ROTATIONAL INDEXING DEVICE FOR A BLOWER RECTIFIER MODULE HUB

Abstract

The invention relates to a fan rectifier module (6) for an aircraft turbomachine test bench comprising an annular hub (11), at least one blade (12), a shroud (16) and at least one fixing member (20) capable of ensuring fixing of the annular hub (11) on the shroud (16). An indexing device (21) in the angular position of the annular hub (11) relative to the shroud (16) comprises at least two indexing holes (22.1, 22.2) made in the shroud (16) angularly spaced apart from each other, and an indexing stud (25) inserted selectively into one of the indexing holes (22.1, 22.2) as a function of an angular position of the annular hub (11) to lock the annular hub (11) in a desired angular position before positioning the fixing member (20). Figure 6

Description

Title of the invention: DEVICE FOR ROTATIONALLY INDEXING A BLOWER RECTIFIER MODULE HUB

[0001] The present invention relates to a device for rotationally indexing a fan module hub. The invention finds a particularly advantageous application in the field of aeronautics, in particular with test machines for a turbomachine test bench.

[0002] The operating principle of a turbomachine fan is to compress the air entering the engine. Part of this air constitutes the primary flow delimited by a primary vein and another part of this air constitutes the secondary flow delimited by a secondary vein. The primary flow passes through a low-pressure compressor integral with the fan, through a high-pressure compressor, through the combustion chamber, through the high-pressure turbine and, finally, through the low-pressure turbine before being ejected.

[0003] [Fig.l] shows a test machine 1 for a test bench comprising from upstream to downstream, an upstream flow vein 2, a fan 3 having a rotor module 4 with moving blades and a rectifier module 5 with fixed blades called OGV (for "Outlet Guide Vane" in English), as well as a downstream flow vein 6. An inlet cone 7 is mounted at the upstream end of the rotor module 4 to deflect part of the air flow which enters the interior of the turbojet towards the blades of the fan 2.

[0004] The rotor module 4 comprises a plurality of blades mounted on a cylindrical hub called a "fan disc" driven in rotation by a pressure turbine. The rotor module 4 provides acceleration to the air particles, by deflecting them relative to the X axis of the engine. The rectifier module 5 slows down the air particles and transforms part of their speed into pressure. The rectifier module 5 brings the flow of air, accelerated by the rotor module 4, back into the X axis of the engine.

[0005] As can be seen in [Fig.2], the rectifier module 5 comprises an annular hub 11 and a plurality of blades 12. The annular hub 11 comprises a plurality of housings 13 for receiving a blade root 15. The rectifier module 5 also comprises a ferrule 16 comprising a centering surface 17 on which the annular hub 11 bears. Fastening members 20 ensure that the annular hub 11 is fastened to the ferrule 16, which can be fixed to a thrust balance 18 making it possible to measure the axial forces, the radial forces and the moments experienced by the rectifier module 5 during a test of the turbomachine. The ferrule 16 is arranged under a closing cover 14 reconstituting a portion of a vein of the turbomachine

[0006] As illustrated in [Fig. 3], a test bench further comprises a pylon 9 corresponding to an attachment zone between the turbomachine and a wing of an aircraft. In addition, intrusive meters 8 are immersed in the air flow to be measured, as shown in [Fig. 4]. There are different types which are suitable for measuring one or more parameters of the flow and which are generally installed in one or more specific zone(s) of the turbomachine where the aerodynamic flow to be measured circulates, such as zones of an aerodynamic vein.

[0007] During aerodynamic tests, it is important to be able to axially misalign the fixed blades of the rectifier module 5 with respect to the pylon 9 or the intrusive meters 8 in order to analyze the influence of the wake of the air flow behind the blades of the rectifier module 5 on the external elements downstream of the vein. In particular, there is a need to be able to carry out a modification of the angular position of the hub without major disassembly of the machine and without changing parts.

[0008] The invention aims to effectively meet this need by proposing a fan rectifier module for an aircraft turbomachine test bench comprising: - an annular hub having an axis, said annular hub comprising at least one blade root housing, - at least one blade provided with a blade root arranged in the blade root housing, - a ferrule comprising a centering surface on which the annular hub rests, - at least one fixing member capable of ensuring fixing of the annular hub on the ferrule, and - a device for indexing the angular position of the annular hub relative to the ferrule comprising: - at least two indexing holes made in the ferrule angularly spaced apart, and - an indexing stud selectively inserted into one of the indexing holes depending on an angular position of the annular hub so as to cooperate with a corresponding hole made in the annular hub to lock the annular hub in a desired angular position before the fixing member is put in place.

[0009] The invention thus makes it possible to easily modify an angular position of the annular hub of the rectifier module in order to test different relative positions of the blades with respect to the pylon or with respect to the intrusive meters without having to dismantle the ferrule and without modifying the centering of the annular hub on the ferrule.

[0010] According to one embodiment of the invention, the indexing stud is held in position by means of a locking screw.

[0011] According to one embodiment of the invention, the locking screw is intended to be inserted inside a locking hole arranged close to a corresponding indexing hole.

[0012] According to one embodiment of the invention, at least two fixing holes made in the ferrule are associated with the fixing member, so that the fixing member can be selectively inserted into one of the fixing holes depending on the angular position of the annular hub.

[0013] According to one embodiment of the invention, said indexing device comprises a device for locating an angular position of the annular hub relative to the ferrule.

[0014] According to one embodiment of the invention, the device for locating the angular position comprises at least one reference locating element arranged on the ferrule and a movable locating element produced on the annular hub, such that an angular rotation of the annular hub moves the movable locating element relative to the reference locating element so as to be able to locate an angular position of the annular hub relative to the ferrule.

[0015] According to one embodiment of the invention, the ferrule comprises a peripheral groove intended to receive a tool for holding the annular hub.

[0016] According to one embodiment of the invention, the shell is arranged under a closing cover reconstituting a portion of a turbomachine vein.

[0017] The invention also relates to a test bench for a turbomachine comprising a rectifier module as previously defined and at least one intrusive meter, the indexing device making it possible to block the annular hub in a first angular position in which the intrusive meter is axially aligned with a blade of the rectifier module or is arranged in place of a blade and a second position in which the intrusive meter is located angularly between two blades of the rectifier module.

[0018] The invention further relates to a test bench for a turbomachine comprising a rectifier module as previously defined and a pylon corresponding to an attachment zone between the turbomachine and an aircraft wing, the indexing device making it possible to block the annular hub in a first angular position in which the pylon is axially aligned with a blade of the rectifier module or is arranged in place of a blade of the rectifier module and a second position in which the pylon is located angularly between two blades of the rectifier module.

[0019] The present invention will be better understood and other characteristics and advantages will become apparent upon reading the detailed description which follows, comprising embodiments given for illustrative purposes with reference to the appended figures, presented as non-limiting examples, which may serve to complete the understanding of the present invention and the description of its embodiment and, where appropriate, contribute to its definition, in which:

[0020] [Fig-1] [Fig.l], already described, is a longitudinal sectional view of a machine of test for a test bench illustrating the low thickness between the primary vein and the vein secondary at the level of a rectifier module;

[0021] [Fig.2] [Fig.2] is a sectional view illustrating a standard attachment of a module fan rectifier on a 16 shell of a test turbomachine;

[0022] [Fig.3] [Fig.3] is a front view illustrating an angular positioning of a fan rectifier module relative to a pylon 9 representing a turbomachine attachment point;

[0023] [Fig.4] [Fig.4] is a front view illustrating a positioning of a module re blower trainer versus intrusive meters;

[0024] [Fig.5] [Fig.5] is a perspective view of a blower rectifier module for an aircraft turbomachine test bench according to the invention;

[0025] [Fig.6] [Fig.6] is a detailed sectional view showing an indexing device in rotation of the hub of the fan rectifier module according to the invention;

[0026] [Fig.7][Fig.8] Figures 7 and 8 are detailed perspective views illustrating two angular positions that the hub of the rectifier module can take thanks to the indexing device according to the invention.

[0027] It should be noted that the structural and / or functional elements common to the different embodiments may have the same references. Thus, unless otherwise stated, such elements have identical structural, dimensional and material properties.

[0028] [Fig. 5] shows a fan rectifier module 5 for an aircraft turbomachine test bench comprising an annular hub 11 having an axis XI and a plurality of blades 12.

[0029] The annular hub 11 comprises a plurality of housings 13 for receiving a blade root 15. The annular hub 11 may be a single-piece annular hub 11, i.e. it is made in a single part. Alternatively, the annular hub 11 is made in two coaxial annular parts assembled together. The blades 12 extend radially outwards from the annular hub 11 along their Y axis.

[0030] The blades 12 are distributed angularly in a regular manner along a circumference of the annular hub 11. Each blade 12 is provided with a blade root 15 arranged inside a corresponding blade root housing 13.

[0031] As shown in Figures 6, 7 and 8, a ferrule 16 of annular shape comprising a centering surface 17 on which the annular hub 11 bears. The centering surface 17 has an annular shape of axial orientation relative to the axis XI of the hub.

[0032] At least one fixing member 20 is capable of ensuring fixing of the annular hub 11 on the ferrule 16. The fixing member 20 preferably takes the form of a screw but can alternatively take the form of a rivet, a stud or any other fixing member suitable for the application.

[0033] An indexing device 21 for the angular position of the annular hub 11 relative to the ferrule 16 comprises at least two indexing holes 22.1, 22.2 made in the ferrule 16 angularly spaced apart from each other, and an indexing stud 25 inserted selectively into one of the indexing holes 22.1, 22.2 as a function of an angular position of the annular hub 11 so as to cooperate with a corresponding hole 26 made in the annular hub 11 to lock the annular hub 11 in a desired angular position before the fixing member 20 is put in place. Of course, depending on the number of desired angular positions of the annular hub 11 relative to the ferrule, more than two indexing holes 22.1, 22.2 may be provided in the ferrule 16.

[0034] The indexing stud 25 is held in position by means of a locking screw 27. For this purpose, the indexing stud 25 is extended by a support plate 28 arranged against an end face of the ferrule 16. The support plate 28 has a hole for the passage of the locking screw 27 screwed onto the ferrule 16. The locking screw 27 is intended to be inserted inside a locking hole 29.1, 29.2 of the ferrule 16 arranged close to a corresponding indexing hole 22.1, 22.2, as shown in FIGS. 7 and 8.

[0035] At least two fixing holes 30.1, 30.2 made in the ferrule 16 are associated with the fixing member 20. The fixing holes 30.1, 30.2 are angularly spaced apart from each other. The fixing member 20 can be selectively inserted into one of the fixing holes 30.1, 30.2 depending on the angular position of the annular hub 11. A given fixing zone of the ferrule 16 comprises at least two indexing holes 22.1, 22.2 associated with the same indexing stud 25, two locking holes 29.1, 29.2 and at least two fixing holes 30.1, 30.2 associated with the same fixing member 20. The ferrule 16 preferably comprises several fixing zones. The fixing zones 16 are distributed along a circumference of the ferrule 16.

[0036] Preferably, as illustrated in Figures 7 and 8, the indexing device 21 comprises a device 31 for locating an angular position of the annular hub 11 relative to the ferrule 16. The device 31 for locating the angular position comprises at least one reference locating element 32 arranged on the ferrule 16 and a movable locating element 33 produced on the annular hub 11, so that an angular rotation of the annular hub 11 moves the movable locating element 33 relative to the reference locating element 32 so as to be able to locate an angular position of the annular hub 11 relative to the ferrule 16.

[0037] The ferrule 16 is arranged under a closing cover 14 reconstituting a portion of the vein of the turbomachine (cf. [Fig.2]).

[0038] The operation of the indexing device 21 in the angular position of the annular hub 11 relative to the ferrule 16 is described below. Initially, as shown in [Fig. 7], the indexing stud 25 is inserted into the first hole indexing 22.1 with the locking screw 27 screwed into the locking hole 29.1 and the fixing member 25 cooperates with the first fixing hole 30.1.

[0039] Firstly, the operator removes the fixing member 20 and the indexing stud 25 after having unscrewed the locking screw 27. It is then possible to move the annular hub 11 in rotation relative to the ferrule 16. During its rotational movement, the annular hub 11 is guided by the centering surface 17 cooperating with an internal periphery of an end portion of the annular hub 11. As illustrated in [Fig. 8], once the annular hub 11 is in the desired angular position identified by the locating device 31, the indexing stud 25 is inserted into the second indexing hole 22.2 and the locking screw 27 is screwed into the locking hole 29.2 to lock the indexing stud 25 in position. The fixing member 25 is then inserted into the second fixing hole 30.2 so as to be screwed onto the annular hub 11.The various operations can be carried out manually or automatically by a robot.

[0040] The ferrule 16 preferably comprises a peripheral groove 34 intended to receive a tool for holding the annular hub 11 during the phase of changing the angular setting of the annular hub 11.

[0041] The indexing device 21 thus makes it possible to block the annular hub 11 in a first angular position in which the intrusive meter 8 is axially aligned with a blade of the rectifier module 5 or is arranged in place of a blade and a second position in which the intrusive meter 8 is located angularly between two blades of the rectifier module 5.

[0042] The indexing device 21 also makes it possible to lock the annular hub 11 in a first angular position in which the pylon 9 is axially aligned or is arranged in place of a blade of the rectifier module 5 and a second position in which the pylon 9 is located angularly between two blades 12 of the rectifier module 5.

[0043] Of course, the various features, variants and / or embodiments of the present invention may be combined with each other in various combinations to the extent that they are not incompatible or mutually exclusive.

[0044] Furthermore, the invention is not limited to the embodiments described above and provided solely by way of example. It encompasses various modifications, alternative forms and other variants that may be envisaged by those skilled in the art within the scope of the present invention and in particular all combinations of the different operating modes described above, which may be taken separately or in association.

Claims

Claims

1. Fan rectifier module (6) for an aircraft turbomachine test bench comprising: - an annular hub (11) having an axis (XI), said annular hub (11) comprising at least one blade root housing (13), - at least one blade (12) provided with a blade root (15) arranged in the blade root housing (13), - a ferrule (16) comprising a centering surface (17) on which the annular hub (11) bears, - at least one fixing member (20) capable of ensuring fixing of the annular hub (11) on the ferrule (16), characterized in that an indexing device (21) in the angular position of the annular hub (11) relative to the ferrule (16) comprises: - at least two indexing holes (22.1, 22.2) made in the ferrule (16) angularly spaced apart from each other, and - an indexing stud (25) selectively inserted into one of the indexing holes (22.1, 22.2) depending on an angular position of the annular hub (11) so as to cooperate with a corresponding hole (26) made in the annular hub (11) to lock the annular hub (11) in a desired angular position before the fixing member (20) is put in place.

2. Rectifier module according to claim 1, characterized in that the indexing stud (25) is held in position by means of a locking screw (27).

3. Rectifier module according to claim 2, characterized in that the locking screw (27) is intended to be inserted inside a locking hole (29.1, 29.2) arranged near a corresponding indexing hole (22.1, 22.2).

4. Rectifier module according to any one of claims 1 to 3, characterized in that at least two fixing holes (30.1, 30.2) made in the ferrule (16) are associated with the fixing member (20), so that the fixing member (20) can be selectively inserted into one of the fixing holes (30.1, 30.2) depending on the angular position of the annular hub (11).

5. Rectifier module according to any one of claims 1 to 4, characterized in that the indexing device (21) comprises a device (31) for locating an angular position of the annular hub (11) by report to the ferrule (16).

6. Rectifier module according to claim 5, characterized in that the angular position locating device (31) comprises at least one reference locating element (32) arranged on the ferrule (16) and a movable locating element (33) produced on the annular hub (11), so that an angular rotation of the annular hub (11) moves the movable locating element (33) relative to the reference locating element (32) so as to be able to locate an angular position of the annular hub (11) relative to the ferrule (16).

7. Rectifier module according to any one of claims 1 to 6, characterized in that the ferrule (16) comprises a peripheral groove (34) intended to receive a tool for holding the annular hub (11).

8. Rectifier module according to any one of claims 1 to 7, characterized in that the ferrule (16) is arranged under a closing cover (14) reconstituting a portion of a turbomachine vein.

9. Test bench for a turbomachine comprising a rectifier module (5) defined according to any one of claims 1 to 8 and at least one intrusive meter (8), the indexing device (21) making it possible to block the annular hub (11) in a first angular position in which the intrusive meter (8) is axially aligned with a blade (12) of the rectifier module (5) or is arranged in place of a blade (12) and a second position in which the intrusive meter (8) is located angularly between two blades (12) of the rectifier module (5).

10. Test bench for a turbomachine comprising a rectifier module (5) defined according to any one of claims 1 to 8 and a pylon (9) corresponding to an attachment zone between the turbomachine and an aircraft wing, the indexing device (21) making it possible to block the annular hub (11) in a first angular position in which the pylon (9) is axially aligned with a blade (12) of the rectifier module (5) or is arranged in place of a blade of the rectifier module (5) and a second position in which the pylon (9) is located angularly between two blades (12) of the rectifier module (5).

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