EP2792849B1

EP2792849B1 - Developments in or relating to rotor balancing

Info

Publication number: EP2792849B1
Application number: EP14170640.8A
Authority: EP
Inventors: Andrew Rix
Original assignee: Rolls Royce PLC
Current assignee: Rolls Royce PLC
Priority date: 2014-05-30
Filing date: 2014-05-30
Publication date: 2016-07-13
Anticipated expiration: 2034-05-30
Also published as: EP2792849A1

Description

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.
In a bladed rotor assembly such as a fan blade assembly in a gas turbine, 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.
During manufacture of the components making up the bladed rotor assembly, efforts are made to minimise mass imbalances in the individual components. Nevertheless, mass imbalances will tend to arise in the completed assembly, for example due to manufacturing tolerances on the blades. Consequently, the assembly as a whole must undergo an initial balancing operation in order to prevent subsequent stress and vibration during operation of the bladed rotor assembly.
In order to balance the final bladed rotor assembly, 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. In either case 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. In addition, 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.
According to the present invention there is provided 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. In particular, 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.
According to another aspect of the invention, there is provided 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.
Embodiments of the invention will now be described, by way of example, with reference to the accompanying drawings, in which:

Figure 1 is a schematic plan view of a bladed rotor assembly;
Figure 2 is a view corresponding to Figure 1, but illustrating axial offsetting of a pair of rotor blades in accordance with the present invention;
Figure 3 is a view corresponding to Figure 1, illustrating a supplementary two plane balancing correction on the bladed rotor assembly according to a further aspect of the present invention;
Figure 4 is a view of corresponding to Figure 1, illustrating use of a single axially-offset blade to form a counterbalancing couple with a correction mass, according to a further aspect of the present invention; and
Figure 5 is a schematic cross-sectional view through part of a bladed rotor assembly illustrating one possible axial blade fixing for allowing convenient axial adjustment of the blades.

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).
Ideally, the centreline will coincide with a principal axis of inertia of the bladed rotor assembly, so that the bladed rotor assembly is dynamically balanced.
In practice, however, mass imbalances caused by manufacturing and fitting tolerances will tend to misalign the principal inertial axis with the centreline of the bladed rotor assembly, with the result that the final bladed rotor assembly will often suffer a dynamic imbalance.
In general, 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 θ 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. By controlling the moment arm of this counterbalancing couple (F_blade1, F_blade2), corresponding to the blade offset x, the principal axis of inertia may thus be realigned with the centreline, as indicated by the arrow A in Figure 2.
It is envisaged that use of the blades 2 to form a counterbalancing couple will reduce the weight penalty associated with conventional two-plane balancing correction by addition or removal of mass from the bladed rotor assembly (in the latter case, by reducing the need for relatively heavy balancing lands).
Although in the embodiment shown 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. In this case, 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.
For a given rotor, a larger counterbalancing couple can be achieved using multiple blade pairs than would be possible using only a single blade pair. In addition, where multiple blade pairs are used to form a given counterbalancing couple, 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.
Depending upon the magnitude of the imbalance couple, it may be necessary to carry out a supplementary two plane balancing correction by adding correction masses 6 as shown in Figure 3. Nevertheless, it will be appreciated that axial adjustment of the blades 2 to reduce the dynamic imbalance will allow for the correction masses 6 to be smaller than would ordinarily be the case carrying out a conventional two plane balancing correction. The use of additional correction masses may be required in particular where a counterbalancing couple is formed by off-setting a pair of blades 2 which are not diametrically opposed to one another.
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.
Figure 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. Here, 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. It will be appreciated here that 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. It will be appreciated that the spring clip 11 retains the blade 2 in axial position against the set screw 8, both during and in between axial adjustments.
Though not essential, 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. For example, the blades may be axially secured using an adjustable shim.
It will be appreciated that although embodiments of the invention have been described in relation to dynamic imbalances caused by irregular mass distribution within one or more components of the bladed rotor assembly, the present invention is equally suitable for reducing dynamic imbalances caused by misalignment between components within a bladed rotor assembly, including angular misalignment of a rotor disc.
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. However, 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

A method of reducing dynamic imbalance in a bladed rotor assembly (1) having axial blade fixings (7), characterised in that the reduction in dynamic imbalance is provided at least in part by axial adjustment of one or more of the blades (2) so as to redistribute mass along the geometric axis of rotation of the bladed rotor assembly (1).
A method according to claim 1, wherein the reduction in dynamic imbalance is provided at least in part by axially offsetting a pair of the blades (2) so as to form a counterbalancing couple.
A method according to claim 2, wherein the counterbalancing couple is provided by axially offsetting a diametrically opposed pair of the blades (2).
A method according to claim 2 or 3, wherein the counterbalancing couple is provided by axially offsetting a plurality of such pairs of blades (2).
A method according to any one of claims 1 to 4, comprising providing a supplementary balancing correction by adding mass to, or removing mass from, the bladed rotor assembly (1) in one or more correction planes positioned along the geometric axis of rotation of the rotor (3).
A method according to any preceding claim, wherein the bladed rotor assembly (1) is a turbine assembly, compressor assembly or fan assembly for a gas turbine.
A bladed rotor assembly (1) comprising a plurality of blades (2) mounted in axial blade slots on a rotor disc (3), at least one of the blades (2) being secured in the respective blade slot by an axial blade fixing (7), characterised in that the axial blade fixing comprises a set screw (8) acting between the rotor disc and the blade (2) for axially adjusting the position of the blade (2), the bladed rotor assembly further comprises a biasing member (11) acting between the blade (2) and the rotor disc (3) for holding the blade (2) in axial position against the set screw (8).