FR3133214A1 - IMPROVED SYSTEM FOR CONTROLLING RECTIFIER BLADE OF A COMPRESSOR FOR AIRCRAFT TURBOMACHINE - Google Patents

Abstract

The invention relates to a system (22) for controlling rectifier blades of a compressor for an aircraft turbomachine, comprising a linear actuation device (44), a first horn (34a) and a second horn (34b) , and a synchronization member (40) connecting the two horns (34a, 34b). The invention is carried out in such a way that the articulation points (P, P1-P6) between the moving parts of the system do not form a critical cusp point, thanks to elastic return means acting on at least one of these parts. Figure 3.

Description

IMPROVED SYSTEM FOR CONTROLLING RECTIFIER BLADE OF A COMPRESSOR FOR AIRCRAFT TURBOMACHINE

The present invention relates to systems for controlling rectifier blades of an aircraft turbomachine compressor.

The invention applies to any type of turbomachine, in particular turbojets and turboprops.

STATE OF PRIOR ART

Turbomachine compressor rectifiers correspond to stator wheels, comprising variable-pitch vanes also called VSV vanes (from the English “Variable Stagger Vanes”).

A control system is provided to control the incidence setting of these blades, that is to say to simultaneously control the angle of incidence of each of the blades of the same straightener, according to the aerodynamic need within the compressor. Such a timing control system is for example known from document EP 1 489 267 A1.

The control system may be required to control several rectifiers of a compressor, for example two rectifiers. In such a case, the control system conventionally provides two control horns, respectively dedicated to the two rectifiers. A synchronization device connects these two horns to allow their simultaneous operation.

The two horns and the synchronization member form a kinematic assembly within which these three parts are in movement relative to each other, during the blade timing change phases. Indeed, the control system is configured so as to be able to simultaneously move the first and second horns between a first extreme angular position and a second opposite extreme angular position, respectively intended to place the vanes of the rectifier in a maximum closed position, and in a maximum open position.

The kinematics of the three parts of the set must meet specific criteria, in particular on the size which must remain as restricted as possible. The kinematics chosen must also prohibit the presence of critical points, commonly referred to as kinematic turnaround points. In known manner, a kinematic cusp corresponds to a point of articulation between two parts of the kinematics, when this point is aligned and located between two other points of articulation belonging respectively to the two other parts considered. The critical nature of this situation is explained by the fact that once reached, it can lead to no longer controlling the relative direction of rotation between the two parts, when the kinematic assembly continues to move.

This type of risk of malfunction of the control system must be avoided, which is why the kinematics are usually determined so as not to encounter any cusps over the entire travel of the horns, between their first and second angular positions. extremes. For example, the kinematics can be planned to approach a first cusp point, without reaching it, when the two horns adopt their first extreme angular position, and in the same way for a second cusp point when the two puppets adopt their second extreme opposite angular position.

Clearances exist between the parts of the kinematic assembly, and they are likely to increase over the life of the control system. These games require additional caution in the design of the kinematics, always in order to avoid the presence of cusp points. This caution in design can have an impact on the sizing and overall size of the control system, which is of course not desirable.

To respond at least partially to the problems mentioned above relating to the achievements of the prior art, the invention firstly relates to a system for controlling rectifier blades of a compressor for an aircraft turbomachine, the system comprising:

- a linear actuation device;

- a first horn comprising a first branch as well as a second branch connected to each other and respectively having a first distal end as well as a second distal end, the first horn being intended to control the setting of the blades of a first compressor rectifier;

- a second horn comprising a third branch as well as a fourth branch connected to each other and respectively having a third distal end as well as a fourth distal end, the second horn being intended to control the setting of the blades of a second compressor rectifier;

- a synchronization member connecting the two horns;

- a rotating control member of the first horn, connecting the linear actuation device to this first horn;

- a first and a second output member;

and the system defining:

- a first point of articulation between the first distal end of the first horn, and one end of the synchronization member;

- a second point of articulation between the second distal end of the first horn, and one end of the first output member;

- a third point of articulation between the third distal end of the second horn, and another end of the synchronization member;

- a fourth point of articulation between the fourth distal end of the second horn, and one end of the second output member;

- a fifth articulation point of the first horn on a fixed part of the control system;

- a sixth articulation point of the second horn on the fixed part of the control system;

the control system being configured so as to be able to move the first and second horns between a first extreme angular position and a second opposite extreme angular position, respectively intended to place the rectifier vanes in a maximum closing position and a maximum closing position opening, or vice versa.

According to the invention, during a movement of the horns towards the first extreme angular position, the first, third and sixth articulation points define a first obtuse angle which increases until reaching a first maximum value of obtuse angle when the puppets occupy their first extreme angular position,

and when the horns move towards the second extreme angular position, the fifth, first and third articulation points define a second obtuse angle which increases until reaching a second maximum value of obtuse angle when the horns occupy their second extreme angular position.

The control system according to the invention further comprises:

- a first elastic return means cooperating with a first associated element among any of the horns and the synchronization member, the control system being designed so that the first elastic return means is requested at least during one end of travel of the horns towards the first extreme angular position as well as in this same first extreme angular position, so as to generate on its first associated element forces leading the horns to be requested towards their second extreme angular position; and or

- a second elastic return means cooperating with a second associated element among any of the horns and the synchronization member, the control system being designed so that the second elastic return means is requested at least during one end of travel of the horns towards the second extreme angular position as well as in this same second extreme angular position, so as to generate on its second associated element forces leading the horns to be biased towards their first extreme angular position.

The invention is thus advantageous in that it presents a kinematics making it possible to approach turning points, even as closely as possible, without risking reaching them due to the presence of the elastic return means(s) active at the end of the point. race. Indeed, each of these two elastic return means firstly makes it possible to avoid reaching a critical reversal point at the end of travel in a given direction of rotation of the horns. In addition, when starting a stroke in the opposite direction of rotation, it also makes it possible to apply a restoring force in a direction favoring the rotation of the horns in the new desired direction. Also, even in the presence of significant clearance between the parts of the kinematics, the risk of reaching reversal points following a reversal of stroke of the horns occupying their first or second extreme angular position, proves advantageously low, even reduced to nothing.

Thanks to the design of the control system according to the invention, the extreme angular positions of the horns can therefore be fixed without risk as close as possible to positions inducing critical points of reversal, which makes it possible to reduce the overall size of this system.

The invention also preferably presents the following optional features, taken individually or in combination.

The first elastic return means is a slat, and/or the second elastic return means is a slat.

Preferably, the first and second elastic return means are formed by the same strip, for great simplicity of production.

Preferably, the strip forming the first elastic return means comprises a first deformed zone defining a boss for supporting said first associated element, and/or the strip forming the second elastic return means comprises a second deformed zone defining a boss for the support of said second associated element. The shape of the boss makes it possible to optimize contact with the associated element, against which the slat is intended to bear.

Preferably, the fixed part of the control system comprises a housing on which the two horns are articulated, the housing being intended to be fixed on a compressor casing.

Preferably, the first and/or the second elastic return means are fixed to the housing, preferably by rivets. This contributes to the simplification of the ordering system.

Preferably, said first associated element and/or said second associated element are formed by the first horn, the first elastic return means cooperating with the first branch, and/or the second elastic return means cooperating with the second branch. Other solutions nevertheless remain possible, without departing from the scope of the invention. For example, the first associated element could be the first horn, and the second associated element could be the second horn.

Preferably, the first and second output members are respectively formed by a first connecting rod and a second connecting rod, and the control system comprises a first ring for controlling the timing of the blades of the first rectifier, controlled by the first connecting rod, and/or it includes a second ring for controlling the timing of the blades of the second rectifier, controlled by the second connecting rod.

The invention also relates to a compressor for an aircraft turbomachine comprising a system for controlling rectifier blades as described above.

Finally, the invention also relates to an aircraft turbomachine comprising at least one such compressor.

Other advantages and characteristics of the invention will appear in the detailed non-limiting description below.

This description will be made with reference to the appended drawings including:

represents a schematic view in axial section of an aircraft turbomachine according to the invention;

represents an enlarged perspective view of a part of a compressor of the turbomachine shown in the previous figure;

represents a radially exterior view showing a rectifier blade control system according to a preferred embodiment of the invention, the horns of this control system being represented in their first extreme angular position;

represents a schematic view similar to the previous one, with the horns of the control system represented in an intermediate position;

represents a view similar to that of the , without the control system box;

represents a view similar to the previous one, with the horns of the control system represented in their second extreme angular position;

represents a view similar to that of the , further showing the housing as well as the elastic return means cooperating with the horns of the control system;

is a partial perspective view of the control system, in its state as shown in the previous figure;

is a perspective view of the elastic return means shown in Figures 7 and 8; And

is a radially exterior view showing the first horn in its first extreme angular position, and cooperating with its associated elastic return means.

With reference first to the , there is shown an aircraft turbomachine 1, according to a preferred embodiment of the invention. This is a dual-flow, dual-body turbojet engine. However, it could be a turbomachine of another type, for example a turboprop, without departing from the scope of the invention.

The turbojet 1 has a central longitudinal axis 2 around which its various components extend. It comprises, from upstream to downstream in a main direction 5 of gas flow through this turbojet, a fan 3, a low pressure compressor 4, a high pressure compressor 6, a combustion chamber 11, a high pressure turbine 7 and a low pressure turbine 8.

Conventionally, after passing through the fan, the air is divided into a central primary flow 12a and a secondary flow 12b which surrounds the primary flow. The primary flow 12a flows in a main stream 14a for circulating the gases passing through the compressors 4, 6, the combustion chamber 11 and the turbines 7, 8. The secondary flow 12b flows in a secondary stream 14b delimited radially outwards by an engine casing, surrounded by a nacelle 9.

The compressors 4, 6 and the turbines 7, 8 are produced by the alternation of moving wheels, called rotor wheels, and fixed wheels, called stator wheels. In the context of compressors 4, 6, the stator wheels are conventionally called compressor rectifiers.

The invention relates to the design of these rectifiers, within any one of the compressors 4, 6. Subsequently, a preferred embodiment will be described where the invention is integrated into the low pressure compressor 4, but the The invention therefore also proves to be applicable to the high pressure compressor 6.

There represents a part of the low pressure compressor 4. It comprises a casing 16 centered on the axis 2. Here, two compressor rectifiers are represented, namely a first rectifier 18a, as well as a second rectifier 18b offset from the first axially towards the 'downstream.

Each rectifier 18a, 18b comprises an annular ring of blades mounted on the casing 16, only one of the blades 20 of the first rectifier 18a being partially shown on the . These stator blades 20 are intended to be set simultaneously in incidence, as a function of precise aerodynamic parameters, using a blade control system specific to the invention.

The control system 22 firstly comprises a fixed part essentially consisting of a housing 24, fixedly mounted on the exterior surface of the casing 16. This housing 24 is used for the articulation of horns, as will be detailed below.

The control system 22 also includes pivots 26, each associated with a blade 20 to allow its rotation along an axis 27 for setting in incidence. The pivots 26 pass through the casing 16, and are each connected to a lever 28, itself controlled by a timing control ring. Thus, the first rectifier 18a is associated with a first control ring 30a centered on the axis 2 and connected to all of the levers 28 controlling the blades of the first rectifier, while the second rectifier 18b is associated with a second ring of control 30b also centered on axis 2 and connected to all of the levers 28 controlling the blades of the second rectifier.

The control system 22 also comprises a first output member 32a in the form of a connecting rod, controlling the rotation of the first ring 30a around the axis 2, while the second output member 32b in the form of a connecting rod controls the second ring 30b in rotation, also around axis 2.

The two connecting rods 32a, 32b are respectively controlled by two horns 34a, 34b articulated on the housing 24 of the system, as will now be described with reference to Figures 3 to 6.

Indeed, the control system 22 comprises a first horn 34a comprising a first branch 36a as well as a second branch 36b connected to each other to result in a general V shape. Opposite to the zone of junction between the two branches, the first branch 36a has a first distal end 38a, and the second branch 36b has a second distal end 38b. This first horn 34a is thus intended to control the setting of the blades of the first rectifier, via the first connecting rod 32a.

In a similar manner, the control system 22 comprises a second horn 34b comprising a third branch 36c as well as a fourth branch 36d connected to each other to also result in a general V shape. In contrast of the junction zone between the two branches, the third branch 36c has a third distal end 38c, and the fourth branch 36d has a fourth distal end 38d. This second horn 34b is thus intended to control the timing of the blades of the second rectifier, via the second connecting rod 32b.

In addition, the control system 22 includes a synchronization member 40 in the form of an arched arm, which connects the two horns so that they can be set in motion simultaneously.

In addition, the first horn 34a is equipped with another branch 42, preferably made in one piece with the other two. This other branch forms a member 42 for controlling the rotation of the first horn 34a. Its distal end 42a is mounted in an articulated manner at a point P on an output member 43 of an actuating device 44 of the system, preferably a cylinder whose body 45 is fixed for example on the casing 16 or the housing 24 .

The aforementioned elements 34a, 34b, 32a, 32b, 40, 44 of the control system 22 form a kinematic assembly whose parts are articulated to each other, along parallel or substantially parallel articulation axes.

More precisely, the control system 22 defines a first articulation point P1 between the first distal end 38a of the first horn 34a, and one end of the synchronization member 40. A second articulation point P2 is defined between the second distal end 38b of the first horn 34a, and one end of the first connecting rod 32a, namely that opposite the ring that it controls. A third articulation point P3 is defined between the third distal end 38c of the second horn 34b, and the opposite end of the synchronization member 40. A fourth articulation point P4 is defined between the fourth distal end 38d of the second horn 34b, and one end of the second connecting rod 32b.

In addition, a fifth point P5 of articulation of the first horn 34a is defined on the fixed housing 24, just as a sixth point P6 of articulation of the second horn 34b is also defined on this housing 24.

As mentioned previously, all of the aforementioned articulation points P, P1-P6 define parallel or substantially parallel articulation axes, preferably orthogonal to the planes of the horns.

The operation of the control system 22 is described below. To change the angle of incidence of the blades of the two rectifiers, the cylinder 44 is actuated so that its output member 43 moves in a linear manner. The translation of the output member leads to the rotation of the control member 42, which causes the rotation of the entire first horn 34a around the point P5.

The rotation of the first horn leads to two other movements in the kinematic assembly. The first lies in the setting in motion, via point P2, of the first output rod 32a, directly actuating the first control ring. The second movement consists of the movement of the synchronization member 40, via point P1. By moving, this member 40 in turn leads to the rotation of the entire second horn 34b around point P6, via the connection made by point P3. The rotation of the second horn leads to the setting in motion, via point P4, of the second output rod 32b, directly actuating the second control ring. Obviously, these movements are carried out simultaneously.

Thus, the control system 22 is configured so as to be able to rotate the horns 34a, 34b between a first extreme angular position shown in Figures 3 and 5, and a second extreme angular position opposite the first, and shown in the . The first extreme position of the horns is intended to place the rectifier vanes in a maximum closed position, in which the vanes have a high pitch angle relative to the direction of the air flow in the compressor, while the second position The extreme angular angle of these horns is intended to place the rectifier blades in a maximum opening position, in which the blades have the lowest pitch angle relative to the direction of the air flow in the compressor.

There , which is schematic, shows certain parts of the control system 22 when the horns 34a, 34b adopt an intermediate angular position between the two extreme positions shown in Figures 3, 5 and 6. It can be observed that during a movement of the horns 34a, 34b from the intermediate position towards the first extreme angular position of Figures 3 and 5, the first, third and sixth points P1, P3, P6 define a first obtuse angle A1 at point P3, this obtuse angle A1 seeing its value increase until reaching a first maximum value of obtuate angle A1max when the horns occupy their first extreme angular position of Figures 3 and 5. Thus, by maintaining such an obtuse angle in this first extreme angular position, no problems are encountered kinematic critical point, that is to say that no turning point is observed at P3 due to the non-alignment between the three points P1, P3, P6.

In a similar manner, it can also be observed that when the horns 34a, 34b are moved from the intermediate position of the , towards the second extreme angular position of the , the fifth, first and third points P5, P1, P3 define a second obtuse angle A2 at point P1, this obtuse angle A2 seeing its value increase until reaching a second maximum value of obtuse angle A2max when the horns occupy their second extreme angular position. Here too, by maintaining such an obtuse angle in this second extreme angular position, no kinematic critical point is encountered, that is to say no turning point is observed at P1 due to the non -alignment between the three points P5, P1, P3.

It is noted that the values A1max and A2max can be provided between 150 and 179°, and even more preferably be of the order of 155 to 175°.

Another particularity of the invention lies in the implementation of elastic return means, cooperating here with the first horn 34a, but which can alternatively be associated with other parts of the kinematic assembly. These elastic means are shown in Figures 7 to 10.

In the preferred embodiment which is represented in these figures, it is a first elastic return means 50a in the shape of a strip, as well as a second elastic return means 50b also in the form of a strip. Preferably, these two flexible elements 50a, 50b are grouped within the same and single elastic strip 50, for example made of metallic material.

The strip 50 is fixed to the housing 24, for example by rivets 54 or by similar fixing elements. Preferably, the fixing is carried out with the strip 50 located between the housing 24 and the exterior lateral flanks of the two branches 36a, 36b of the first horn 34a. The strip 50 in fact follows the outer lateral flanks of the tip of the rounded V defined by this horn, near point P5, then goes up along part of the outer lateral flank of each of the two branches 36a, 36b. This allows the single strip 50 to respectively form the first elastic return means 50a, as well as the second elastic return means 50b.

To optimize the desired contact between each of the two means 50a, 50b, and its associated branch 36a, 36b, a first zone deformed by folding is provided so as to define a first contact boss 52a for supporting the first branch 36a of the horn, as well as a second zone deformed by folding so as to define a second contact boss 52b for supporting the second branch 36b.

The control system 22 is then designed so that the first elastic return means 50a is biased by the first branch 36a from any intermediate position, during a stroke of the horns 34a, 34b towards the first extreme angular position of the . In other words, this stress is observed at least during the end of travel of the two horns towards this first extreme angular position, and is preserved in this same first extreme angular position. Such a situation is represented on the , showing the first boss 52a constrained by the first branch 36a, with the first elastic means 50a deformed. This deformation leads the elastic means 50a to generate restoring forces on the first branch 36a causing the first horn 34a to be stressed in the opposite direction, that is to say in the direction of its second extreme angular position. These restoring forces therefore make it possible to avoid reaching a critical reversal point at the end of the closing stroke, at the level of the point P3 and in relation to the first obtuse angle A1 which cannot thus deform until reaching a flat angle. Furthermore, when initiating a stroke in the opposite direction of opening, the restoring forces are exerted on the first branch 36a in a direction favoring the rotation of the first bellcrank 34a in the desired direction of rotation. Also, even in the presence of clearances between the parts, the risk is very low or zero of reaching a reversal point following a reversal of travel of the first horn occupying its first extreme angular position. It is noted that the restoring forces are transmitted directly to the first branch 36a, but due to the presence of the synchronization member, it is the two horns 34a, 34b which are biased towards their second extreme angular position, following a reversal of course from their first extreme position.

At the same time, the second boss 52b remains at a distance from its second associated branch 36b, and does not induce any return effort in the first horn.

Similarly, the control system 22 is designed so that the second elastic return means 50b is biased by the second branch 36b from any intermediate position, during a stroke of the horns 34a, 34b towards the second angular position. extreme of Figures 7 and 8. In other words, this stress is observed at least during the end of travel of the two horns towards this second extreme angular position, and is preserved in this same second extreme angular position. Such a situation is visible on the , showing the second boss 52b constrained by the second branch 36a, with the second elastic means 50b deformed. This deformation leads the elastic means 50b to generate restoring forces on the second branch 36b causing the first horn 34a to be stressed in the opposite direction, that is to say in the direction of its first extreme angular position. These restoring forces therefore make it possible to avoid reaching a critical reversal point at the end of the opening stroke, at the level of the point P1 and in relation to the second obtuse angle A2 which cannot thus be deformed until it reaches a flat angle. Furthermore, when initiating a stroke in the opposite direction of closing, the restoring forces are exerted on the second branch 36b in a direction favoring the rotation of the first horn 34a in the desired direction of rotation. Also, even in the presence of clearances between the parts, the risk is very low or zero of reaching a reversal point following a reversal of travel of the first horn occupying its second extreme angular position. It is noted that the return forces are transmitted directly to the second branch 36b, but due to the presence of the synchronization member 40, it is here also the two horns 34a, 34b which are requested in the direction of their first position extreme angular, following a reversal of course from their second extreme position.

At the same time, the first boss 52a remains at a distance from its first associated branch 36a, and does not induce any return effort in the first horn.

Of course, various modifications can be made by those skilled in the art to the invention which has just been described, solely by way of non-limiting examples and the scope of which is delimited by the appended claims.

Claims (10)

System (22) for controlling rectifier blades of a compressor for an aircraft turbomachine, the system comprising:
- a linear actuation device (44);
- a first horn (34a) comprising a first branch (36a) as well as a second branch (36b) connected to each other and respectively having a first distal end (38a) as well as a second distal end (38b ), the first horn being intended to control the setting of the blades of a first rectifier (18a) of the compressor;
- a second horn (34b) comprising a third branch (36c) as well as a fourth branch (36d) connected to each other and respectively having a third distal end (38c) as well as a fourth distal end (38d ), the second horn being intended to control the setting of the blades of a second rectifier (18b) of the compressor;
- a synchronization member (40) connecting the two horns (34a, 34b);
- a member (42) for controlling the rotation of the first horn, connecting the linear actuation device (44) to this first horn;
- a first and a second output member (32a, 32b);
and the system defining:
- a first articulation point (P1) between the first distal end (38a) of the first horn, and one end of the synchronization member (40);
- a second articulation point (P2) between the second distal end (38b) of the first horn, and one end of the first output member (32a);
- a third articulation point (P3) between the third distal end (38c) of the second horn, and another end of the synchronization member (40);
- a fourth articulation point (P4) between the fourth distal end (38d) of the second horn, and one end of the second output member (32b);
- a fifth articulation point (P5) of the first horn (34a) on a fixed part of the control system;
- a sixth articulation point (P6) of the second horn (34b) on the fixed part of the control system;
the control system being configured so as to be able to move the first and second horns (34a, 34b) between a first extreme angular position and a second opposite extreme angular position, respectively intended to place the rectifier vanes in a maximum closed position and a maximum opening position, or vice versa,
characterized in that when the horns (34a, 34b) move towards the first extreme angular position, the first, third and sixth articulation points (P1, P3, P6) define a first obtuse angle (A1) which increases until reaching a first maximum value of obtuse angle (A1max) when the horns occupy their first extreme angular position,
in that during a movement of the horns (34a, 34b) towards the second extreme angular position, the fifth, first and third articulation points (P5, P1, P3) define a second obtuse angle (A2) which increases until 'to reach a second maximum value of obtuse angle (A2max) when the horns occupy their second extreme angular position,
and in that the control system further comprises:
- a first elastic return means (50a) cooperating with a first associated element (34a) among any of the horns (34a, 34b) and the synchronization member (40), the control system being designed so that the first elastic return means (50a) is requested at least during an end of travel of the horns towards the first extreme angular position as well as in this same first extreme angular position, so as to generate on its first associated element (34a) forces leading the horns to be requested towards their second extreme angular position; and or
- a second elastic return means (50b) cooperating with a second associated element (34a) among any of the horns (34a, 34b) and the synchronization member (40), the control system being designed so that the second elastic return means (50b) is requested at least during an end of travel of the horns towards the second extreme angular position as well as in this same second extreme angular position, so as to generate on its second associated element (34a) forces leading the horns (34a, 34b) to be requested in the direction of their first extreme angular position. Control system according to claim 1, characterized in that the first elastic return means (50a) is a slat, and/or in that the second elastic return means (50b) is a slat. Control system according to claim 2, characterized in that the first and second elastic return means (50a, 50b) are formed by the same strip (50). Control system according to claim 2 or claim 3, characterized in that the strip forming the first elastic return means (50a) comprises a first deformed zone defining a boss (52a) for supporting said first associated element (34a) , and/or in that the strip forming the second elastic return means (50b) comprises a second deformed zone defining a boss (52b) for supporting said second associated element (34a). Control system according to any one of the preceding claims, characterized in that the fixed part of the control system comprises a housing (24) on which the two horns (34a, 34b) are articulated, the housing (24) being intended to be fixed on a casing (16) of the compressor. Control system according to the preceding claim, characterized in that the first and/or the second elastic return means (50a, 50b) are fixed to the housing (24), preferably by rivets. Control system according to any one of the preceding claims, characterized in that said first associated element and/or said second associated element are formed by the first horn (34a), the first elastic return means (50a) cooperating with the first branch (36a), and/or the second elastic return means (50b) cooperating with the second branch (36b). Control system according to any one of the preceding claims, characterized in that the first and second output members are respectively formed by a first connecting rod (32a) and a second connecting rod (32b), and in that it comprises a first ring (30a) for controlling the timing of the blades of the first rectifier (18a), controlled by the first connecting rod (32a), and/or in that it comprises a second ring (30b) for controlling the timing of the blades of the second rectifier (18b), controlled by the second connecting rod (32b). Compressor (4, 6) for an aircraft turbomachine comprising a system (22) for controlling rectifier blades according to any one of the preceding claims. Aircraft turbomachine (1) comprising at least one compressor (4, 6) according to the preceding claim.