tested,
  • Movement of the follower piston is detected directly by linear variable differential transformer 63 and thus it is possible to fully set the trip points by moving sleeve 53 while still monitoring the follower piston. Hence, during trip circuit setting, continuous monitoring of rotor axial movement is maintained.
  • a device for following the axial movement of a rotating shaft including a casing mounted adjacent the rotating shaft having a hydraulically positioned follower piston slidably mounted within the casing defining opposite first and second chambers; the device further comprising:
  • a piston nozzle slidably mounted within the follower piston, the piston nozzle having an open end closely adjacent the rotating shaft defining a hydraulic gap therebetween; the first chamber in fluid communication with the second chamber and the second chamber in fluid communication with the piston nozzle and hydraulic gap;
  • the device recited in claim 1 further comprising a calibrated orifice interconnecting the first and second opposite chambers.
  • a second fluid supply connected to the second chamber including a valve for selectively introducing the second fluid supply into the second chamber;
  • a pipe interconnecting the first and second fluid supplies at a point downstream from the valve, the pipe including the calibrated orifice.
  • the device recited in claim 1 further including a linear variable differential transformer having a rod slidable therein positioned by the follower piston.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Control Of Turbines (AREA)
  • Measuring Arrangements Characterized By The Use Of Fluids (AREA)
  • Control Of Non-Positive-Displacement Pumps (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Positive-Displacement Pumps (AREA)
  • Measurement Of Length, Angles, Or The Like Using Electric Or Magnetic Means (AREA)
US442507A 1974-02-14 1974-02-14 Thrust wear detector Expired - Lifetime US3861818A (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
US442507A US3861818A (en) 1974-02-14 1974-02-14 Thrust wear detector
CA216,874A CA1027353A (en) 1974-02-14 1974-12-23 Thrust wear detector
GB2759/75A GB1491803A (en) 1974-02-14 1975-01-22 Device for detecting the axial movement of a rotating shaft
DE19752503077 DE2503077A1 (de) 1974-02-14 1975-01-25 Verschleissdetektor fuer schublager
CH103575A CH585894A5 (it) 1974-02-14 1975-01-29
IT19837/75A IT1031362B (it) 1974-02-14 1975-01-31 Rivelatore di usura di un cuscinetto di spinta
JP50017531A JPS5914640B2 (ja) 1974-02-14 1975-02-13 推力摩耗検出器
FR7504694A FR2261505B1 (it) 1974-02-14 1975-02-14

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US442507A US3861818A (en) 1974-02-14 1974-02-14 Thrust wear detector

Publications (1)

Publication Number Publication Date
US3861818A true US3861818A (en) 1975-01-21

Family

ID=23757062

Family Applications (1)

Application Number Title Priority Date Filing Date
US442507A Expired - Lifetime US3861818A (en) 1974-02-14 1974-02-14 Thrust wear detector

Country Status (8)

Country Link
US (1) US3861818A (it)
JP (1) JPS5914640B2 (it)
CA (1) CA1027353A (it)
CH (1) CH585894A5 (it)
DE (1) DE2503077A1 (it)
FR (1) FR2261505B1 (it)
GB (1) GB1491803A (it)
IT (1) IT1031362B (it)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USB471735I5 (it) * 1974-05-20 1976-02-03
FR2381281A1 (fr) * 1977-02-16 1978-09-15 Gen Electric Dispositif de controle du deplacement axial d'un arbre
US4302963A (en) * 1980-05-12 1981-12-01 General Electric Company Thrust bearing wear detector positioner
US4502832A (en) * 1982-02-11 1985-03-05 Arthur Pfeiffer Vakuumtechnik Wetzlar Gmbh Turbo-molecular pump
US4762461A (en) * 1985-12-20 1988-08-09 Ngk Insulators Ltd. Leakless pump
US6657217B2 (en) 2001-04-10 2003-12-02 York International Corporation Probe for sensing movement in a compressor system
US20060159547A1 (en) * 2005-01-15 2006-07-20 Siemens Westinghouse Power Corporation Warning system for turbine component contact
US20100156652A1 (en) * 2008-12-23 2010-06-24 Honeywell International Inc. Portable bearing test device
CN103048123A (zh) * 2012-11-30 2013-04-17 天津大学 缸套-活塞环摩擦副磨损试验机
WO2014134129A1 (en) * 2013-02-26 2014-09-04 Fuller Kenneth A Methods and apparatus for measuring axial shaft displacement within gas turbine engines
CN104634682A (zh) * 2015-01-15 2015-05-20 江苏师范大学 缸套活塞环摩擦副磨损试验机
CN111347246A (zh) * 2020-03-30 2020-06-30 江门市科达仪表有限公司 一种用于车辆仪表装配和检测的一体机

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3644733A1 (de) * 1987-01-07 1988-07-14 Vnii Metrologiceskoj Sluzby Satz von normalmassen zur attestierung und eichung von geraeten zur parametermessung bei unebenheiten von profilen und oberflaechen
DE3703528C1 (de) * 1987-02-03 1987-09-03 Mannesmann Ag Verfahren zur UEberwachung von Rollen in Stranggiessanlagen und Vorrichtung zur Durchfuehrung des Verfahrens
CN106052538B (zh) * 2016-06-23 2018-08-03 国家电网公司 一种水轮机组轴系动力系统状态在线诊断装置及方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1575993A (en) * 1924-06-09 1926-03-09 Westinghouse Electric & Mfg Co Automatic stop for turbines
US2888023A (en) * 1956-04-13 1959-05-26 Gen Electric Hydraulic thrust bearing wear indicator and safety device
US3220244A (en) * 1963-09-06 1965-11-30 Cooper Bessemer Corp Thrust bearing wear sensing device
US3612710A (en) * 1970-04-30 1971-10-12 Carrier Corp Centrifugal refrigerant gas compressor

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1575993A (en) * 1924-06-09 1926-03-09 Westinghouse Electric & Mfg Co Automatic stop for turbines
US2888023A (en) * 1956-04-13 1959-05-26 Gen Electric Hydraulic thrust bearing wear indicator and safety device
US3220244A (en) * 1963-09-06 1965-11-30 Cooper Bessemer Corp Thrust bearing wear sensing device
US3612710A (en) * 1970-04-30 1971-10-12 Carrier Corp Centrifugal refrigerant gas compressor

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USB471735I5 (it) * 1974-05-20 1976-02-03
US3989408A (en) * 1974-05-20 1976-11-02 Westinghouse Electric Corporation Positioning device for a turbine rotor position sensor
FR2381281A1 (fr) * 1977-02-16 1978-09-15 Gen Electric Dispositif de controle du deplacement axial d'un arbre
US4302963A (en) * 1980-05-12 1981-12-01 General Electric Company Thrust bearing wear detector positioner
US4502832A (en) * 1982-02-11 1985-03-05 Arthur Pfeiffer Vakuumtechnik Wetzlar Gmbh Turbo-molecular pump
US4762461A (en) * 1985-12-20 1988-08-09 Ngk Insulators Ltd. Leakless pump
US6657217B2 (en) 2001-04-10 2003-12-02 York International Corporation Probe for sensing movement in a compressor system
US6744061B2 (en) 2001-04-10 2004-06-01 York International Corporation System and method for sensing movement in a compressor system
US20060159547A1 (en) * 2005-01-15 2006-07-20 Siemens Westinghouse Power Corporation Warning system for turbine component contact
US7207768B2 (en) 2005-01-15 2007-04-24 Siemens Power Generation, Inc. Warning system for turbine component contact
US20100156652A1 (en) * 2008-12-23 2010-06-24 Honeywell International Inc. Portable bearing test device
US8094006B2 (en) * 2008-12-23 2012-01-10 Honeywell International Inc. Portable bearing test device
CN103048123A (zh) * 2012-11-30 2013-04-17 天津大学 缸套-活塞环摩擦副磨损试验机
WO2014134129A1 (en) * 2013-02-26 2014-09-04 Fuller Kenneth A Methods and apparatus for measuring axial shaft displacement within gas turbine engines
US10125682B2 (en) 2013-02-26 2018-11-13 Rolls-Royce Corporation Methods and apparatus for measuring axial shaft displacement within gas turbine engines
CN104634682A (zh) * 2015-01-15 2015-05-20 江苏师范大学 缸套活塞环摩擦副磨损试验机
CN111347246A (zh) * 2020-03-30 2020-06-30 江门市科达仪表有限公司 一种用于车辆仪表装配和检测的一体机

Also Published As

Publication number Publication date
GB1491803A (en) 1977-11-16
DE2503077A1 (de) 1975-09-18
CA1027353A (en) 1978-03-07
CH585894A5 (it) 1977-03-15
FR2261505B1 (it) 1978-10-06
IT1031362B (it) 1979-04-30
JPS5914640B2 (ja) 1984-04-05
FR2261505A1 (it) 1975-09-12
JPS50115311A (it) 1975-09-09

Similar Documents

Publication Publication Date Title
US3861818A (en) Thrust wear detector
JP3979091B2 (ja) ターボ形流体機械及びそれに用いられるドライガスシール
JP7077077B2 (ja) ドライガスシール
CZ284460B6 (cs) Turbostroj s axiální plynovou třecí ucpávkou
US4777979A (en) Position detector for clapper of non-return valve
US4181017A (en) Fault detecting apparatus for fluid pressure systems
US2175868A (en) Packing
US3392983A (en) Safety control device for use with mechanical seals
US3220244A (en) Thrust bearing wear sensing device
US4302963A (en) Thrust bearing wear detector positioner
US3989408A (en) Positioning device for a turbine rotor position sensor
US3002374A (en) Hydraulic thrust bearing wear indicator
GB1598205A (en) Monitoring clearances between relatively moving machine parts
KR101968265B1 (ko) 발전 정지 없이 테스트 가능한 터빈 트립 장치
US9650912B2 (en) System and device for over-speed protection of a turbo-machine
US4442704A (en) Viscosity meter
US4073184A (en) Shaft axial position monitoring system
US3090221A (en) Test apparatus and hydraulic systems
GB2290145A (en) Device for monitoring and detecting irregularities in a pressurised circuit
EP0145190B1 (en) Hydraulic proximity probe
US3050987A (en) Contamination meter and process for detecting contamination
Sixsmith et al. A miniature wet turboexpander
US3680572A (en) Pneumatic overspeed protective system
JPS59165801A (ja) タ−ボ機械の推力調整方法及び装置
US11852248B2 (en) Packing system and diagnostic method for a packing system of a valve assembly