SYSTEM FOR ADJUSTING THE ROTATION OF A BLADE OF A FAN MODULE BY MEANS OF SUPPORT SCREWS

Abstract

The invention relates to an aircraft turbomachine module, in particular for a test bench, comprising a system (17) for adjusting the rotation of the blade (11) comprising: - a first adjusting screw (18) inserted inside a first through-threaded hole (19) made in the annular hub (10), said first adjusting screw (18) having an end intended to bear against a first contact face (20) arranged on the blade root (12), - a second adjusting screw (25) inserted inside a second through-threaded hole (26) made in the annular hub (10), said second adjusting screw (26) having an end intended to bear against a second contact face (27) arranged on the blade root (12), so that tightening the first adjusting screw (18) and loosening the second adjusting screw (25), or vice versa, makes it possible to modify a position angular angle 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 SUPPORT SCREWS

[0001] The present invention relates to a system for adjusting the rotation of a blade of a fan module by means of support screws. 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, and - a blade rotation adjustment system comprising: - a first adjusting screw inserted inside a first through-tapped hole made in the annular hub, said first adjusting screw having an end intended to come into contact with a first contact face arranged on the blade root, - a second adjusting screw inserted inside a second through-tapped hole made in the annular hub, said second adjusting screw having one end intended to bear against a second contact face arranged on the blade root, so that tightening the first adjusting screw and loosening the second adjusting screw, or vice versa, allows an angular position of the blade to be modified.

[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 end of the first adjustment screw intended to come into contact with the first contact face has the shape of a spherical tip.

[0010] According to one embodiment of the invention, the end of the second adjustment screw intended to come into contact with the second contact face has the shape of a spherical tip.

[0011] According to one embodiment of the invention, the first adjustment screw and the second adjustment screw are located in the same plane perpendicular to an axis of the blade.

[0012] According to one embodiment of the invention, the first contact face and the second contact face extend in a plane parallel to an axis of the blade.

[0013] According to one embodiment of the invention, the first contact face and the second contact face form an angle of 180 degrees relative to each other.

[0014] According to one embodiment of the invention, the assembly formed by one end of the first adjustment screw and one end of the second adjustment screw protruding respectively from the first through-tapped hole and the second through-tapped hole, 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 first adjustment screw and to the second adjustment screw 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 rotor module.

[0018] According to one embodiment of the invention, the module is a 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 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] 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.

[0025] [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.

[0026] The annular hub 10 comprises a plurality of blade root housings 12. In this case, the annular hub 10 may be formed by two coaxial annular elements 10.1, 10.2 fixed to each other and defining between them the housings 12 of blade roots 11, as can be seen in FIGS. 3a, 3b and 4. Each housing 12 of blade root is defined by a portion of element 10.1 and by a portion of element 10.2. Alternatively, the annular hub 10 is a single-piece hub.

[0027] 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].

[0028] A rotation adjustment system 17 of the blade 11 makes it possible to modify and lock a desired angular position of the blade 11 for a test.

[0029] As illustrated in Figures 3a and 3b, the rotation adjustment system 17 of the blade 11 comprises a first adjustment screw 18 inserted inside a first threaded through hole 19 made in the annular hub 10. The first threaded through hole 19 opens on the one hand onto an external face of the hub 10 and on the other hand inside the blade root housing 12.

[0030] The first adjustment screw 18 has an end intended to bear against a first contact face 20 arranged on the blade root 12. The end of the first adjustment screw 18 intended to bear against the first contact face 20 preferably has a spherical tip shape. This guarantees a punctual support between the end of the first adjustment screw 18 and the first contact face 20.

[0031] The first adjustment screw 18 comprises a first screw head 21 comprising an imprint intended to cooperate with a tool of corresponding shape, such as a flat-head screwdriver, cross-head screwdriver or any other shape suitable for the application.

[0032] A second adjusting screw 25 is inserted inside a second through-threaded hole 26 made in the annular hub 10. The second through-threaded hole 26 opens on the one hand onto an external face of the hub 10 and on the other hand inside the blade root housing 12.

[0033] The second adjustment screw 26 has an end intended to come into contact with a second contact face 27 arranged on the blade root 12. The end of the second adjustment screw 25 intended to come into contact with the second contact face 27 preferably has the shape of a spherical tip.

[0034] The second adjustment screw 25 comprises a second screw head 28 comprising an imprint intended to cooperate with a tool of corresponding shape, such as a flat-head screwdriver, cross-head screwdriver or any other shape suitable for the application.

[0035] The first adjustment screw 18 and the second adjustment screw 25 are located in the same plane perpendicular to the Y axis of the blade 11.

[0036] Preferably, the first contact face 20 and the second contact face 27 extend in a plane parallel to an axis Y of the blade 11. The first contact face 20 and the second contact face 27 form an angle of 180 degrees with respect to each other. The first contact face 20 and the second contact face 27 are produced along two different radii of the annular hub 10. The first contact face 20 and the second contact face 27 are produced in a volume delimited by the external periphery of the annular hub 10. In this case, the contact faces 20, 27 are produced in a large diameter portion of the blade root 12. The contact faces 20, 27 extend in an axial direction and in a radial direction with respect to the axis Y of the blade 11.

[0037] The operation of the rotation adjustment system 17 according to the invention is described below.

[0038] As illustrated by [Fig.3a] and 3b, in order to modify the angular position of the blade 11 in a first direction of rotation, the first adjustment screw 18 is tightened and the second adjustment screw 25 is loosened. Conversely, in order to modify the angular position of the blade 11 in a second direction of rotation, the first adjustment screw 18 is loosened and the second adjustment screw 25 is tightened. The blade 11 is kept in rotation by the two adjustment screws 18, 25 bearing against the contact faces 20, 27 diametrically opposite one another.

[0039] It is then possible to carry out the tests of the blower according to this configuration of the stator module.

[0040] The operations of handling the blade 11 and tightening and loosening the adjustment screws 18, 25 can be carried out by a human operator or automatically by a robot.

[0041] The invention thus makes it possible to quickly modify the setting of the blades 11 between two tests. The invention makes it possible to limit downtime during the test as much as possible. The invention allows the adjustment of the blade setting while remaining in a dimensionally constrained environment. Furthermore, in the event of breakage of a blade 11, disassembly can be carried out in situ, which constitutes a significant time saving.

[0042] The assembly formed by one end of the first adjustment screw 18 and one end of the second adjustment screw 25 projecting respectively from the first through-tapped hole 19 and the second through-tapped hole 26 is arranged inside a housing 30 located under a vein of the module, as shown in [Fig.4].

[0043] An access cover 31 reconstituting the vein allows access to the adjustment screws 18, 25 to modify an angular position of the blade 11.

[0044] The invention thus respects the aerodynamic profile of the vein whatever the position of the blade, the vibrations, or its internal movements due to phenomena pumping or transient flows during a timing change.

[0045] The invention further guarantees mechanical strength of the parts and the assembly at all operating speeds of the turbomachine.

[0046] The invention also has the advantage of being a simple solution to implement containing a minimum of parts.

[0047] Alternatively, the fan module 5 may be a rotor module.

[0048] 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.

[0049] 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 framework 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: - a first adjusting screw (18) inserted inside a first through-threaded hole (19) made in the annular hub (10), said first adjusting screw (18) having one end intended to bear against a first contact face (20) arranged on the blade root (12), - a second adjusting screw (25) inserted inside a second through-threaded hole (26) made in the annular hub (10),said second adjustment screw (26) comprising an end intended to come into contact with a second contact face (27) arranged on the blade root (12), so that tightening the first adjustment screw (18) and loosening the second adjustment screw (25), or vice versa, makes it possible to modify an angular position of the blade (11).,

2. Module according to claim 1, characterized in that the end of the first adjustment screw (18) intended to come into contact with the first contact face (20) has the shape of a spherical tip.

3. Module according to claim 1 or 2, characterized in that the end of the second adjustment screw (25) intended to come into contact with the second contact face (27) has the shape of a spherical tip.

4. Module according to any one of claims 1 to 3, characterized in that the first adjustment screw (18) and the second adjustment screw (25) are located in the same plane perpendicular to an axis (Y) of the blade (11).

5. Module according to any one of claims 1 to 4, characterized in that the first contact face (20) and the second contact face (27) extend in a plane parallel to an axis (Y) of the blade (H).

6. Module according to any one of claims 1 to 5, characterized in that the first contact face (20) and the second contact face (27) form an angle of 180 degrees with respect to each other.

7. Module according to any one of claims 1 to 6, characterized in that the assembly formed by one end of the first adjustment screw (18) and one end of the second adjustment screw (25) protruding respectively from the first threaded through hole (19) and the second threaded through hole (26), is arranged inside a housing (30) located under a vein of the module.

8. Module according to claim 7, characterized in that it comprises an access cover (31) reconstituting the vein allowing access to the first adjustment screw (18) and to the second adjustment screw (25) 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 rotor module.

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

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