US20150152743A1 - Method for minimizing the gap between a rotor and a housing - Google Patents

Method for minimizing the gap between a rotor and a housing Download PDF

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Publication number
US20150152743A1
US20150152743A1 US14/416,071 US201314416071A US2015152743A1 US 20150152743 A1 US20150152743 A1 US 20150152743A1 US 201314416071 A US201314416071 A US 201314416071A US 2015152743 A1 US2015152743 A1 US 2015152743A1
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US
United States
Prior art keywords
rotor
housing
gap
turbine
monitoring system
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.)
Abandoned
Application number
US14/416,071
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English (en)
Inventor
Andreas Luttenberg
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Siemens AG
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Siemens AG
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Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Lüttenberg, Andreas
Publication of US20150152743A1 publication Critical patent/US20150152743A1/en
Abandoned legal-status Critical Current

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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
    • 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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
    • 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
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/334—Vibration measurements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/40—Type of control system
    • F05D2270/44—Type of control system active, predictive, or anticipative

Definitions

  • the invention relates to a method for minimizing the gap between a rotor, especially a rotor blade, and a housing, especially a housing of a turbine, wherein the gap between rotor and housing can be adjusted, especially by displacement of the rotor and the housing in relation to each other. It also relates to a turbine, especially a gas turbine, comprising a rotor, especially a rotor blade, and a housing, wherein the gap between rotor and housing can be adjusted by means of an adjusting device, especially by displacement of rotor and housing in relation to each other.
  • a turbine is a turbomachine which converts the internal energy (enthalpy) of a flowing fluid (liquid or gas) into rotational energy and ultimately into the mechanical driving energy. Some of its internal energy is extracted from the fluid flow by the laminar circumflow—which is swirl free as far as possible—around the turbine blades, which portion of internal energy is transferred to the rotor blades of the turbine. Via these rotor blades, the turbine shaft is then made to rotate, the useful power being transmitted to a coupled working machine, such as a generator.
  • Rotor blades and shaft are parts of the movable rotor or rotating component of the turbine which is arranged inside a housing.
  • a plurality of blades are mounted on the shaft.
  • Rotor blades which are mounted in one plane form a blade wheel or rotor wheel in each case.
  • the blades are profiled with a slight curve, similar to an aircraft airfoil.
  • a stator wheel is customarily located in front of each rotor wheel. These stator blades project from the housing into the flowing medium and cause it to swirl.
  • the swirl which is generated in the stator wheel (kinetic energy) is utilized in the following rotor wheel in order to cause rotation of the shaft upon which the rotor wheel blades are mounted.
  • Stator wheel and rotor wheel together are referred to as a stage. A plurality of such stages are frequently connected in series. Since the stator wheel is stationary, its stator blades can be fastened both on the inside of the housing and on the outside of the housing, and therefore provide a support for the shaft of the rotor wheel.
  • a gap which for example serves for compensation of the heat expansion during operation, usually exists between the rotor blade tips of the rotor and the housing.
  • the gap between blade tip and housing is to be minimal, however, since fluid flows through the gap past the rotor blades and therefore does not contribute to energy generation.
  • an output signal of a structure-borne sound monitoring system which is associated with the rotor and/or housing, being used as a measure for the size of the gap and therefore for setting a minimum gap, wherein the structure-borne sound monitoring system is a component part of a foreign-body detection system.
  • the invention is based in this case on the consideration that a particularly simple monitoring of the gap size would be possible by means of sensors which are as non-invasive as possible and are to be attached in the outer regions.
  • a simple signal which is generated in the event of contact of rotor and housing, is the sound which is propagated, moreover, by solid bodies, such as a turbine housing.
  • solid bodies such as a turbine housing.
  • an acoustic detection of vibrations which are generated by blade tips colliding with the housing, is enabled in the outer regions of the housing. Therefore, a structure-borne sound monitoring system allows a particularly simple and technically inexpensive checking of a possible contact of blade tips and housing during a displacement of housing and rotor in relation to each other. This enables an accurate setting of a minimum gap.
  • the structure-borne sound monitoring system is a component part of a foreign-body detection system, especially of the turbine.
  • Foreign-body detection systems are frequently used in turbines in order to detect in good time possibly penetrating foreign bodies or breaking-away parts of the turbine itself and to initiate a shutdown of the turbine.
  • Foreign-body detection systems are based on acoustic detection. Therefore, it is advantageous to also use the structure-borne sound monitoring system of the foreign-body detection system in the manner of a dual-use system for setting a minimum gap. It may be the case that no constructional interventions at all in the turbine are even necessary for this purpose, but only a corresponding adjustment of sensors and control electrics.
  • the rotor can be displaced in an axial direction in relation to the housing for adjusting the size of the gap. Owing to the typically conical shape of the turbine, a uniform reduction of the gap over the entire circumference and in each turbine stage is achieved as a result.
  • the rotor is advantageously displaced just until there is no longer a contact which generates output signals. That is to say, the rotor is displaced until the turbine rotor blading comes into contact with the housing.
  • This contact is monitored by means of a structure-borne sound monitoring system and as a result of this limits the range of travel.
  • the rotor after a possibly short reverse displacement—is fixed directly at the limit for contact.
  • a turbine especially a gas turbine, comprising a rotor, especially a rotor blade, and a housing
  • the gap between rotor and housing is advantageously minimized by means of the described method.
  • the object is achieved by a structure-borne sound monitoring system being associated with the rotor and/or housing in a turbine and on the output side being connected to the adjusting device.
  • the structure-borne sound monitoring system is advantageously a component part of a foreign-body detection system and/or the rotor can be advantageously displaced in an axial direction in relation to the housing for adjusting the size of the gap.
  • the rotor particularly at the tips of the rotor blades, can be at least partially abradable. That is to say that corresponding abrasion points are provided and are designed for a slight contact of the housing during the adjustment process. At the abrasion points, material is then possibly worn away, but these points are designed so that no structural damage to the rotor, especially to the rotor blades, occurs as a result. Therefore, the rotor can displaced without risk up to the point of the slight signal-generating contact, which enables an optimum gap setting.
  • a power plant advantageously comprises a described turbine.
  • FIGURE shows a gas turbine
  • the FIGURE shows a turbine 100 , in this case a gas turbine, in a longitudinal partial section.
  • the gas turbine 100 has rotor 103 which is rotatably mounted around a rotational axis 102 (axial direction) and which is also referred to as a turbine rotor.
  • an intake housing 104 Arranged in series along the rotor 103 are an intake housing 104 , a compressor 105 , a toroidal combustion chamber 110 —especially an annular combustion chamber 106 —with a plurality of coaxially arranged burners 107 , a turbine 108 and the exhaust gas housing 109 .
  • the annular combustion chamber 106 communicates with an annular hot gas passage 111 .
  • Four series-connected turbine stages 112 form the turbine 108 there.
  • Each turbine stage 112 is formed from two blade rings.
  • a row 125 formed from rotor blades 120 follows a stator blade row 115 , as seen in the flow direction of a working medium 113 .
  • stator blades 130 are fastened on the stator 143 in this case, whereas the rotor blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133 .
  • the rotor blades 120 therefore form component parts of the rotor or rotating component 103 .
  • a generator or a working machine (not shown) is coupled to the rotor 103 .
  • air 135 is inducted by the compressor 105 through the intake housing 104 and compressed.
  • the compressed air which is made available at the turbine-side end of the compressor 105 is directed to the burners 107 and mixed with a combustible medium there.
  • the mixture is then combusted in the combustion chamber 110 , forming a working medium 113 .
  • the working medium 113 flows along the hot gas passage 111 past the stator blades 130 and the rotor blades 120 .
  • the working medium 113 is expanded, transmitting an impulse, so that the rotor blades 120 drive the rotor 103 and this drives the working machine which is coupled to it.
  • the components which are exposed to the hot working medium 113 are subjected to thermal loads during operation of the gas turbine 100 .
  • the stator blades 130 and rotor blades 120 of the first turbine stage 112 are thermally loaded most of all next to the heat shield tiles which line the combustion chamber 106 . In order to withstand the temperatures prevailing there, these are cooled by means of a cooling medium.
  • the stator blade 130 has a stator blade root (not shown here) which faces the inner housing 138 of the turbine 108 and a stator blade tip which lies opposite the stator blade root.
  • the stator blade tip faces the rotor 103 and is fastened on a fastening ring 140 of the stator 143 .
  • the gas turbine 100 has a foreign-body detection system which is not shown in more detail according to the FIGURE. This serves for detecting foreign bodies penetrating the gas turbine 100 along with the air 135 or for detecting foreign bodies which have broken away due to damage in the turbine 100 and, if necessary, for initiating a rapid shutdown of the turbine 100 .
  • the foreign-body detection system comprises a structure-borne sound monitoring system which is connected to a multiplicity of sensors on the rotor 103 and housing 138 which emit output signals with regard to the acoustic vibrations which occur in the turbine 100 .
  • the rotor 103 can be axially displaced along the axis 102 .
  • the gap d between rotor 103 —especially the rotor blade tips—and the housing 138 is decreased or increased by an axial displacement of the rotor 103 or of the housing 138 .
  • the axial displacement is carried out hydraulically.
  • the existing gap d is made narrower and until finally a first contact is made, leading to vibrations and therefore to the creation of sound.
  • This sound is transmitted by the housing 138 and is detected by the structure-borne sound monitoring system and converted into corresponding output signals.
  • stator blades 120 are fixed or—in the case of a contact of excessive force—shifted back again just until there is no longer a contact indicated by a corresponding output signal.
  • a minimum gap d is then set. This setting of the minimum gap can be carried out during operation of the turbine 100 , typically after it has warmed up.
  • the turbine blade 120 has an outer wear layer.
  • the outer wear layer is porous and/or ceramic, for example, so that even a slight contact does not cause any permanent damage.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Hydraulic Turbines (AREA)
  • Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
US14/416,071 2012-07-25 2013-07-15 Method for minimizing the gap between a rotor and a housing Abandoned US20150152743A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102012213016.0 2012-07-25
DE102012213016.0A DE102012213016A1 (de) 2012-07-25 2012-07-25 Verfahren zur Minimierung des Spalts zwischen einem Läufer und einem Gehäuse
PCT/EP2013/064901 WO2014016153A1 (de) 2012-07-25 2013-07-15 Verfahren zur minimierung des spalts zwischen einem läufer und einem gehäuse

Publications (1)

Publication Number Publication Date
US20150152743A1 true US20150152743A1 (en) 2015-06-04

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US14/416,071 Abandoned US20150152743A1 (en) 2012-07-25 2013-07-15 Method for minimizing the gap between a rotor and a housing

Country Status (6)

Country Link
US (1) US20150152743A1 (de)
EP (1) EP2864596A1 (de)
JP (1) JP2015524530A (de)
CN (1) CN104471194B (de)
DE (1) DE102012213016A1 (de)
WO (1) WO2014016153A1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130312249A1 (en) * 2010-06-14 2013-11-28 Tobias Buchal Method for adjusting the radial gaps which exist between blade airfoil tips or rotor blades and a passage wall
US20180298758A1 (en) * 2017-04-17 2018-10-18 General Electric Company Method and system for cooling fluid distribution
US10450967B2 (en) 2014-02-25 2019-10-22 Siemens Aktiengesellschaft Method for the operation of a gas turbine by active hydraulic gap adjustment

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3540182A1 (de) * 2018-03-14 2019-09-18 Siemens Aktiengesellschaft Verfahren zur steuerung einer spaltminimierung einer gasturbine
CN108956106B (zh) * 2018-05-17 2020-06-30 中国航发湖南动力机械研究所 双转子涡轮试验件
DE102018214752A1 (de) * 2018-08-30 2020-03-05 Siemens Aktiengesellschaft Verfahren zum Betrieb einer Gasturbine
DE102019109638B4 (de) 2019-04-11 2021-11-18 Rittal Gmbh & Co. Kg Schaltschrankanordnung mit einem Schaltschrankrahmengestell und einem auf einer Montageplatte montierten mehrpoligen Berührungsschutzmodul
CN110725722B (zh) * 2019-08-27 2022-04-19 中国科学院工程热物理研究所 一种适用于叶轮机械的动叶叶顶间隙动态连续可调结构
CN114251130B (zh) * 2021-12-22 2022-12-02 清华大学 一种用于控制叶顶泄漏流的鲁棒性转子结构和动力系统

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US4330234A (en) * 1979-02-20 1982-05-18 Rolls-Royce Limited Rotor tip clearance control apparatus for a gas turbine engine
US4335600A (en) * 1980-11-13 1982-06-22 General Electric Company Detecting internal abnormalities in turbines
US4831535A (en) * 1985-12-18 1989-05-16 Man Gutehoffnungshuette Gmbh Method of controlling the surge limit of turbocompressors
US4888948A (en) * 1987-03-25 1989-12-26 Stewart Hughes Limited Monitoring of foreign object ingestion in engines
US5056986A (en) * 1989-11-22 1991-10-15 Westinghouse Electric Corp. Inner cylinder axial positioning system
US5070722A (en) * 1990-09-21 1991-12-10 United Technologies Corporation Turbine engine debris ingestion monitor
US5206816A (en) * 1991-01-30 1993-04-27 Westinghouse Electric Corp. System and method for monitoring synchronous blade vibration
US5330320A (en) * 1992-04-01 1994-07-19 Abb Carbon Ab Method and a device in a rotating machine
US5704759A (en) * 1996-10-21 1998-01-06 Alliedsignal Inc. Abrasive tip/abradable shroud system and method for gas turbine compressor clearance control
US6499350B1 (en) * 2000-04-04 2002-12-31 Swantech, L.L.C. Turbine engine foreign object damage detection system
US6676372B2 (en) * 2001-04-12 2004-01-13 Siemens Aktiengesellschaft Gas turbine with axially mutually displaceable guide parts
US6668655B2 (en) * 2001-09-27 2003-12-30 Siemens Westinghouse Power Corporation Acoustic monitoring of foreign objects in combustion turbines during operation
US7201556B2 (en) * 2002-12-20 2007-04-10 Rolls-Royce Plc Displacement casing
US7559741B2 (en) * 2004-01-22 2009-07-14 Siemens Aktiengesellschaft Turbomachine having an axially displaceable rotor
US8449243B2 (en) * 2005-10-13 2013-05-28 Mtu Aero Engines Gmbh Device and method for axially displacing a turbine rotor
US20070128016A1 (en) * 2005-12-06 2007-06-07 Samhita Dasgupta Multi-range clearance measurement system and method of operation
US20100247283A1 (en) * 2009-03-25 2010-09-30 General Electric Company Method and apparatus for clearance control
US20100303612A1 (en) * 2009-05-26 2010-12-02 General Electric Company System and method for clearance control
US20110243715A1 (en) * 2010-03-30 2011-10-06 Strock Christopher W Abradable turbine air seal

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130312249A1 (en) * 2010-06-14 2013-11-28 Tobias Buchal Method for adjusting the radial gaps which exist between blade airfoil tips or rotor blades and a passage wall
US9200529B2 (en) * 2010-06-14 2015-12-01 Siemens Aktiengesellschaft Method for adjusting the radial gaps which exist between blade airfoil tips or rotor blades and a passage wall
US10450967B2 (en) 2014-02-25 2019-10-22 Siemens Aktiengesellschaft Method for the operation of a gas turbine by active hydraulic gap adjustment
US20180298758A1 (en) * 2017-04-17 2018-10-18 General Electric Company Method and system for cooling fluid distribution
US10544803B2 (en) * 2017-04-17 2020-01-28 General Electric Company Method and system for cooling fluid distribution

Also Published As

Publication number Publication date
WO2014016153A1 (de) 2014-01-30
CN104471194B (zh) 2016-04-13
JP2015524530A (ja) 2015-08-24
EP2864596A1 (de) 2015-04-29
CN104471194A (zh) 2015-03-25
DE102012213016A1 (de) 2014-01-30

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Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:LUETTENBERG, ANDREAS;REEL/FRAME:034767/0352

Effective date: 20141215

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION