SYSTEM FOR ADJUSTING THE ROTATION OF A BLADE OF A FAN MODULE BY MEANS OF A CONNECTING ROD

Abstract

The invention relates to an aircraft turbomachine module, in particular for a test bench, comprising: - an annular hub (10), - at least one blade (11), and - a system (17) for adjusting the rotation of the blade (11) comprising: - an adjustment rod (19) having a first end and a second end, the first end being connected to the blade root (13) via a pivot connection (20), - said adjustment rod (19) being inserted inside a through opening (23) made in the annular hub (10) opening onto an external face of the annular hub (10), and - an adjustment nut (26) cooperating with the second end of the adjustment rod (19), so that tightening or loosening the adjustment nut (26) makes it possible to modify an angular position of the blade (11). Figure 3a

Description

Title of the invention: SYSTEM FOR ADJUSTING THE ROTATION OF A BLADE OF A FAN MODULE BY MEANS OF A CONNECTING ROD

[0001] The present invention relates to a system for adjusting the rotation of a blade of a fan module by a connecting rod. The invention finds a particularly advantageous, but not exclusive, application with a fan rectifier module.

[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] The present invention relates in particular to a test machine for a test bench, for example a fan of an aerodynamic demonstrator which has only a single air flow and which does not have a low pressure compressor, nor a high pressure compressor or a combustion chamber. Such a test machine aims to test different parts of the turbomachine and to optimize the operating settings of the turbomachine.

[0004] [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.

[0005] 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 supplied with air by the test bench. 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.

[0006] During a test campaign, it is important to be able to ensure rapid assembly and disassembly of a blade as well as modification of its angular setting in order to find an optimum setting of the turbomachine. There is therefore a need to be able to carry out these operations as quickly as possible in order to limit the downtime of the test machine during a test campaign. These operations must can also be carried out without having to dismantle the test machine which is fully instrumented.

[0007] The invention aims to effectively meet the aforementioned needs by proposing an aircraft turbomachine module, in particular for a test bench, comprising: - an annular hub comprising at least one blade root housing, - at least one blade provided with a blade root intended to be arranged inside the blade root housing, - said module comprising a blade rotation adjustment system comprising: - an adjustment rod having a first end and a second end, the first end being connected to the blade root via a pivot connection, - said adjusting rod being inserted inside a through opening made in the annular hub opening onto an external face of the annular hub, and - an adjusting nut cooperating with the second end of the adjusting rod, so that tightening or loosening the adjusting nut makes it possible to modify an angular position of the blade.

[0008] The invention thus makes it possible to easily modify the angular setting of the blade between two tests without having to dismantle the test machine. The invention makes it possible to limit downtime during the test as much as possible. The invention allows the adjustment of the setting of the blade while remaining in a dimensionally constrained environment. The invention also respects the aerodynamic profile of the vein regardless of the position of the blade, the vibrations, or its internal displacements due to pumping phenomena or transient flows during a change of setting. In the event of breakage of a blade, the invention also makes it possible to facilitate in situ disassembly. The invention also has the advantage of being a simple solution to implement containing a minimum of parts.

[0009] According to one embodiment of the invention, the adjustment rod has a longitudinal extension direction perpendicular to an axis of the blade.

[0010] According to one embodiment of the invention, said module comprises a locking device capable of locking the adjustment nut after having selected a desired angular position of the blade.

[0011] According to one embodiment of the invention, said module comprises a ball joint arranged between the adjustment rod and the annular hub.

[0012] According to one embodiment of the invention, said module comprises a convex or concave washer device arranged behind the adjustment nut to compensate for movements of the adjustment rod.

[0013] According to one embodiment of the invention, the adjustment rod being a first adjustment rod, said module comprises a second adjustment rod parallel to the first adjustment rod, said second adjustment rod being inserted inside a second through opening made in the annular hub, said second adjustment rod having a first end connected to the blade root via a second pivot connection and a second end cooperating with a second adjustment nut.

[0014] According to one embodiment of the invention, the assembly formed by one end of the adjustment rod and the adjustment nut is arranged inside a housing located under a vein of the module.

[0015] According to one embodiment of the invention, said module comprises an access cover reconstituting the vein allowing access to the adjustment rod to modify an angular position of the blade.

[0016] According to one embodiment of the invention, the annular hub is made in two parts.

[0017] According to one embodiment of the invention, the module is a rectifier module.

[0018] According to one embodiment of the invention, the module is a rotor 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 with which the invention is implemented;

[0021] [Fig.2] [Fig.2] is a perspective view of a rectifier module for a bench aircraft turbomachine testing according to the present invention;

[0022] [Fig.3a] [Fig.3b] Figures 3a and 3b are top views of a system according to the invention of adjusting the rotation of a blade oriented according to two different angular positions;

[0023] [Fig.4] [Fig.4] is a detailed perspective view of a vane foot and a system for adjusting the rotation of a blade according to the invention;

[0024] [Fig.5] [Fig.5] is a perspective view illustrating the use of a device for locking a nut of the rotation adjustment system of a blade according to the invention;

[0025] [Fig.6] [Fig.6] is a top view of a first variant embodiment of a rotation adjustment system for a blade according to the invention;

[0026] [Fig.7] [Fig.7] is a top view of a second variant embodiment of a rotation adjustment system for a blade according to the invention.

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

[0028] [Fig.2] shows a rectifier module 5 for an aircraft turbomachine test bench comprising an annular hub 10 having an axis XI and a plurality of blades 11.

[0029] The annular hub 10 comprises a plurality of blade root housings 12. Advantageously, the annular hub 10 can be formed by two coaxial annular parts 10.1, 10.2 fixed to each other and defining between them the housings 12 of blade roots 11, as shown in particular in FIGS. 3a, 3b and 4. Thus, each part 10.1, 10.2 delimits a portion of a housing 12. As a variant, the annular hub 10 is a single-piece hub.

[0030] The blades 11 extend radially along their axis Y towards the outside of the hub 10. The blades 11 are distributed angularly in a regular manner along a circumference of the hub 10. Each blade 11 is provided with a blade root 13 of generally cylindrical shape intended to be arranged inside a corresponding blade root housing 12. A large diameter portion of the blade root 13 can come to bear against a shoulder 15 of the housing 12 intended to ensure radial retention of the blade root 13 relative to the axis XI, as shown in [Fig.4].

[0031] As illustrated in Figures 3a, 3b and 4, a rotation adjustment system 17 of the blade 11 makes it possible to modify an angular position of the blade 11 between two tests. The adjustment system 17 comprises an adjustment connecting rod 19 having a first end and a second end which is threaded. The first end of the connecting rod is connected to the blade root 13 via a pivot connection 20 having an axis X2 parallel to the axis Y of the blade. As shown in [Fig.4], the pivot connection 20 may be arranged inside a cavity made in the blade root 13.

[0032] The adjustment rod 19 is inserted inside a through opening 23 made in the annular hub 10 opening onto an external face of the annular hub 10.

[0033] An adjustment nut 26 cooperates with the second threaded end of the adjustment rod 19. The nut 26 is pressed against the external face of the hub 10. The adjustment rod 19 has a longitudinal extension direction perpendicular to an axis Y of the blade 11.

[0034] Thus, as can be seen in Figures 3a and 3b, tightening or loosening the adjustment nut 26 makes it possible to modify an angular position of the blade 11. The adjustment of the angular position of the blade 11 by tightening or loosening the adjustment nut 26 can be carried out by a human operator or automatically by a robot. The invention thus makes it possible to quickly modify the setting of the blades 11 between two tests. Furthermore, in the event of breakage of a blade 11, disassembly can be carried out in situ, which constitutes a significant time saving.

[0035] In the embodiment of [Fig. 5], a locking device 27 is capable of locking the adjustment nut 26 after having selected an angular position of the blade 11 desired. For this purpose, the locking device 27 comprises two legs 28 and a central portion 29 cooperating with the adjustment nut 26 to hold it in position. The central portion 29 may come to bear against the adjustment nut 26 or comprise a window cooperating with an external periphery of the adjustment nut 26. This makes it possible to avoid a modification of the angular adjustment during the test.

[0036] In the embodiment of [Fig. 6], a ball joint 32 is arranged between the adjustment rod 19 and the annular hub 10. The ball joint 32 is arranged inside the through opening 23. Such a configuration makes it possible to avoid blocking of the mechanism due to the movement of the adjustment rod 19 along an arc of a circle on the side of the pivot connection 20 of the blade 11 and along a straight line on the side of the adjustment nut 26.

[0037] A device 33 with a convex or concave washer can be arranged behind the adjustment nut 26 to compensate for movements of the adjustment rod 19.

[0038] In the embodiment of [Fig.7], the adjustment system 17 comprises a second adjustment rod 19' parallel to the first adjustment rod 19. The second adjustment rod 19' is inserted inside a second through opening 23' made in the annular hub 10. The second adjustment rod 19' has a first end connected to the blade root 13 via a second pivot connection 20' and a second end cooperating with a second adjustment nut 26'. Thus, tightening the adjustment nuts 19, 19' ensures that the blade 11 is locked in rotation.

[0039] Advantageously, the assembly formed by one end of the adjustment rod 19 and the adjustment nut 26 is arranged inside a housing 35 located under a vein of the fan module.

[0040] An access cover 36 reconstituting the vein allows access to the adjustment rod 19 to modify an angular position of the blade 11. Advantageously, an access cover 36 is located in an extension of the vein. This access cover 36 makes it possible to avoid aerodynamic disturbances of the vein.

[0041] The invention respects the aerodynamic profile of the vein whatever the position of the blade, the vibrations, or its internal movements due to pumping phenomena or transient flows during a change of timing.

[0042] The invention makes it possible to limit downtimes during testing as much as possible. The invention allows the adjustment of the blade timing while remaining in a dimensionally constrained environment. The invention guarantees mechanical strength of the parts and the assembly at all operating speeds of the turbomachine.

[0043] The invention also has the advantage of being a simple solution to implement containing a minimum of parts.

[0044] Alternatively, the fan module 5 may be a rotor module.

[0045] 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.

[0046] 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. Aircraft turbomachine module (5), in particular for a test bench, comprising: - an annular hub (10) comprising at least one blade root housing (12), - at least one blade (11) provided with a blade root (13) intended to be arranged inside the blade root housing (12), characterized in that said module (5) comprises a system (17) for adjusting the rotation of the blade (11) comprising: - an adjustment rod (19) having a first end and a second end, the first end being connected to the blade root (13) via a pivot connection (20), - said adjustment rod (19) being inserted inside a through opening (23) made in the annular hub (10) opening onto an external face of the annular hub (10), and - an adjustment nut (26) cooperating with the second end of the adjustment rod (19) setting (19),so that tightening or loosening the adjusting nut (26) makes it possible to modify an angular position of the blade (11).,

2. Module according to claim 1, characterized in that the adjustment rod (19) has a longitudinal extension direction perpendicular to an axis (Y) of the blade (11).

3. Module according to claim 1 or 2, characterized in that it comprises a locking device (27) capable of locking the adjustment nut (26) after having selected a desired angular position of the blade (11).

4. Module according to any one of claims 1 to 3, characterized in that it comprises a ball joint (32) arranged between the adjustment rod (19) and the annular hub (10).

5. Module according to any one of claims 1 to 4, characterized in that it comprises a device (33) with a convex or concave washer arranged behind the adjustment nut (26) to compensate for movements of the adjustment rod (19).

6. Module according to any one of claims 1 to 5, characterized in that the adjustment rod (19) being a first adjustment rod (19), said module comprises a second adjustment rod (19') parallel to the first adjustment rod (19), said second adjustment rod (19') being inserted inside a second through opening (23') made in the annular hub (10), said second adjustment rod (19') having a first end connected to the blade root (13) via a second pivot connection (20') and a second end cooperating with a second adjustment nut (26').

7. Module according to any one of claims 1 to 6, characterized in that the assembly formed by one end of the adjustment rod (19) and the adjustment nut (26) is arranged inside a housing (35) located under a vein of the module.

8. Module according to claim 7, characterized in that it comprises an access cover (36) reconstituting the vein allowing access to the adjustment rod (19) to modify an angular position of the blade (11).

9. Module according to any one of claims 1 to 8, characterized in that the annular hub (10) is made in two parts.

10. Module according to any one of claims 1 to 9, characterized in that the module is a rectifier module (5).

11. Module according to any one of claims 1 to 9, characterized in that the module is a rotor module.

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