EP2792849B1 - Perfectionnements à ou se rapportant à l'équilibrage d'un rotor - Google Patents

Perfectionnements à ou se rapportant à l'équilibrage d'un rotor Download PDF

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Publication number
EP2792849B1
EP2792849B1 EP14170640.8A EP14170640A EP2792849B1 EP 2792849 B1 EP2792849 B1 EP 2792849B1 EP 14170640 A EP14170640 A EP 14170640A EP 2792849 B1 EP2792849 B1 EP 2792849B1
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EP
European Patent Office
Prior art keywords
blade
blades
rotor assembly
bladed rotor
axial
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.)
Not-in-force
Application number
EP14170640.8A
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German (de)
English (en)
Other versions
EP2792849A1 (fr
Inventor
Andrew Rix
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.)
Rolls Royce PLC
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Rolls Royce PLC
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Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to EP14170640.8A priority Critical patent/EP2792849B1/fr
Publication of EP2792849A1 publication Critical patent/EP2792849A1/fr
Application granted granted Critical
Publication of EP2792849B1 publication Critical patent/EP2792849B1/fr
Not-in-force 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
    • 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
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Definitions

  • the present invention relates to rotor balancing and, in particular, to a method of reducing dynamic imbalance in a bladed rotor assembly having axial blade fixings.
  • the invention is particularly suitable for use in weight-critical applications such as in bladed rotor assemblies in gas turbines for aerospace applications.
  • the invention is not, however, limited to gas turbine applications.
  • the blades are manufactured separately and then assembled together on one or more rotor discs using suitable blade fixings.
  • the blade fixings generally take the form of either circumferential blade fixings, where a root portion of each blade is located in a circumferential slot machined out of the rotor disc, or axial blade fixings, where the blades comprise an axial root portion which slides axially into respective axial mounting slots in the rotor disc.
  • a two plane balancing correction is typically carried out by addition or removal of mass from the bladed rotor assembly in two spaced apart correction planes which extend perpendicular to the geometric axis of the bladed rotor assembly.
  • this involves a weight penalty, either from the direct effect of adding a balancing mass, or because the removal of material means that sacrificial balancing lands need to be provided which add to the weight of the bladed rotor assembly.
  • the weight penalty can in principle be reduced by increasing the separation of the correction planes along the geometric axis of rotation to increase the coupling moment of the balancing masses, but in practical terms this is often not viable due to space constraints.
  • an increased separation of the balancing masses tends to increase bending of the rotor shaft at or near resonant frequencies of the bladed rotor assembly.
  • This bending of the rotor shaft can be reduced or nearly eliminated by using multi-plane balancing techniques, but again space constraints can make it difficult to provide multiple balancing lands, or sufficient space for mounting balancing masses in multiple planes.
  • EP 0 609 979 A1 discloses a balanced rotor for a gas turbine engine comprises a disc having an annular array of aerofoil blades each of which has a fir-tree root portion which locates in a corresponding groove in the disc.
  • the blade root portions are retained axially by retention plates located in an annular array on the rotor adjacent the root portions. A minority of the retention plates are lighter than the remainder. The lighter plates are so distributed around the rotor as to ensure the balance of the rotor.
  • EP 1 995 456 A2 discloses a fan blade retaining structure comprising a disk having a plurality of circumferentially spaced dovetail grooves each of which accommodates a fan blade.
  • the disk further comprises a radially outwardly extending flange positioned ahead of the dovetail grooves.
  • a ring-shape retainer member locates the blade against the flange.
  • EP 1 452 687 A2 discloses a method of balancing a rotor, by first determining the position of the centre of mass of a rotor to be balanced prior to the rotor being machined to its final dimensions, and subsequently machining the rotor to its final dimensions by removing material along the length of the rotor. The material is removed in the direction of its axis such that the centre of mass of the rotor is adjusted to be substantially co-incident with its axis of rotation.
  • EP 2 677 119 A2 discloses a method of balancing a rotor in which a balance correction mass is identified, with a material deposition process being subsequently performed on the rotor to add the selected balance correction mass. It is an object of the present invention to seek to provide an improved method for reducing dynamic imbalance in a bladed rotor assembly having axial blade fixings.
  • a method of reducing dynamic imbalance in a bladed rotor assembly having axial blade fixings wherein the reduction in dynamic imbalance is provided at least in part by axial adjustment of one or more of the blades so as to redistribute mass along the geometric axis of rotation of the bladed rotor assembly.
  • the reduction in dynamic imbalance may be provided at least in part by axially offsetting a pair of the blades so as to form a counterbalancing couple.
  • the counterbalancing couple may be provided by axially offsetting a diametrically opposed pair of the blades.
  • the counterbalancing couple may be provided by axially offsetting a plurality of such pairs of blades.
  • the method may comprise providing a supplementary balancing correction by adding mass to, or removing mass from, the bladed rotor assembly in one or more correction planes positioned along the geometric axis of rotation of the rotor.
  • the bladed rotor assembly may be a turbine assembly, compressor assembly or fan assembly for a gas turbine.
  • a bladed rotor assembly having axial blade fixings, at least one of the blades being secured by an axial blade fixing comprising a set screw acting between the rotor disc and the blade for axially adjusting the position of the blade, and a biasing member acting between the blade and the rotor disc for holding the blade in axial position against the set screw.
  • Figure 1 shows a bladed rotor assembly 1 for a gas turbine.
  • the bladed rotor assembly 1 comprises a plurality of separately manufactured blades 2 (only two of which are visible in Figure 1 ) mounted on a rotor disc 3.
  • the blades 2 incorporate axial root portions (not shown) which locate in corresponding axial slots machined out of the rotor disc 3.
  • the rotor disc 3 is carried on a rotor shaft 4 which, in operation of the bladed rotor assembly 1, rotates about a centreline (CL) of the bladed rotor assembly (representing the geometric axis of rotation of the bladed rotor assembly 1).
  • the centreline will coincide with a principal axis of inertia of the bladed rotor assembly, so that the bladed rotor assembly is dynamically balanced.
  • the dynamic imbalance in the final bladed rotor assembly will include a so-called “couple imbalance”, wherein equal mass imbalances located in angular opposition to one another (ie 180° apart) form a 'couple', tending angularly to misalign the principal axis of inertia and the centreline.
  • Figure 1 shows the bladed rotor assembly 1 having a couple imbalance caused by angularly opposed “heavy spots” 5, and the resulting angular misalignment ⁇ of the principal axis of inertia (PIA) with the centreline.
  • the couple imbalance is indicated by the arrows F1 and F2.
  • the dynamic imbalance of the bladed rotor assembly 1 is reduced in accordance with the present invention by axially offsetting a diametrically opposed pair of the blades 2, thus re-distributing mass along the centreline of the bladed rotor assembly 1, as shown in Figure 2
  • the off-set blades 2 form a "two-plane" counterbalancing couple, indicated by the arrows F blade1 and F blade2 in Figure 2 , which counteracts the couple imbalance F1, F2.
  • this counterbalancing couple F blade1 , F blade2
  • the principal axis of inertia may thus be realigned with the centreline, as indicated by the arrow A in Figure 2 .
  • a counterbalancing couple is formed by axially off-setting only a single pair of diametrically opposed blades 2, a plurality of pairs of blades may alternatively be axially-offset to form a corresponding, resultant counterbalancing couple.
  • the magnitude and plane of the resultant counterbalancing couple may be determined for a given plurality of axially-offset blade pairs using conventional vector addition.
  • a larger counterbalancing couple can be achieved using multiple blade pairs than would be possible using only a single blade pair.
  • the axial off-set of each individual blade pair may be smaller than in the case where only a single blade pair is used to form the counterbalancing couple; this may be particularly advantageous in the case where large individual blade off-sets would compromise the aerodynamic efficiency of the rotor.
  • the correction masses 6 may also be used to correct any static component of dynamic imbalance in the bladed rotor assembly 1, in particular where static imbalance in the bladed rotor assembly cannot be fully corrected by interchanging the location of the blades according to their inertial mass moment.
  • FIG. 4 shows an alternative embodiment for reducing a dynamic imbalance in a bladed rotor assembly 1 in accordance with the present invention, in this case following correction of a static imbalance in the bladed rotor assembly 1.
  • the static imbalance has been corrected by removing part of a balancing land 6a (the removed part of the balancing land 6a is indicated in phantom in Figure 4 ).
  • Resulting couple imbalance between the balancing land 6a and the centre of gravity C disc is corrected by axially off-setting single blade 2a to form a suitable counterbalancing couple.
  • the reduction in dynamic imbalance of the bladed rotor assembly 1 is provided at least in part by axial adjustment of the blade 2a.
  • Figure 5 shows an axial blade fixing 7 for allowing convenient axial adjustment of a blade 2 on the rotor disc 3.
  • the axial blade fixing 7 comprises a set screw 8, in this case a grub screw, extending through a segmented lock plate 9 which sits in a circumferential channel 10 fixed on the rotor disc 3.
  • a biasing member in the form of a spring clip 11 acts between the rotor disc 3 and the blade root 2b to hold the blade 2 against the set screw 8, thus locking the lock plate 9 against the side of the channel 10, as indicated by the arrow A.
  • the set screw 8 thus acts between the rotor disc 3 and the blade 2 and can be used to axially adjust the position of the blade root 2b in the respective blade slot, as indicated by the arrow B.
  • the spring clip 11 retains the blade 2 in axial position against the set screw 8, both during and in between axial adjustments.
  • corresponding circumferential channel sections 12 may be provided on the rotor disc 3, in between blade slots (only one channel section 12 is visible in Figure 5 ).
  • any other suitable axial blade fixing may be provided for the blades.
  • the blades may be axially secured using an adjustable shim.
  • the present invention finds particular application in high speed rotating machinery such as bladed rotor assemblies in gas turbines, including fan assemblies, turbines assemblies and compressor assemblies.
  • the invention is not intended to be limited to such applications and, in general, may be used on any suitable bladed rotor assembly having axial blade fixings.

Claims (7)

  1. Une méthode de réduction du déséquilibre dynamique d'un ensemble de rotor à aubes (1) avec fixations axiales des aubes (7), caractérisée en ce que la réduction du déséquilibre dynamique est assurée, du moins en partie, par l'ajustage axial d'une ou plusieurs des aubes (2) de façon à redistribuer la masse le long de l'axe de rotation géométrique de l'ensemble de rotor à aubes (1).
  2. Une méthode selon la revendication 1, la réduction du déséquilibre dynamique étant assurée, du moins en partie, par le décalage axial d'une paire d'aubes (2) de façon à former un couple de contrebalancement.
  3. Une méthode selon la revendication 2, le couple de contrebalancement étant réalisé par le décalage axial d'une paire diamétralement opposée des aubes (2).
  4. Une méthode selon la revendication 2 ou 3, le couple de contrebalancement étant réalisé par le décalage axial d'une pluralité desdites paires d'aubes (2).
  5. Une méthode selon une quelconque des revendications 1 à 4, comprenant l'exécution d'une rectification supplémentaire de l'équilibrage en ajoutant de la masse à l'ensemble de rotor à aubes (1), ou en réduisant la masse de celui-ci, dans un ou plusieurs plans de correction positionnés le long de l'axe de rotation géométrique du rotor (3).
  6. Une méthode selon une quelconque des revendications précédentes, l'ensemble de rotor à aubes (1) étant un assemblage de turbine, un assemblage de compresseur, ou un assemblage de soufflante pour une turbine à gaz.
  7. Un assemblage de rotor à aubes (1) comprenant une pluralité d'aubes (2) montées dans des fentes d'aubes axiales sur un disque de rotor (3), au moins une des aubes (2) étant fixée dans la fente à aube correspondante par une fixation d'aube axiale (7), caractérisé en ce que la fixation d'aube axiale comprend une vis d'arrêt (8) agissant entre le disque de rotor et l'aube (2) pour l'ajustage axial de la position de l'aube (2), l'assemblage de rotor à aubes comprenant en outre un dispositif de sollicitation (11) agissant entre l'aube (2) et le disque de rotor (3) pour maintenir l'aube (2) dans sa position axiale contre la vis d'arrêt (8).
EP14170640.8A 2014-05-30 2014-05-30 Perfectionnements à ou se rapportant à l'équilibrage d'un rotor Not-in-force EP2792849B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP14170640.8A EP2792849B1 (fr) 2014-05-30 2014-05-30 Perfectionnements à ou se rapportant à l'équilibrage d'un rotor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14170640.8A EP2792849B1 (fr) 2014-05-30 2014-05-30 Perfectionnements à ou se rapportant à l'équilibrage d'un rotor

Publications (2)

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EP2792849A1 EP2792849A1 (fr) 2014-10-22
EP2792849B1 true EP2792849B1 (fr) 2016-07-13

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EP14170640.8A Not-in-force EP2792849B1 (fr) 2014-05-30 2014-05-30 Perfectionnements à ou se rapportant à l'équilibrage d'un rotor

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Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9302064D0 (en) * 1993-02-03 1993-03-24 Rolls Royce Plc Balanced rotor
GB2398882B (en) * 2003-02-27 2007-09-05 Rolls Royce Plc Rotor balancing
JP2007247406A (ja) * 2006-03-13 2007-09-27 Ihi Corp ファンブレードの保持構造
GB201210870D0 (en) * 2012-06-20 2012-08-01 Rolls Royce Plc Rotor balancing method

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EP2792849A1 (fr) 2014-10-22

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