Transient unbalance simulation device and turbomachine equipped with such a device

Abstract

Transient unbalance simulation device (10) configured to simulate a transient unbalance in a turbomachine (100) at a predetermined regime, the transient unbalance simulation device (10) comprising a mounting portion (12), a weight (14) and a fitting (16) mechanically connecting the mounting portion (12) and the weight (14), an assembly (E) formed by the fitting (16) and the weight (14) being configured to adopt a first configuration when the regime of the turbomachine (100) is below a predetermined regime, and to take a second configuration distinct from the first configuration, when the regime of the turbomachine (100) is greater than or equal to the predetermined regime, in which in the first configuration the weight (14) is disposed in a first position (P1) and in the second configuration the weight (14) is disposed in a second position (P2) distinct from the first position (P1).Figure for the abridged version: Fig. 4.

Description

Title of the invention: Transient unbalance simulation device and turbomachine equipped with such a device technical field

[0001] The present exposition relates to a transient unbalance simulation device and a turbomachine equipped with such a device.

[0002] The term "turbomachine" refers to all gas turbine devices that produce motive power, among which a distinction is made in particular between turbojets, which provide the thrust necessary for propulsion by reaction to the high-speed ejection of gas, and turboshaft engines, in which motive power is supplied by the rotation of a drive shaft. For example, turboshaft engines are used as engines for helicopters, ships, trains, or as industrial engines. Turboprops (turboshaft engines driving a propeller) are also turboshaft engines used as aircraft engines. Previous technique

[0003] Under certain flight conditions of an aircraft equipped with a turboprop engine, a transient imbalance can occur within the turbomachine, for example, during bird strike or when conditions are such that ice forms at the turbomachine inlet (so-called "icing" conditions). In the latter case, the ice formed can detach in chunks from a rotor, the residual ice adhering to the rotor then generating an imbalance (a phenomenon known as "ice shedding").

[0004] In order to test and size turbomachines for this type of event, it is important to be able to simulate a transient unbalance on a test bench. Known devices of the "imposed unbalance" type, where a weight is simply fixed eccentrically within the turbomachine, of the "impulse excitation" or "ping test" type, where the impulse response of the equipment at standstill is studied, or even of the "actuator" type, which allows a weight to be physically moved within a turbomachine in operation, are either not sufficiently representative of the phenomenon studied, or too cumbersome and complex to implement.

[0005] Other systems related to an unbalance phenomenon are known from FR3125087, FR2943726 and FR2943725, but these systems are for turbomachinery in operation, are not for experimental purposes and are unrelated to the context of this presentation.

[0006] There is therefore a need for a simple and effective experimental device for simulating transient unbalance within a running turbomachine. Description of the invention

[0007] One embodiment relates to a transient unbalance simulation device configured to simulate a transient unbalance in a turbomachine at a predetermined speed, the transient unbalance simulation device comprising a mounting portion configured to be fixed to a rotating element of the turbomachine, a weight and a fitting mechanically connecting the mounting portion and the weight, an assembly formed by the fitting and the weight being configured to adopt a first configuration when the turbomachine speed is below a predetermined speed, and to take a second configuration distinct from the first configuration, when the turbomachine speed is greater than or equal to the predetermined speed,in which, in the first configuration, the weight is disposed in a first position relative to the mounting portion, and in the second configuration, the weight is disposed in a second position relative to the mounting portion, distinct from the first position.

[0008] In the following, and unless otherwise indicated, "the device" means "the transient unbalance simulation device".

[0009] In use, the mounting portion can be attached to a turbine rotor, for example, a rotating shaft, a rotating bladed wheel, or any other rotating element of the turbine. For example, in the first configuration, the device can be configured to be balanced and not generate any imbalance within the turbine when the turbine speed is below the predetermined speed (i.e., in the first configuration).

[0010] The weight is mechanically connected to the mounting portion via the fitting. The fitting may have a certain rigidity to maintain the weight in the initial position as long as the turbomachine speed, i.e., the rotational speed of a rotating part of the turbomachine, for example, the rotational speed of the fan, the low-pressure housing shaft, or the high-pressure housing shaft, is below the predetermined speed. For example, the fitting may be configured to exhibit no elastic deformation, or negligible elastic deformation, as long as the turbomachine speed is below the predetermined speed.For example, the predetermined speed can be between 1000 rpm (one thousand revolutions per minute) and 30000 rpm (thirty thousand revolutions per minute), for example between 1000 rpm (one thousand revolutions per minute) and 10000 rpm (ten thousand revolutions per minute) for a device configured to simulate a transient unbalance within a low-pressure rotor, for example between 10000 rpm (ten thousand revolutions per minute) and 30000 rpm (thirty thousand revolutions per minute) for a device configured to simulate a transient unbalance within a high-pressure rotor.

[0011] The assembly comprising the weight and the fitting (hereinafter and unless otherwise specified, "the assembly") is configured so that, when the turbomachine is running becomes greater than or equal to the predetermined speed, the weight moves from the first position to the second position. For example, the assembly can be configured to move from the second configuration to the first configuration, and therefore for the weight to move from the second position to the first position, when the turbomachine speed falls below the predetermined speed, but not necessarily.

[0012] For example, the fitting and / or the weight may have a sacrificial portion or a portion configured to break and allow the weight to move from the first position to the second position when the turbomachine speed becomes greater than or equal to the predetermined speed. For example, the fitting may include a sacrificial screw holding the weight in the first position within a guide or rail, the screw being breakable, for example by shear stress, from a threshold force reached when the turbomachine speed becomes greater than or equal to the predetermined speed, the weight then being guided by the rail to the second position (for example reached when the weight cooperates against a suitable stop).In another example, the fitting and / or the weight may have a ratchet (or ratchet system) configured to allow the weight to move from the first position to the second position when the turbomachine speed becomes greater than or equal to the predetermined speed. In yet another example, the fitting and / or the weight may be configured to deform elastically (i.e., within the elastic range of the materials) or plastically (i.e., within the plastic range of the materials) and allow the weight to move from the first position to the second position when the turbomachine speed becomes greater than or equal to the predetermined speed.

[0013] The first and second positions can be two discrete and distinct positions, and the transition from one to the other can be brief or instantaneous. In other words, the transition from the first position to the second position, and possibly vice versa, may not be gradual over time, or may not be proportional to the rotor's rotational speed. That is to say, the counterweight does not have an equilibrium position between the first and second positions. The transition from the first to the second position characterizes the "transient" aspect of the unbalance: in the first position there is no unbalance (or negligible for the test in question), while in the second position there is a predetermined unbalance, the transition from the first to the second position being instantaneous when the turbomachine's speed becomes greater than or equal to the predetermined speed.

[0014] For example, the second position may be offset only radially, for example radially outwards, relative to the first position. For example, the second position may be radially distant from the first position by a distance of between 5 mm (five millimeters) and 500 mm (five hundred millimeters). For example, the mass of the counterweight can range from 1 g (one gram) to 500 g (five hundred grams). For example, the device can be configured so that the transient unbalance ranges from 100 cm·g (one hundred centimeter-grams) to 30,000 cm·g (thirty thousand centimeter-grams). For example, the fitting can be metallic, such as steel or titanium, or any steel and / or titanium alloy, for a rotor upstream of a combustion chamber, or nickel or Inconel, or any nickel- or Inconel-based alloy, for a rotor downstream of a combustion chamber.

[0015] As a reminder, generally speaking, within a turbomachine, the axial direction corresponds to the direction of the axis of rotation of a shaft of the gas generator, and a radial direction is a direction perpendicular to the axis of rotation. The azimuthal or circumferential direction corresponds to the direction describing a ring around the axial direction. The three directions—axial, radial, and azimuthal—correspond respectively to the directions defined by the ridge, the radius, and the angle in a cylindrical coordinate system.

[0016] By allowing the counterweight to move from the first position to the second position when the turbomachine's operating speed becomes greater than or equal to the predetermined speed, the device simulates the instantaneous generation of an unbalance of a predetermined mass (i.e., the mass of the counterweight) at a predetermined position (the second position), starting from the predetermined operating speed. The device thus allows for precise control of the experimental parameters for generating an unbalance, while offering a simple structure that is easy to install within the turbomachine (via the mounting portion). In other words, the device allows a predetermined unbalance to evolve as quickly as possible in order to reproduce a transient phenomenon during an accidental event, for example, during the ingestion of a bird or the release of ice.This type of event is distinct from a case of sustained and stabilized imbalance, which can occur if the rotor is poorly balanced or if a component is damaged or worn.

[0017] In some embodiments, the fastening portion may include a ring. According to one variant, the fastening portion may include only a ring.

[0018] Such a mounting portion can ensure a certain balance in the first configuration, ease and reliability of mounting on a rotating element of the turbomachine, and a simple structure facilitating the fabrication of the device. Such a mounting portion can contribute to controlling the experimental parameters for generating an imbalance, while providing the device with a simple structure that is easy to install within the turbomachine.

[0019] In certain embodiments, the first position of the weight can be ra- diamentally closer to a center of the ring than the second position of the weight, the first and second positions being radially inside the ring.

[0020] Such an arrangement of the first and second positions relative to the ring can contribute to controlling the experimental parameters for generating an imbalance, while providing the device with a simple structure that is easy to install within the turbomachine. This can, for example, also allow for easy assembly / disassembly of the device, which can lead to a reduction in the use time of the test bench, compared to the assembly / disassembly time of a more complex prior art device, or even avoid the use of explosives requiring the presence of a pyrotechnician to artificially generate an imbalance on a test bench.

[0021] In some embodiments, the connection may include a beam. According to one variant, the connection may include only a beam.

[0022] The term "beam" means any element having a large length relative to the dimensions of its cross-section (i.e., transverse to the length direction), for example, a length at least ten times greater than the maximum extent of the cross-section (for example, an extent along a width or height direction, or a diameter, etc.). The cross-section may have any shape.

[0023] For example, the beam has a first end and a second end opposite the first end, the first end being mechanically connected to the mounting portion while the second end is mechanically connected to the counterweight. For example, the beam extends radially. For example, the mounting portion comprises a ring, the beam extends radially from the ring towards the inside of the ring, and the counterweight is arranged radially inside the ring.

[0024] Such a beam can contribute to controlling the experimental parameters to generate an imbalance, while providing the device with a simple structure that is easy to install within the turbomachine.

[0025] In some embodiments, the unbalance simulation device can be configured so that the beam deforms by buckling when the turbomachine regime is greater than or equal to the predetermined regime.

[0026] For example, the buckling can be elastic buckling so that the assembly can return to the first configuration when the turbomachine speed becomes lower than the predetermined speed.

[0027] The beam can maintain the counterweight in the first position as long as the turbomachine speed is below the predetermined speed, and when the turbomachine speed becomes greater than or equal to the predetermined speed, the beam buckles under the effect of the centrifugal force exerted by the counterweight which exceeds a predetermined threshold determined and instantly moves the counterweight from the first position to the second position. When the turbomachine's speed drops below the predetermined speed, the centrifugal force exerted by the counterweight on the beam falls below the predetermined threshold, causing the beam to instantly right itself and return the counterweight from the second position to the first position. Since the buckling phenomenon is very rapid, instantaneous, the device can produce an imbalance in the shortest possible time to simulate an accidental transient such as a bird strike or an ice release.

[0028] For example, the beam may have in the first configuration an imposed shape suitable for ensuring controlled deformation of the beam when the weight passes from the first position to the second position, and ensuring that buckling occurs on the desired side.

[0029] Such a deformable beam, deformable by buckling, can contribute to controlling the experimental parameters for generating an unbalance, while providing the device with a particularly simple structure that is easy to install within the turbomachine. The device can be reused, which can make it particularly economical.

[0030] In some embodiments, the transient unbalance simulation device may include a guide configured to guide the weight in translation between the first position and the second position.

[0031] For example, the guide can extend radially and can be configured to guide the weight radially, for example, only radially. Such a guide can be implemented with various solutions, such as, for example, the sacrificial piece, the ratchet system, or the beam configured to deform by buckling mentioned above.

[0032] Such a guide can improve control of the weight's movement between the first and second positions, as well as maintaining the weight in these two positions. In other words, the guide can control the weight's trajectory between the first and second positions. The guide can contribute to controlling the experimental parameters for generating an imbalance, while providing the device with a simple structure that is easy to install within the turbomachine.

[0033] In some embodiments, the weight may have a spherical shape or a cylindrical shape with a circular cross-section.

[0034] For example, the circular section cylinder may have an axis extending perpendicularly to the radial direction, for example perpendicularly to the length direction of the beam, and for example parallel to the plane of the ring of the fastening portion.

[0035] Such shapes can, for example, allow rotational movements of the weight, for example relative to the possible guide, thereby preventing buckling of the The beam can remain free and unconstrained. In other words, such shapes of the counterweight can ensure that the degrees of freedom necessary to allow the beam to buckle remain free (i.e., unconstrained).

[0036] In some embodiments, the fastening portion can be configured to be fixed to a flange for the attachment of a turbojet fan cone.

[0037] This can allow a particularly easy, reliable and quick assembly of the device within a turbomachine such as a turbojet, the blower cone being a portion directly accessible from outside the turbojet and easily removable to access the flange on which the cone is mounted.

[0038] One embodiment relates to a turbomachine comprising a transient unbalance simulation device according to any one of the embodiments described in this presentation. Brief description of the drawings

[0039] The purpose of this presentation and its advantages will be better understood upon reading the detailed description below of various embodiments given by way of non-limiting examples. This description refers to the attached figure pages, on which:

[0040] [Fig-1] [Fig.1] partially represents a turbomachine equipped with a device simulation of transient unbalance,

[0041] [Fig.2] Fig.2 represents a perspective view of the transient unbalance simulation device,

[0042] [Fig.3] [Fig.3] shows a cutaway view of the turbomachine of [Fig.1], when the turbomachine speed is below a predetermined speed,

[0043] [Fig.4] [Fig.4] shows a cutaway view of the turbomachine of [Fig.1], when the turbomachine speed is greater than or equal to the predetermined speed,

[0044] [Fig. 5] Fig. 5 represents a variant of the transient unbalance simulation device, and

[0045] [Fig.6] The [Fig.6] represents a variant of mounting a transient unbalance simulation device within a turbomachine. Description of the implementation methods

[0046] Figure 1 shows a partial view of a turbomachine 100, in this example a turbojet, equipped with a transient unbalance simulation device 10. The turbomachine 100 comprises, in this example, a fan 52 and a gas generator 54. In this example, the gas generator 54 comprises, from upstream to downstream, a compressor (or compressor section), a combustion chamber, and a turbine (or turbine section). For the sake of simplification and readability of Figure 1, only a portion of the... The pressurizer, in this example a part of the low-pressure compressor 54CBP, is shown; the other elements of the gas generator are not shown and are well known from other sources. The nacelle 80 of the turbomachine 100 is shown schematically, the turbomachine 100 being, for example, mounted on a test bench (not shown). In this example, the transient unbalance simulation device 10 is mounted upstream of the combustion chamber, for example, upstream of the gas generator 54. Figure 6 shows a variant where the transient unbalance simulation device 10 is mounted within a turbine 102 of a turbomachine, for example, a low-pressure turbine, downstream of the combustion chamber.

[0047] Figure 2 shows in more detail the transient unbalance simulation device 10. The device 10 is configured to simulate a transient unbalance in a turbomachine at a predetermined speed. The transient unbalance simulation device 10 comprises a mounting portion 12 configured to be fixed to a rotating element of the turbomachine 100, a weight 14, and a fitting 16 mechanically connecting the mounting portion 12 and the weight 14. An assembly E formed by the fitting 16 and the weight 14 is configured to adopt a first configuration (see Figures 2 and 3) when the speed of the turbomachine 100 is below a predetermined speed, and to assume a second configuration (see Figure 4), distinct from the first configuration, when the speed of the turbomachine 100 is greater than or equal to the predetermined speed.In the first configuration the weight 14 is disposed at a first position PI relative to the fixing portion 12 and in the second configuration the weight 14 is disposed at a second position P2 relative to the fixing portion 12, distinct from the first position PL.

[0048] In this example, the mounting portion may include a ring 12 with axis X. The ring 12 may have a plurality of holes through 12A, for example, for the passage of mounting bolts 90A or 190A (see [Fig. 1] or [Fig. 6]). The ring 12 may have a radial width LR that varies along the circumferential direction C, to ensure the balance of the device 10 so that it does not generate any imbalance when the assembly E is in the first configuration and the turbomachine speed is below the predetermined speed. According to an alternative (not shown), the ring 12 may have a constant radial width LR along the circumferential direction C and be equipped with a counterweight for balancing.

[0049] In this example, the fitting may include a beam 16 extending along a length direction L (the length Lo of the beam being measured along the length direction L). The beam 16 may extend radially inside the ring 12, such that the length direction L is parallel to the radial direction R of the ring 12. The beam 16 may have a tongue shape. For example, the tongue may have a rectangular cross-section in the length direction L. Beam 16 has a first end 16A and a second end 16B opposite the first end 16A along the length direction L, the first end 16A being mechanically connected to the ring 12 while the second end 16B is mechanically connected to the counterweight 14. The counterweight 14 can be arranged radially inside the ring 12. As will be described in more detail below, the device 10 is configured so that the beam 16 deforms by buckling when the speed of the turbomachine 100 is greater than or equal to the predetermined speed.

[0050] For example, the ring may have a maximum radial width LR1, or be equipped with a counterweight not shown, at a position diametrically opposite to the fitting 16.

[0051] For example, the fastening portion 12 and the fitting 16 may form a single part, for example, resulting from cutting a sheet of metal. For example, the fastening portion may comprise only the ring 12 and the fitting may comprise only the beam 16.

[0052] The counterweight 14 may have a spherical shape (variant not shown) or, as in the present example, a cylindrical shape with a circular cross-section. In this example, the cylindrical counterweight 14 has an axis B, perpendicular to the radial direction R and parallel to the plane of the ring 12. In this example, the axis B is inscribed in a plane P containing the neutral fiber (not shown) of the beam 16. With reference to Figures 3 and 4, the first position PI of the counterweight 14 is radially closer to the center A of the ring 12 than the second position P2 of the counterweight 14, the first and second positions PI and P2 being radially inside the ring 12. According to an example not shown, the position PI may correspond to a position centered on the axis of the turbomachine 100 when the device 10 is mounted on the turbomachine 100. For example, the position PI may correspond to the center of the ring 12.For example, to determine the position of the weight 14, one can consider the position of the center of gravity of the weight 14. In the example of figures 2, 3 and 4, the position PI is eccentric with respect to the center A of the ring 12.

[0053] In the present example, the device 10 may include a guide 18 configured to guide the weight 14 in translation between the first position PI and the second position P2. In this example, the guide 18 is a radial guide, which radially guides the weight 14 between positions PI and P2. In this example, the guide 18 can constrain any translational displacement of the weight along the axial direction X and its rotational displacement about the radial direction R. The fitting 16 may, for example, have sufficient rigidity to block any translational displacement of the weight 14 along the circumferential direction C and its rotational displacement about the axial direction X. In this example, the guide 18 and the weight 14 may be configured to allow rotational movements of the weight around a direction perpendicular to the radial direction R and parallel to the plane of the ring 12, in this example around the direction of the axis B of the weight 14. In this example, the guide 18 may include four rods 18A extending within the ring 12 parallel to the length direction L of the beam 16, and framing the weight 14 in pairs along the axial direction X. For example, the weight 14 has two free end portions 14A and 14B opposite along the direction of the axis B of the weight 14, each end 14A and 14B being sandwiched along the axial direction X by a pair of rods 18A. The cylindrical shape of the weight 14 allows the latter to rotate around its axis B within the guide 18, and permits a bending of the beam 16 leading to its buckling and a purely radial translational displacement of the weight 14.As shown in [Fig.2], when device 10 is not in use, assembly E is in the first configuration and the weight is in the first position PI.

[0054] In this example, for mounting the device 10 within a turbomachine, the mounting portion 12 is configured to be fixed to a flange 90 for the attachment of a turbojet fan cone 92 (see [Fig.1]). In this example, the ring shape of the mounting portion 12 and the holes 12B allow the device 10 to be attached to the flange 90 of the turbomachine 100 for the attachment of the cone 92 of the blower 52. In this example, when the device 10 is mounted within the turbomachine 10, the axial X, radial R and circumferential C directions of the device 10 and the turbomachine 100 coincide, so that the axial, radial and circumferential directions of the device 10 correspond respectively to the axial, radial and circumferential directions of the turbomachine 100. The mounting portion 12 can be configured to be fixed between two successive turbine wheel discs 192 and 194 (see [Fig. 6]).

[0055] In operation, when the turbomachine 100 is running at a speed lower than the predetermined speed, in this example when the fan 52 is rotating at a speed lower than the predetermined speed, the assembly E remains in the first configuration, as shown in [Fig. 3]. The counterweight 14 is in the first position PI, and no imbalance is generated. When the turbomachine 100 is running at a speed greater than or equal to the predetermined speed, in this example when the fan 52 is rotating at a speed greater than or equal to the predetermined speed, the centrifugal force exerted by the counterweight 14 on the beam 16 becomes such that the beam 16 is deformed by buckling, in this example by elastic buckling, and the assembly E instantaneously changes from the first configuration shown in [Fig. 3] to the second configuration shown in [Fig. 4].The weight 14 then instantly moves from the first position PI to the second position P2, and a predefined imbalance, . Since the mass of the counterweight and the position P2 are predefined, the unbalance is generated instantaneously. All measurements can then be taken and all relevant parameters of the turbomachine 100 recorded under these experimental conditions of unbalance simulation. In this example, the buckling of beam 16 being elastic, when the speed of the turbomachine 100 falls below the predetermined speed (in this example, when the fan 52 rotates again at a speed below the predetermined speed), the centrifugal force exerted by the counterweight 14 on beam 16 decreases and becomes sufficient again, causing beam 16 to straighten. The assembly E returns to its initial configuration, and the counterweight 14 returns from the second position P2 to the first position PI. The device 10 can then be reused for other tests, either within the same turbomachine or on another turbomachine.

[0056] In general, the experimental parameters for simulating the unbalance, and in particular the predetermined regime, can for example be determined by the dimensioning of the beam and the counterweight. For example, the beam can be dimensioned to buckle when subjected to a force greater than or equal to a force F = M (Ro - Lo) O2 , where the force F is expressed in Newtons (N), M is the mass of the counterweight 14 expressed in kilograms (Kg), Ro is the internal radius of the ring 12 at the point of junction with the beam 16 expressed in meters (m), Lo is the length of the beam 16 expressed in meters (m), and Q is the regime or speed of rotation to which the device 10 is subjected expressed in radians per second (rad / s), the characteristics of the beam 16 being able to be obtained via the Euler formula p = n2 EI / (0.7.Lo)2, where the force F is expressed in Newtons (N), E is the Young's modulus expressed in Pascals (Pa), I is the second moment of area of ​​beam 16 expressed in meters to the fourth power (m4), and Lo is the length of beam 16 expressed in meters (m). Note that the coefficient 0.7 is specific to this example and is related to the presence of guide 18. In a variant without guide 18, the coefficient 0.7 would be replaced by 2.0.

[0057] Figure 5 represents a transient unbalance simulation device 110 according to a variant of the device 10 in which the fitting / beam 16 is replaced by a radially extending fitting / rod 116 having two notches 116A, 116B configured to receive the weight 14 and hold it in position in two different positions. The other elements are unchanged from the device 10, retain the same datum symbols, and are not described again. The notch 116A, the one closest to the X-axis along the radial direction R, is configured to hold the weight 14 in the first position P1, while the notch 116B, the one furthest from the X-axis along the radial direction R, is configured to hold the weight 14 in the second position P2. Between the two notches 116A and 116B, the rod 116 forms a track configured to radially guide the weight 14 between the first position PI and the second position P2. When the turbomachine speed is below a predetermined speed, the weight 14 remains within the notch 116A, in the first position PL. When the turbomachine speed is greater than or equal to the predetermined speed, under the effect of the centrifugal force exerted by the weight 14, the rod 116 deforms elastically so that the weight 14 disengages from the notch 116A, slides radially outwards along the track until it engages in the second notch 116B, in the second position P2. The rod 116 and the notches 116A and 116B form an example of a ratchet system configured to allow the weight 14 to move from the first position PI to the second position P2 when the turbomachine speed becomes greater than or equal to the predetermined speed. Just like device 10, device 110 can be mounted upstream of the gas generator (see [Fig.1]) or within a turbine (see [Fig.6]).

[0058] Although the present invention has been described with reference to specific embodiments, it is evident that modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the claims. In particular, individual features of the various embodiments illustrated / mentioned can be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than a restrictive sense.

[0059] It is also evident that all the characteristics described with reference to a process are transposable, alone or in combination, to a device, and conversely, all the characteristics described with reference to a device are transposable, alone or in combination, to a process.

Claims

Demands

1. Transient unbalance simulation device (10, 110) configured to simulate a transient unbalance in a turbomachine (100) at a predetermined speed, the transient unbalance simulation device (10, 110) comprising a mounting portion (12) configured to be fixed to a rotating element (52) of the turbomachine (100), a weight (14) and a fitting (16, 116) mechanically connecting the mounting portion (12) and the weight (14), an assembly (E) formed by the fitting (16, 116) and the weight (14) being configured to adopt a first configuration when the speed of the turbomachine (100) is below a predetermined speed, and to take a second configuration distinct from the first configuration, when the speed of the turbomachine (100) is greater than or equal to the predetermined speed,in which in the first configuration the weight (14) is disposed at a first position (PI) relative to the fixing portion (12) and in the second configuration the weight (14) is disposed at a second position (P2) relative to the fixing portion (12), distinct from the first position (PD-,

2. Transient unbalance simulation device (10, 110) according to claim 1, wherein the fastening portion includes a ring (12).

3. Transient unbalance simulation device (10, 110) according to claim 2, wherein the first position (PI) of the weight (14) is radially closer to a center (A) of the ring (12) than the second position (P2) of the weight (14), the first position (PI) and the second position (P2) being radially inside the ring (12).

4. Transient unbalance simulation device (10) according to any one of claims 1 to 3, wherein the fitting comprises a beam (16).

5. Transient unbalance simulation device (10) according to claim 4, configured so that the beam (16) deforms by buckling when the turbomachine (100) regime is greater than or equal to the predetermined regime.

6. Transient unbalance simulation device (10, 110) according to any one of claims 1 to 5, comprising a guide (18) configured to guide the weight (14) in translation between the first position (PI) and the second position (P2).

7. Transient unbalance simulation device (10, 110) according to any one of claims 1 to 6, wherein the weight (14) has a spherical shape or a cylindrical shape with a circular cross-section.

8. Transient unbalance simulation device (10, 110) according to any one of claims 1 to 7, wherein the fastening portion (12) is configured to be fixed to a flange (90) for the attachment of a turbojet fan cone (92).

9. Turbomachine (100) comprising a transient unbalance simulation device (10, 110) according to any one of claims 1 to 8.

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