CN104471194B - By minimized for the gap between rotor and casing method - Google Patents

By minimized for the gap between rotor and casing method Download PDF

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Publication number
CN104471194B
CN104471194B CN201380037767.5A CN201380037767A CN104471194B CN 104471194 B CN104471194 B CN 104471194B CN 201380037767 A CN201380037767 A CN 201380037767A CN 104471194 B CN104471194 B CN 104471194B
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CN
China
Prior art keywords
rotor
casing
gap
turbo machine
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.)
Expired - Fee Related
Application number
CN201380037767.5A
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Chinese (zh)
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CN104471194A (en
Inventor
A.卢滕伯格
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Siemens AG
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Siemens AG
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Filing date
Publication date
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Publication of CN104471194A publication Critical patent/CN104471194A/en
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Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
  • Hydraulic Turbines (AREA)

Abstract

The present invention relates to a kind of by rotor (120), especially working blade (120) and casing (138), especially the minimized method in gap (d) and between the casing (138) of turbo machine (100), wherein, the gap (d) between rotor (120) and casing (138) especially moves relative to each other by rotor (120) and casing (138) and adjusts.The object of this invention is to provide and a kind ofly make the minimized easy method in gap between rotor and casing.For this reason, the output signal of the solid-borne noise monitoring system arranged for rotor (120) and/or casing (138) correspondence is used in the size of measuring described gap (d), and is thus used in the minimum gap (d) of setting one.

Description

By minimized for the gap between rotor and casing method
Technical field
The present invention relates to a kind of by rotor, especially working blade and casing, the minimized method in the gap especially and between the casing of turbo machine, wherein, the gap between rotor and casing especially moves relative to each other by rotor and casing and adjusts.The invention still further relates to a kind of turbo machine, especially gas turbine, comprise rotor especially working blade and casing, wherein, the gap between rotor and casing can to move relative to each other particularly by rotor and casing by regulating device and adjust.
Background technique
Turbo machine is a kind of fluid machinery, and the interior energy (enthalpy) of fluid (liquid or gas) is transformed to rotating energy by it, and is finally converted into the driving energy of machinery.By streaming turbine blade without vortex ground laminar-flow type as far as possible, from the fluid stream flowing through moving turbine blade, extract energy in its part.Then by turbine shaft can be made in this part to rotate, available power delivery gives the machine for doing work be coupled with it, such as generator.Working blade and axle are the constituent elements of turbine movements rotor, and rotor is arranged on casing inside.
Usually many blades are installed on axle.The working blade be arranged in a plane forms impeller or an active wheel.The moulding of these blades is slightly bending, is similar to plane airfoil.A guide vane wheel is usually set before each active wheel.Guide vane to stretch in flowing medium from casing and flowing medium is reversed.The torsion (kinetic energy) caused in guide vane wheel, is used in active wheel in succession, and the axle being provided with working blade is rotated.
The combination of guide vane wheel and active wheel is called level by people.Often multiple this level tandem.Because guide vane wheel transfixion, so its guide vane is not only fixed on interior casing, but also be fixed on outer casing, and thus for the axle of active wheel provides supporting.
Between the working blade end and casing of rotor, usually leave gap, it is such as compensating thermal expansion during operation.But in order to reach high efficiency, the gap between blade tip and casing should be minimum, because fluid is flow through on working blade side by gap, and thus produce power is not contributed.
Possibility is provided, by corresponding regulating device, by rotor relative to casing moving influence gap size by turbine and around the cone shape of its casing.Such as more known to the method relative to casing movable rotor by DE4223495 and WO00/28190.Known to minimized for gap method by DE3910319C2, DE3901167A1 and EP1524411B1.Especially known by the latter, the size in gap is known by resistivity when determining conductive contact between rotor and casing.
But do not relate to when casing and rotor contact detect vibration other for by minimized for gap method, such as can learn from GB2396438A, US2009/0226302A1 or from US2005/0286995A1.
But these need high equipment to pay wages by the method that prior art is known and/or not bery accurately, only adopt so frequent actually the fixed length specified by rotor movement one.So be desirably in equipment spending aspect to do further improvement.
Summary of the invention
The technology that the present invention will solve is that topic is to provide a kind of method, the gap between rotor and casing can be made in a straightforward manner to minimize with it.
Be solve the problems of the technologies described above the measure taked to be by the present invention, the output signal of the solid-borne noise monitoring system arranged for rotor and/or casing correspondence is used in the size in tolerance gap, and be thus used in the minimum gap of setting one, wherein, described solid-borne noise monitoring system is the constituent element of foreign material detection system.
The starting point that the present invention considers in this respect is, by the least possible sensor be placed in intrusively in perimeter, can monitor gap size especially simply.The simple signal of one produced when rotor contacts with casing is sound, and it is propagated by solid such as turbine casing again.Therefore in the perimeter of casing, just acoustically can detect the vibration that the blade tip by colliding with casing produces.When rotor and casing move relative to each other, solid-borne noise monitoring system can realize facilitating especially and technically checking blade tip to contact with casing is contingent simply.Which achieves and accurately set up minimum gap.
According to the present invention, described solid-borne noise monitoring system is the constituent element of the foreign material detection system of especially turbo machine.Often use foreign material detection system in the turbine, in order that even can the early detection foreign matter that may enter or also have the fragment of turbo machine and impel turbo machine to close down.Foreign material detection system is based on acoustic detection.Therefore advantageously, the acoustic monitoring system of foreign material detection system also can be used in setting minimum clearance by the mode of dual utilization.Perhaps here do not need even completely to implement structural intervention in turbo machine, but only need sensor and the corresponding electricity coupling of controller.
By favourable expansion design, in order to the size of adjusting play, rotor can move relative to casing vertically.Therefore by the typical cone shape of turbine, reach and reduce gap equably along whole circumference with in each turbine stage.
Advantageously, by rotor movement be, until just in time no longer there is the output signal come in contact.This means, movable rotor, contact until moving turbine blade enters with casing.This contact is monitored and moving-limiting distance whereby by solid-borne noise monitoring system.Once be recorded to first contact indication, rotor is just just in time fixed on by the border of contact after the short travelling backwards of necessity.
At a kind of turbo machine comprising rotor, especially working blade and casing, especially in gas turbine, the gap between rotor and casing advantageously minimizes by illustrated method.
In addition the technical problem to be solved in the present invention is, provides a kind of turbo machine, and wherein, the gap between rotor and casing minimizes, and this should realize when equipment spending is very low.
For to solve the problems of the technologies described above and the measure taked is, be that rotor and/or casing correspondence arrange solid-borne noise monitoring system in the turbine, it is connected with regulating device at output terminal.
Also relevant with turbo machine, described solid-borne noise monitoring system is the constituent element of foreign material detection system, and/or in order to the size of adjusting play, rotor advantageously can move relative to casing vertically.
By favourable expansion design, rotor, especially can wear and tear at least partly in working blade end.This means to there is corresponding abrading section, they are designed for and are in course of adjustment and casing gentle contact.Now may denude by generating material in abrading section, but they are designed to, thus not to rotor, especially working blade causes structural destruction.Therefore rotor can move to the gentle contact that can produce signal with being safe from danger always, consequently, can realize best gap adjustment.
Power station equipment advantageously comprises illustrated turbo machine.
The advantage adopting the present invention to obtain especially is, by by the contact between foreign material identification system identification rotor and casing, operation technique can realize minimizing of radial clearance by simple especially device.Thus the efficiency of turbo machine maximize and improve power.Consequently also provide the advantage of environmental protection aspect, because by changing control technique, reach remarkable fuel saving and emissions reduction.
Accompanying drawing explanation
The present invention is elaborated below by accompanying drawing.
Accompanying drawing represents a gas turbine.
Embodiment
Accompanying drawing fragmentary longitudinal section represents a turbo machine 100, is here gas turbine.Gas turbine 100 has the rotor 103 around spin axis 102 (axis) swivel bearing in inside, it is also referred to as turbine rotor.Follow one another along rotor 103: inlet casing 104, gas compressor 105, comprise the circular ring type firing chamber 110 of the burner 107 of multiple arranged in co-axial alignment, especially annular combustion chamber 106, turbine 108 and exit casing 109.
Annular combustion chamber 106 is connected with the hot-gas channel 111 of annular.The turbine stage 112 of such as four series connection forms turbine 108 there.Each turbine stage 112 is made up of two blade rings.See along the flow direction of working medium 113 in hot-gas channel 111, with the leaf circle 125 be made up of working blade 120 after directing vane circle 115.
Guide vane 130 is fixed on stator 143 here, and the working blade 120 of a leaf circle 125 is then arranged on rotor 103 by the turbine disk 133.Therefore working blade 120 becomes the constituent element of rotor 103.Generator coupled or machine for doing work (not representing in figure) on rotor 103.
At gas turbine 100 run duration, sucked and pressurized air 135 by inlet casing 104 by gas compressor 105.Gas compressor 105 the pressurized air provided in the end of turbine side input burner 107, and there with fuel mix.Then, mixture in firing chamber 110 combustion to form working medium 113.Set out therefrom, working medium 113 flows through guide vane 130 and working blade 120 along hot-gas channel 111.Working medium 113 expands on working blade 120 with transmitting momentum, so working blade 120 drives rotor 103 and drives the machine for doing work be coupled with it.
The component meeting with high temperature refrigerant 113 at gas turbine 100 run duration bears heat load.First turbine stage 112 that the flow direction along working medium 113 is seen, its guide vane 130 and working blade 120 are in the heat shielding block side as annular combustion chamber 106 liner, so heat load is maximum.In order to sustain the temperature existed there, they are by coolant cools.Equally, blade 120,130 can have anticorrosive coat (MCrAlX; M=Fe, CO, Ni, rare earth) and heat shield (thermal-protective coating, such as ZrO 2, Y 2o 4-ZrO 2).
The guide vane leaf top that the guide vane blade root (not having in figure to represent) that guide vane 130 has to face casing 138 in turbine 108 is opposite with guide vane blade root with one.Guide vane leaf top facing rotors 103 is also fixed on the retaining ring 140 of stator 143.
In control technique, the foreign material detection system do not represented in detail in figure is had by the turbo machine 100 of accompanying drawing.It invades foreign matter in turbo machine 100 with air 135 or owing to damaging the foreign material dropped in turbo machine 100 for detecting, and forces turbo machine 100 to be closed down fast where necessary.In addition, foreign material detection system also comprises solid-borne noise monitoring system, and it is connected with multiple sensor on rotor 103 and casing 138, and output signal relates to the acoustic vibration produced in turbo machine 100.
In addition, rotor 103 can move axially along axis 102.Based on the rotor top of rotor 103 and the mutual conicity of casing 138, by moving axially of rotor 103 or casing 138, reduce or increase rotor 103, the gap d between especially working blade end, and casing 138.The described hydraulic type that moves axially carries out.
Moved axially relative to casing 138 by rotor 103, reduce the gap d of formation, until finally cause first time contact, this causes vibration and thus produces sound.Sound is propagated by casing 138, is detected and be converted to corresponding output signal by solid-borne noise monitoring system.
According to working blade 120 moving axially relative to casing 138, cause contact more or less strong between turbine blade 120 and casing 138, also change the intensity of the solid-borne noise produced thus and thus change output signal.Thus obtain the different output signal relevant from axial internal clearance.
Cause first time contact time, steady job blade 120 or cross strong contact time by its travelling backwards again, until just in time no longer there is the contact by outputing signal instruction accordingly.Now set up as minimum clearance d.The adjustment of minimum clearance d can be carried out at turbo machine 100 run duration, typically implements after turbo machine 100 thoroughly warming-up.
Turbine blade 120 has outer fret.Outer fret is such as porous and/or is ceramic, even if so slightly contact and also can not cause sustaining breakdown.

Claims (7)

1. one kind by the minimized method in gap (d) between rotor (120) and the casing (138) of turbo machine (100), wherein, gap (d) between rotor (120) and casing (138) moves relative to each other by rotor (120) and casing (138) and adjusts, wherein, by the output signal of the solid-borne noise monitoring system for rotor (120) and/or the arranging of casing (138) correspondence for measuring the size of described gap (d), and thus for setting up minimum gap (d), it is characterized by: described solid-borne noise monitoring system is the constituent element of the foreign material detection system of turbo machine (100).
2. in accordance with the method for claim 1, wherein, in order to adjust the size in described gap, rotor (120) can vertically (102) mobile relative to casing (138).
3. according to the method one of all claims in prostatitis Suo Shu, it is characterized by, by rotor (120) movement be, until just in time no longer there is the contact between rotor (120) and casing (138) producing output signal.
4. a turbo machine (100), comprise rotor (120) and casing (138), wherein, gap (d) between rotor (120) and casing (138) can by regulating device, moved relative to each other by rotor (120) and casing (138) and adjust, wherein, for rotor (120) and/or casing (138) arrange solid-borne noise monitoring system, described solid-borne noise monitoring system is connected with regulating device at output terminal, it is characterized by: described solid-borne noise monitoring system is the constituent element of the foreign material detection system of turbo machine (100).
5. according to turbo machine according to claim 4 (100), wherein, in order to adjust the size in described gap, rotor (120) can vertically (102) mobile relative to casing (138).
6. according to the turbo machine (100) described in claim 4 or 5, wherein, rotor (120) can wear and tear at least partly.
7. a power station equipment, comprises according to the turbo machine (100) one of claim 4 to 6 Suo Shu.
CN201380037767.5A 2012-07-25 2013-07-15 By minimized for the gap between rotor and casing method Expired - Fee Related CN104471194B (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102012213016.0 2012-07-25
DE102012213016.0A DE102012213016A1 (en) 2012-07-25 2012-07-25 Method for minimizing the gap between a rotor and a housing
PCT/EP2013/064901 WO2014016153A1 (en) 2012-07-25 2013-07-15 Method for minimizing the gap between a rotor and a housing

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CN104471194A CN104471194A (en) 2015-03-25
CN104471194B true CN104471194B (en) 2016-04-13

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US (1) US20150152743A1 (en)
EP (1) EP2864596A1 (en)
JP (1) JP2015524530A (en)
CN (1) CN104471194B (en)
DE (1) DE102012213016A1 (en)
WO (1) WO2014016153A1 (en)

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Publication number Publication date
US20150152743A1 (en) 2015-06-04
CN104471194A (en) 2015-03-25
JP2015524530A (en) 2015-08-24
WO2014016153A1 (en) 2014-01-30
EP2864596A1 (en) 2015-04-29
DE102012213016A1 (en) 2014-01-30

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