EP2792849A1 - 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
EP2792849A1
EP2792849A1 EP14170640.8A EP14170640A EP2792849A1 EP 2792849 A1 EP2792849 A1 EP 2792849A1 EP 14170640 A EP14170640 A EP 14170640A EP 2792849 A1 EP2792849 A1 EP 2792849A1
Authority
EP
European Patent Office
Prior art keywords
assembly
blade
blades
axial
rotor
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.)
Granted
Application number
EP14170640.8A
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German (de)
English (en)
Other versions
EP2792849B1 (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 assembly in two spaced apart correction planes which extend perpendicular to the geometric axis of the 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 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 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.
  • 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 the 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 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 fixing arrangement 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 fan assembly 1 for a gas turbine.
  • the fan 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 fan assembly 1, rotates about a centreline (CL) of the assembly (representing the geometric axis of rotation of the fan assembly 1).
  • the centreline will coincide with a principal axis of inertia of the fan assembly, so that the fan assembly is dynamically balanced.
  • the dynamic imbalance in the final 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 fan 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 fan 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 fan 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 fan 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 fan assembly 1 in accordance with the present invention, in this case following correction of a static imbalance in the fan 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 fan assembly 1 is provided at least in part by axial adjustment of the blade 2a.
  • Figure 5 shows an axial fixing arrangement 7 for allowing convenient axial adjustment of a blade 2 on the rotor disc 3.
  • the axial fixing arrangement 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 fixing arrangement 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 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.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
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)

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

Family

ID=50943069

Family Applications (1)

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

Country Status (1)

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EP (1) EP2792849B1 (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0609979A1 (fr) * 1993-02-03 1994-08-10 ROLLS-ROYCE plc Rotor équilibré pour une turbine à gaz
EP1452687A2 (fr) * 2003-02-27 2004-09-01 Rolls-Royce Plc Equilibrage de rotor
EP1995467A1 (fr) * 2006-03-13 2008-11-26 IHI Corporation Structure support pour pale de ventilateur
EP2677119A2 (fr) * 2012-06-20 2013-12-25 Rolls-Royce plc Procédé d'équilibrage d'un rotor

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0609979A1 (fr) * 1993-02-03 1994-08-10 ROLLS-ROYCE plc Rotor équilibré pour une turbine à gaz
EP1452687A2 (fr) * 2003-02-27 2004-09-01 Rolls-Royce Plc Equilibrage de rotor
EP1995467A1 (fr) * 2006-03-13 2008-11-26 IHI Corporation Structure support pour pale de ventilateur
EP2677119A2 (fr) * 2012-06-20 2013-12-25 Rolls-Royce plc Procédé d'équilibrage d'un rotor

Also Published As

Publication number Publication date
EP2792849B1 (fr) 2016-07-13

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