EP3896252B1 - Procédé et dispositif pour commander le positionnement d'au moins un disque de rotor autour d'un tirant d'un rotor assemblé partiellement - Google Patents

Procédé et dispositif pour commander le positionnement d'au moins un disque de rotor autour d'un tirant d'un rotor assemblé partiellement Download PDF

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Publication number
EP3896252B1
EP3896252B1 EP20169754.7A EP20169754A EP3896252B1 EP 3896252 B1 EP3896252 B1 EP 3896252B1 EP 20169754 A EP20169754 A EP 20169754A EP 3896252 B1 EP3896252 B1 EP 3896252B1
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EP
European Patent Office
Prior art keywords
coupled
rotor
tie
rod
reference device
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EP20169754.7A
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German (de)
English (en)
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EP3896252A1 (fr
Inventor
Enrico Pignone
Roberto BOSCA
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Ansaldo Energia SpA
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Ansaldo Energia SpA
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Priority to EP20169754.7A priority Critical patent/EP3896252B1/fr
Priority to CN202110410829.9A priority patent/CN113530608A/zh
Publication of EP3896252A1 publication Critical patent/EP3896252A1/fr
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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/027—Arrangements for balancing

Definitions

  • the invention relates to a method and an assembly for controlling the positioning of a rotor disc about a tie-rod of a partially assembled rotor of a gas turbine.
  • a gas turbine rotor of a plant for the production of electrical energy usually comprises a plurality of bladed rotor discs, which are centred on an axis and are coupled one another. The coupling between adjacent rotor discs is obtained by means of Hirth joints.
  • each rotor disc is provided with two respective annuli provided with radial teeth, the so-called Hirth teeth sets, one on each face.
  • the annuli are coupled to annuli of adjacent discs so as to build the so-called Hirth joints.
  • the rotors discs are provided with respective blade sets and are bound into packs by a central tie-rod, which engages respective central holes of the rotor discs.
  • Each bladed disc defines a compressor rotor stage or a turbine rotor stage.
  • Gas turbine rotors must be produced and assembled with utmost precision, so as to ensure a nearly perfect balancing. Given the masses and the high rotation speeds (the rotor usually rotates at 3000 rpm or 3600 rpm, depending on the standards of the different countries), even the smallest defects can cause dangerous vibrations exceeding the allowed limits, thus forcing the plant to be stopped in order to carry out corrective interventions aimed at bringing the vibrations back to the allowed limits.
  • Assembling a rotor currently involves stacking the rotor discs about a central tie-rod arranged in a vertical position.
  • the rotor discs automatically center themselves, thanks to the fact that the contact between the discs occurs through the Hirth toothing described above.
  • Assembling the rotor usually requires stacking a large number of rotor discs (e.g. about twenty). Therefore, having a lack of homogeneity in just one of these discs (for example, due to the fact that the disc has non-parallel faces) is enough to obtain, at the end of the stacking step, an inclined stack, namely a stack where the center of the last disc is not vertically aligned with the one of the first disc.
  • the compliance of the discs is usually controlled when the rotor is already clamped.
  • the rotor compliance of the discs is usually controlled on a rotor tilted horizontally and transported to a lathe machine, where it is possible to measure the "run-out" eccentricity of each disc with respect to the axis formed by the bearings. Possible corrective actions may require the rotor to be disassembled.
  • Control method for controlling the compliance of the discs before the stacking are known. However, they do not ensure the detection of all non-compliances of the discs, as operators need to carry out manual activities and personal assessments. Therefore, the accuracy and the times needed for the checks and the corrections cannot be considered as satisfying.
  • the central tie-rod In overhauled rotors, in fact, the central tie-rod cannot be used as a valid reference for axial symmetry, as it is usually deformed by the long time and thermomechanical stresses to which it has been subjected during operation.
  • the invention relates to a method for controlling the positioning of rotor discs about a tie-rod of a partially assembled rotor of a gas turbine; the tie-rod extending along a longitudinal axis; the method comprising:
  • a further object is to provide an assembly for controlling the positioning of a rotor disc about a tie-rod of a partially assembled rotor of a gas turbine, which is precise, reliable and capable of easing the operations to be carried out in order to check the compliance of the discs, thus minimizing operators' manual activities and personal assessments.
  • the invention relates to an assembly for controlling the positioning of at least one rotor disc about a tie-rod of a partially assembled rotor of a gas turbine; the tie-rod extending along a longitudinal axis; the assembly comprising:
  • reference number 1 indicates a gas turbine rotor of a plant for the production of electrical energy comprising a plurality of discs 2 aligned along an axis A and bound into packs by means of a central tie-rod 3.
  • the central tie-rod 3 extends along the longitudinal axis A.
  • a first group of discs 2, provided with respective first rotor blades 5, defines a compressor section 1a of the rotor 1
  • a second group of discs 2, provided with respective second rotor blades 6, defines a turbine section 1b of the rotor 1.
  • the compressor section 1a and the turbine section 1b are separated from one another by a spacer disc 7 without blades, which basically acts as a spacer element and is substantially shaped like a cylinder.
  • a combustion chamber (not shown) of the gas turbine is arranged around the spacer disc 7.
  • each rotor disc 2 is provided with a central through hole 8 and with a peripheral edge 9 provided with a plurality of seats 10 properly shaped so as to be engaged by respective first rotor blades 5 or to respective second rotor blades 6.
  • the central hole 8 will be engaged, in use, by the tie-rod 3 of the rotor 1.
  • Each rotor disc 2 is further provided with a radial teeth annulus 12, commonly named as Hirth toothing, on each face 13a, 13b of the rotor disc 2 (in figure 2 only face 13a of the rotor disc 2 is well visible).
  • the radial teeth annulus 12 is arranged along the respective face close to the peripheral edge 9 of the rotor disc 2.
  • the radial teeth annuli 12 are positioned and shaped to be coupled to the respective annuli of the adjacent rotor discs 2 in order to build the so-called Hirth joint and to ensure a stable coupling of the rotor discs 2.
  • Figure 3 shows a partially assembled rotor 1, in which the tie-rod 3 is arranged and supported in a vertical position.
  • the tie-rod 3 is positioned so as the longitudinal axis A is substantially vertical.
  • the tie-rod 3 is provided with one first end 15 and with a second end 16 axially opposite to the first end 15.
  • the first end 15 is coupled to a front shaft 18 ( figure 1 and 3 ) and the second end 16 protrudes from a rear hollow shaft 19 (visible only in figure 1 ).
  • the front shaft 18 is housed in a stacking pit 21, which ensures a correct and stable vertical positioning of the tie-rod 3.
  • the configuration shown in figure 3 can occur both during the assembling of the rotor 1 (when the rotor discs 2 are stacked on top of one another, so that the radial teeth annuli 12 of the adjacent rotor discs 2 can be coupled to one another in order to build the Hirth joints) and during the disassembling of the rotor 1 (when the rotor discs 2 are removed one by one).
  • the method for controlling the positioning of at least one rotor disc 2 about a tie-rod 3 according to the invention is applied to a partially assembled rotor 1 like the one shown in the configuration of figure 3 .
  • the method comprises detecting at least one parameter correlated to the position of at least one rotor disc 2 with respect to one or more references.
  • the method comprises detecting the eccentricity of the rotor disc 2 with respect to the longitudinal axis A with an assembly 23 for controlling the positioning of the rotor disc 2 comprising a main device 24 coupled to a free face 13a of the rotor disc 2 and at least one reference device 25 26 coupled to the tie-rod 3.
  • the detection of the eccentricity of the rotor disc 2 is obtained by at least three lasers emitters 28 coupled to one between the main device 24 or the at least one reference device 25 and at least three respective photosensitive sensors 30 coupled to the other between the main device 24 and the at least one reference device 25.
  • the three lasers emitters 28 are preferably arranged at 120° from each other.
  • the photosensitive sensors 30 are arranged at 120° from each other too and are disposed to intercept the beams of the respective lasers emitters 28.
  • the detection of the eccentricity is made by means of the main device 24 coupled to the free face 13a of the rotor disc 2 and two reference devices 25 26 coupled to the tie-rod 3.
  • a first measure of the eccentricity is made using the main device 24 and the reference device 25 and a second measure of eccentricity is obtained using the main device 24 and the reference device 26.
  • the reference device 25 is coupled in the proximity of the first end 15 of the tie-rod 3, while the reference device 26 is coupled in the proximity of the second end 16 of the tie-rod 3.
  • the main device 24, is coupled to the free face 13a of the rotor disc 2 whose position need to be controlled.
  • the reference device 25 is preferably fixed to the front shaft 18. More preferably, the reference device 25 is fixed to a portion 31 (see also figure 1 ) of the front shaft 18 comprised between the first rotor disc 2 and an annular seat 32 made in the front shaft 18 and configured to house, in use, a compressor collar bearing (not shown in the attached figures).
  • the reference device 25 supports three laser emitters 28, each of which is configured to emit a laser beam B substantially along a vertical direction.
  • each laser emitter 28 is coupled to a base structure 35, which is provided with a positioning device 36.
  • the positioning device 36 is configured to regulate the position of the laser emitter 28. In use, the positioning device 36 is regulated so as each laser emitter 28 of the reference device 25 emits a laser beam along a substantially vertical direction.
  • the positioning device 36 (see figure 3A ) has a plurality of degrees of freedom.
  • the positioning device 36 comprises at least two regulating elements 37a 37b which are rotatable about a respective axis of rotation 01, 02.
  • the rotation axes 01, 02 are orthogonal one with respect to the other.
  • each laser beam B emitted by the laser emitter 28 can be controlled manually or electronically.
  • the positioning device can be replaced by an orientation device similar to the ones that will described later and shown in figures 8 and 9 .
  • the reference device 25 is provided with an annular base 39 from which at least three spokes 40 protrudes (only two of which are visible in figure 3 ). Each spoke 40 has a free end 41 to which a respective laser emitter 28 is coupled.
  • the free ends 41 of the spokes 40 are arranged at 120° one from another.
  • the spokes 40 are radially arranged about the annular base 39.
  • the length of the spokes 40 is sufficiently greater than the maximum height of the compressor blades 5 and turbine blades 6 so as the free ends 41 of the spokes 40 protrude over the compressor blades 5 and turbine blades 6 when the reference device 25 is fixed to the rotor 1.
  • the annular base 30 can be opened and closed so as to allow its positioning and fixing about the portion 31 of the front shaft 18.
  • the reference device 26 is coupled to the second end 16 of the tie-rod 3 and is retractable.
  • the reference device 26 comprises one cage structure 43, which is fixed to the tie-rod 3 and at least three retractable arms 44 which are housed in the cage structure 43 and arranged at 120° one from another.
  • Each arm 44 can move from an operative position, wherein the arm 44 is extended outside the cage structure 43 (configuration shown in figures 3 and 5 ), and one rest position, wherein the arm 44 is retracted and is completely housed in the cage structure 43 (configuration shown in figure 4 ).
  • Each arm 44 is an articulated arm having one end 45 coupled to a movable bush 46 and one free end 47 coupled to a respective photosensitive sensor 30.
  • Each arm 44 is configured to have a length in the operative position so as each photosensitive sensors 30 is able to detect the laser beam B' emitted by respective laser emitter 28 supported by the main device 24 as can be detailed later.
  • the arms 44 are arranged at the same angular position of the laser beams B' emitted by the laser emitters 28.
  • the photosensitive sensors 30 coupled to the arms 44 are arranged at the same radial distance from the longitudinal axis A.
  • the movable bush 46 is arranged about a shaft 49. When the bush 46 is in the upper position (configuration shown in figure 4 ), the arms 44 are in the rest position, while when the bush 46 is in the lower position (configuration shown in figure 5 ) the arms 44 are in the operative position.
  • the bush 46 is preferably moved by a remotely controlled tool (not illustrated).
  • the main device 24 is coupled to a free face 13a of the rotor disc 2.
  • free face we here and hereinafter mean a face of the rotor disc 2 that is not coupled to a further face of the adjacent rotor disc 2.
  • the method according to the invention can be applied both during the assembling and during the disassembling of the rotor 1.
  • the detection of the position of the disc 2 takes place before a further rotor disc 2 is stacked on the rotor disc 2 being controlled, whereas, during the disassembling, the detection of the position of the rotor disc 2 takes place before the rotor disc 2 being controlled is removed.
  • the method according to the invention requires the main device 24 to be coupled to one rotor disc 2 at a time.
  • the main device 24 comprises a support 53, a centring system 54 configured to center the support 53 on the rotor disc 2 being controlled, and at least three laser emitter 28 and at least three photosensitive sensors 30 coupled to the support 53.
  • the support 53 comprises an annular frame 58 and at least three spokes 60 with protrudes radially from the annular frame 58 and are arranged at 120° one from another.
  • Each spoke 60 supports a respective photosensitive sensor 30.
  • the photosensitive sensor 30 is coupled to the side of the spoke 60 facing the free face 13a of the rotor disc 2.
  • the photosensitive sensor 30 is coupled to the side of the spoke 60 facing, in use, the reference device 25.
  • the photosensitive sensor 30 is coupled to the free end 61 of the respective spoke 60.
  • the length of the spokes 60 is sufficiently greater than the maximum height of the compressor blades 5 and turbine blades 6 so as the free ends 61 of the spokes 60 protrude over the compressor blades 5 and turbine blades 6 when the main device 24 is coupled to the rotor disc 2.
  • the sensors 30 are placed on the spokes 60 at the same angular position and at the same radial distance from the longitudinal axis A of the laser beams B emitted by the laser emitters 28 on the reference device 25. For example, the sensors 30 are placed on the spokes 60 long a circumference having a diameter of about 3.5 m.
  • the annular frame 58 has one coupling face 62 (visible in figure 6 ), which, in use, faces the rotor disc 2 being controlled, and one operating face 63 (visible in figure 7 ), which is opposite the coupling face 62.
  • the coupling face 62 is coupled to the centring system 54, while the operating face 63 supports the at least three laser emitter 28.
  • the laser emitters 28 are configured to emit respective laser beams B' and are arranged at 120° at the same radial distance from the center of the annular frame 58 (in use coinciding with the longitudinal axis A).
  • the laser emitters 28 are placed on the operating face 63 along a circumference having a diameter of about 0.6 m.
  • the spokes 60 are preferably arranged on the operating face 63.
  • the support 53 comprises a further annular element 65, which is configured to protect the electronic devices (batteries, tilting sensors, control electronics, laser emitters 28, etc.) during the movement of the main device 24.
  • the further annular element 65 is also configured so as to provide hooking points for the lifting of the support 53, for example by means of an overhead crane (not shown).
  • the support 53 has dimensions that are compatible with the dimensions of the tie-rod 3 and of the rotor discs 2 making up the rotor 1.
  • the centring system 54 comprises at least two portions 67 of a Hirth toothing annulus couplable to a respective portion of the radial teeth (Hirth) annulus 12 arranged on the free face 13a of one of the rotor discs 2 making up the rotor 1.
  • the portions 67 of the Hirth toothing annulus must be shaped so as to have a minimum radius that is equal to the inner radius of the radial teeth annulus 12 of the smallest rotor disc 2 and a maximum radius that is equal to the outer radius of the radial teeth annulus 12 of the largest rotor disc 2.
  • the portions 67 of the Hirth toothing annulus must have teeth that are oriented like the teeth of the radial teeth annulus 12, namely towards the center of the rotor discs 2, preserving all other parameters thereof (inclination of the walls of the teeth, number of teeth, etc.), so as to ensure a correct and stable coupling between the portions 67 and the radial teeth annulus 12 of the rotor discs 2.
  • the centring system 54 comprises three portions 67 that are separate and arranged on a same plane, preferably at approximately 120° from one another.
  • the three portions 67 are substantially identical.
  • Each laser emitter 28 coupled to the operating face 63 of the annular frame 58 of the support 53 is preferably coupled to an orientation device 70 ( figure 8 ) , configured to regulate the position of the laser emitter 28 so as the laser beam B' emitted by the laser emitter 28 is substantially vertical.
  • the orientation device 70 comprises a casing 71 containing a fluid 72.
  • the fluid is, for example, mercury in liquid state.
  • the casing is coupled to the operating face 63 of the annular frame 58.
  • the laser emitter 28 is arranged in the casing 71 floating on the fluid 72. As the free surface 73 of the fluid 72 is always substantially horizontal independently from the inclination of the surface 63 supporting the casing 71, the laser emitter 28 is able to emit a laser B' always substantially vertical.
  • the orientation device 70 of figure 8 works properly if the laser emitter 28 has to emit a laser beam upwards, i.e. towards the end 16 of the tie-rod 3.
  • the laser emitters 28 are coupled to the surface 62 of the annular frame 58 of the support 53 in order to emit laser beams downwards, i.e. towards the end 15 of the tie-rod 3.
  • each laser emitter 28 is coupled to an axial-symmetrical body 75, which is hinged to the surface 62 of the annular frame 58 of the support 53.
  • the body 75 due to its structure and weight, will be oriented so as the laser beam B' emitted by the laser emitter 28 is always substantially vertical independently from the inclination of the surface 62 supporting the body.
  • the laser emitters can be coupled to other kind of devices able to regulate properly the orientation of the laser beams.
  • other kind of devices able to regulate properly the orientation of the laser beams.
  • motorized device or other known laser levelling systems for example, motorized device or other known laser levelling systems.
  • the main device 24 comprises also a biaxial inclinometer 78, which is coupled to the support 53 and is configured to measure the inclination of the support 53 with respect to two orthogonal axes.
  • the biaxial inclinometer 78 measures the inclination of the rotor disc 2 to which the main device 24 is coupled.
  • the biaxial inclinometer 78 is coupled to surface 63 of the annular frame 58 of the support 53.
  • the main device 24 comprises also at least two distance detectors 80, which are coupled to the support 53 and arranged in respective points belonging to a same circumference (represented with a broken line in figure 7 ).
  • the distance detectors 80 are oriented towards the centre of the above referred circumference. In this way, in use, the distance detectors 80 detect a distance along a radial direction with respect to the tie-rod 3.
  • the main device 24 comprises three distance detectors 80, which are preferably arranged at 0°-90°-225° along the circumference.
  • the distance detectors 80 are coupled to the operative surface 63 of the annular frame 58 and are arranged at a radial distance from the centre of the annular frame 58 shorter than the radial distance of the laser emitters 28. In other words, the distance detectors 80 are arranged internally with respect to the laser emitters 28.
  • the distance detectors 80 preferably are contactless detectors, for example laser triangulation systems; the distance detectors 80 allow to measure also the eccentricity of the external surface of the tie-rod 3 (used and potentially deformed) with respect to a virtual cylinder that is coaxial with the longitudinal axis A of the rotor 1.
  • the laser emitters 28 on the reference device 25 emit laser beams B towards the photosensitive sensors 30 of the main device 24, while the laser emitters 28 of the main device 24 emit laser beams B' towards photosensitive sensors 30 of the reference device 26.
  • the reference device 25 comprises photosensitive sensors and the main device 24 comprises laser emitters emitting laser beams towards the photosensitive sensors of the reference device.
  • reference device 26 comprises laser emitters emitting laser beams towards respective photosensitive sensors 30 of the main device.
  • Each photosensitive sensor 30 is configured to detect the laser beam impacting on it and to provide the radial position of the impacting point with respect to the longitudinal axis A.
  • the photosensitive sensors 30 on the main device 24 are able to provide respective radial distances R1, R2, R3 with respect to longitudinal axis A by detecting the laser beams B emitted by the laser emitters 28 on the reference device 25 (the lower one), while the photosensitive sensors 30 on the reference device 26 (the upper one) are able to provide respective radial distances R1', R2', R3' with respect to the longitudinal axis A by detecting the laser beams B' emitted by the laser emitters 28 on the main device 24.
  • Laser emitters 28 are preferably low power laser emitters to ensure the safety of operators. In order to avoid external light noise detected by the photosensitive sensors 30, the laser emitters 28 emits laser beam with a frequency modulation. In this way, the photosensitive sensors 30 can be provided with appropriate filters.
  • the control device 8 comprises a first eccentricity calculator 86 and a second eccentricity calculator 87.
  • the first eccentricity calculator 86 is configured to elaborate the radial distances R1, R2, R3, define a circumference passing through the points detected by the sensors 30 and calculate the eccentricity value Vecc of said circumference with respect to the centre of symmetry "O" of the main device 24.
  • the radial distances R1, R2, R3 have to be fitted using an ellipse (instead of a circle); that ellipse can be calculated by taking into account the data detected by the inclinometer 78 (that is an input of block 86).
  • the second eccentricity calculator 87 is configured to elaborate the radial distances R1', R2', R3', define a circumference (or a ellipse taking into account the data of the inclinometer 78) passing through the points detected by the sensors 30 and calculate the eccentricity value Vecc' of said circumference (or ellipse) with respect to the centre of symmetry "O" of the main device 24.
  • the eccentricity values Vecc Vecc' are sent to an evaluation module 90, wherein the data about the eccentricity of each disc 2 of the rotor 1 are memorized and an assessment of the positioning of each the rotor disc 2 can be elaborated.
  • control device 85 comprises only one eccentricity calculator.
  • control device 85 comprises a further module, which is configured to give indications on possible corrective actions to be carried out in the light of the eccentricity values detected.
  • the data detected by the photosensitive sensors 30 are sent to the control device 85 by means of wi-fi communications.
  • laser emitters 28 are remotely controlled by means of wi-fi communications.
  • control device 85 is not coupled to the support 53 and is integrated in an external processor (e.g. a tablet) available to the operator who follows the assembling/disassembling of the rotor 1.
  • an external processor e.g. a tablet
  • the tablet can give the operator information on the correct positioning of the disc on the stack, respecting all tolerances, and, in any case, store the information.
  • the operators In use, for controlling the positioning of a rotor disc 2 about the tie-rod 3 the operators have to position the rotor 1 vertically by means of a crane (not shown).
  • the front shaft 18 of the rotor 1 is housed in the stacking pit 21 to ensures a correct and stable vertical positioning of the tie-rod 3.
  • the reference devices 25 and 26 are coupled to the rotor 1 respectively in the proximity of the end 15 and of the end 16 of the tie-rod 3.
  • the reference devices 25 and 26 are moved by a crane.
  • the main device 24 is arranged on the free face 13a of the rotor disc 2.
  • the positioning of the main device 24 on the rotor disc 2 is regulated so as to ensure that laser emitters 28 are substantially vertically aligned with respective photosensitive sensors 30.
  • the main device 24 is moved by using a crane.
  • the inclinometer 78 and the distance detectors 80 are activated in order to improve the controlling of the positioning of the rotor disc 2.
  • the assembly 23 and the method for controlling the positioning of the rotor disc according to the invention allow the assembling of the rotor 1 to be improved and optimized, thus avoiding assembling an unbalanced rotor and avoiding, especially, the costs deriving from one or more corrective interventions to be carried out on an already assembled rotor.
  • the assembly 23 and the method for controlling the positioning of a rotor disc according to the invention can also be applied to already assembled rotors that were assembled with the preceding assembling techniques.
  • the assembly 23 and the method according to the invention can be applied during the disassembling of the rotor 1 disc by disc.
  • the rotor discs 2 are removed one at a time and the assembly is used to detect the position of each rotor disc 2 until the rotor disc (or the rotor discs) is (are) found that is (are) responsible for the unbalance of the rotor 1.
  • the application of the assembly 23 during the disassembling of the rotor 1 is advantageous compared to currently known solutions, as it gives objective indications on the positioning of each rotor disc 2, without introducing operators' personal assessment elements.
  • the identification of an unbalance does not always lead to the replacement of the rotor disc 2.
  • the unbalance can simply be corrected by means of proper rotations of the rotor discs.
  • the device 16 has a crucial role in establishing whether the corrective actions were effective and sufficient to compensate the unbalance.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Length Measuring Devices By Optical Means (AREA)

Claims (15)

  1. Procédé de contrôle du positionnement d'au moins un disque de rotor (2) autour d'un tirant (3) d'un rotor partiellement assemblé (1) d'une turbine à gaz ; le tirant (3) s'étendant le long d'un axe longitudinal (A) ;
    le procédé comprenant :
    • le positionnement du tirant (3) de manière à ce que l'axe longitudinal (A) s'étende sensiblement verticalement ;
    • la détection de l'excentricité du disque de rotor (2) par rapport à l'axe longitudinal (A) du tirant au moyen d'un ensemble (23) comprenant un dispositif principal (24) couplé à une face libre (13a) du disque de rotor (2) et au moins un premier dispositif de référence (25, 26) couplé au tirant (3) ; l'ensemble (23) comprenant en outre au moins trois émetteurs laser (28) couplés à l'un entre le dispositif principal (24) et le au moins un premier dispositif de référence (25, 26) et au moins trois capteurs photosensibles respectifs (30) couplés à l'autre entre le dispositif principal (24) et le au moins un premier dispositif de référence (25, 26) ; les capteurs photosensibles (30) étant disposés de manière à intercepter des faisceaux laser (B) émis par les émetteurs laser respectifs (28).
  2. Procédé selon la revendication 1, dans lequel l'étape de détection de l'excentricité comprend la mesure d'une distance radiale
    (R1, R2, R3 ; Rl', R2', R3') entre l'axe longitudinal (A) et chaque faisceau laser (B) émis par les émetteurs laser (28) au moyen des au moins trois détecteurs photosensibles (30) et le signalement d'une occurrence d'excentricité (Vecc ; Vecc') sur la base des distances radiales détectées (R1, R2, R2 ; Rl', R2', R3').
  3. Procédé selon la revendication 1 ou 2, dans lequel le tirant (3) présente une première extrémité (15), qui est disposée près du sol lorsque le tirant (3) est en position verticale, et une seconde extrémité (16), axialement opposée à la première extrémité (15) ; le au moins un premier dispositif de référence (25, 26) étant couplé à proximité de la première extrémité (15) et/ou de la seconde extrémité (16) .
  4. Procédé selon l'une quelconque des revendications précédentes, dans lequel le au moins un dispositif de référence (25 ; 26) comprend au moins trois éléments de support (40 ; 44), chacun d'eux supportant un élément entre l'émetteur laser (28) et le capteur photosensible (30).
  5. Procédé selon la revendication 3 ou 4, dans lequel l'ensemble (23) comprend un second dispositif de référence (26) ; le premier dispositif de référence (25) étant couplé à proximité de la première extrémité (15) et le second dispositif de référence étant couplé à la seconde extrémité (16) .
  6. Procédé selon la revendication 5, dans lequel l'étape de détection de l'excentricité du disque de rotor (2) comprend :
    la mesure d'une première distance radiale (R1, R2, R2) entre l'axe longitudinal (A) et chaque faisceau laser (B) émis par des premiers émetteurs laser (28) disposés sur le premier dispositif de référence (25) au moyen d'au moins trois premiers détecteurs photosensibles (30) disposés sur le dispositif principal (24) ;
    la mesure d'une seconde distance radiale (R1', R2', R3') entre l'axe longitudinal (A) et chaque faisceau laser (B') émis par des seconds émetteurs laser (28) disposés sur le dispositif principal (24) au moyen d'au moins trois seconds détecteurs photosensibles (30) disposés sur le second dispositif de référence (26) ;
    le signalement d'une seconde occurrence d'excentricité (Vecc') sur la base des secondes distances radiales (R1', R2', R3').
  7. Procédé selon l'une quelconque des revendications précédentes, dans lequel au moins un émetteur laser (28) est couplé à un dispositif d'orientation (70, 75) configuré pour réguler la position de l'émetteur laser (28) de sorte que le faisceau laser (B) émis par l'émetteur laser (28) soit sensiblement vertical.
  8. Procédé selon l'une quelconque des revendications précédentes, comprenant également l'étape consistant à mesurer l'inclinaison au moyen d'un inclinomètre (78) couplé au dispositif principal (24).
  9. Ensemble pour contrôler le positionnement d'au moins un disque de rotor (2) autour d'un tirant (3) d'un rotor (1) partiellement assemblé d'une turbine à gaz ; le tirant (3) s'étendant le long d'un axe longitudinal (A) ; l'ensemble comprenant :
    • un dispositif principal (24) couplé, en utilisation, à une face libre (13a) du disque de rotor (2) ; et
    • au moins un premier dispositif de référence (25, 26) couplé, en cours d'utilisation, au tirant (3) ; caractérisé en ce que
    • au moins trois émetteurs laser (28) couplés à l'un entre le dispositif principal (24) et le au moins un premier dispositif de référence (25, 26) ; et
    • au moins trois capteurs photosensibles respectifs (30) couplés l'un à l'autre entre le dispositif principal (24) et le au moins un premier dispositif de référence (25, 26) ; les capteurs photosensibles (30) étant disposés de manière à intercepter des faisceaux laser (B) émis par des émetteurs laser respectifs (28).
  10. Ensemble selon la revendication 9, dans lequel les au moins trois détecteurs photosensibles (30) sont configurés pour mesurer une distance radiale (R1, R2, R3 ; Rl', R2', R3') entre l'axe longitudinal (A) et chaque faisceau laser (B) émis par les émetteurs laser (28).
  11. Ensemble selon la revendication 10, comprenant un dispositif de commande (85) configuré pour signaler une occurrence d'excentricité (Vecc ; Vecc') sur la base des distances radiales détectées (R1, R2, R2 ; Rl', R2', R3').
  12. Ensemble selon l'une quelconque des revendications 9 à 11, dans lequel le au moins un dispositif de référence (25 ; 26) comprend au moins trois éléments de support (40 ; 44), chacun d'eux supportant un élément entre l'émetteur laser (28) et le capteur photosensible (30).
  13. Ensemble selon l'une quelconque des revendications 9 à 12, dans lequel le au moins un premier dispositif de référence (25, 26) est couplé, en cours d'utilisation, à proximité d'une première extrémité (15) et/ou d'une seconde extrémité (16) du tirant (3).
  14. Ensemble selon la revendication 13, comprenant un second dispositif de référence (26) ; le premier dispositif de référence (25) étant couplé à proximité de la première extrémité (15) et le second dispositif de référence étant couplé à la seconde extrémité (16).
  15. Ensemble selon l'une quelconque des revendications 9 à 14, dans lequel au moins un émetteur laser (28) est couplé à un dispositif d'orientation (70, 75) configuré pour réguler la position de l'émetteur laser (28) de sorte que le faisceau laser (B) émis par l'émetteur laser (28) soit sensiblement vertical.
EP20169754.7A 2020-04-16 2020-04-16 Procédé et dispositif pour commander le positionnement d'au moins un disque de rotor autour d'un tirant d'un rotor assemblé partiellement Active EP3896252B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP20169754.7A EP3896252B1 (fr) 2020-04-16 2020-04-16 Procédé et dispositif pour commander le positionnement d'au moins un disque de rotor autour d'un tirant d'un rotor assemblé partiellement
CN202110410829.9A CN113530608A (zh) 2020-04-16 2021-04-16 用于控制至少一个转子盘围绕部分组装的转子的连杆的定位的方法和组件

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EP20169754.7A EP3896252B1 (fr) 2020-04-16 2020-04-16 Procédé et dispositif pour commander le positionnement d'au moins un disque de rotor autour d'un tirant d'un rotor assemblé partiellement

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EP3896252B1 true EP3896252B1 (fr) 2023-04-12

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Publication number Priority date Publication date Assignee Title
US3916495A (en) * 1974-02-25 1975-11-04 Gen Electric Method and means for balancing a gas turbine engine
EP3140513B1 (fr) * 2014-05-09 2019-04-24 Ansaldo Energia S.p.A. Procédé et appareil auxiliaire d'équilibrage d'un rotor d'une turbine à gaz
IT201600123382A1 (it) 2016-12-05 2018-06-05 Ansaldo Energia Spa Metodo e dispositivo per controllare il posizionamento di almeno un disco rotorico attorno ad un tirante di un rotore di una turbina a gas

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CN113530608A (zh) 2021-10-22

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