SYSTEM FOR VIBRATION MANAGEMENT IN ROTATING MACHINERY

Abstract

A system (1) for vibration management comprises a stator (24, 45); a rotor (26) being mounted rotatably with respect to the stator (24, 45) about a rotational axis (9); one or more active devices (41A-41C) adapted to apply forces and/or moments on the rotor (26) and/or on the stator (24, 45); at least two sensors (42) for measuring vibrational parameter values with respect to two or more different positions, particularly along the rotational axis (9); and a controller (44) adapted to provide control signals to the one or more active devices (41A-41C) based on the vibrational parameter values of the at least two sensors (42) and on the respective position.

Claims

1. A system (1) for vibration management, comprising: a stator (24, 45); a rotor (26) being mounted rotatably with respect to the stator (24, 45) about a rotational axis (9); one or more active devices (41A-41C) adapted to apply forces and/or moments on the rotor (26) and/or on the stator (24, 45); at least two sensors (42) for measuring vibrational parameter values with respect to two or more different positions, particularly along the rotational axis (9); and a controller (44) adapted to provide control signals to the one or more active devices (41A-41C) based on the vibrational parameter values of the at least two sensors (42) and on the respective position.

2. A system (1) for vibration management, in particular according to claim 1, comprising: a stator (24, 45); a rotor (26) being mounted rotatably with respect to the stator (24, 45) about a rotational axis (9); at least two active devices (41A-41C) arranged at two or more different positions, particularly along the rotational axis (9), and each being configured to apply forces and/or moments on the rotor (26) and/or on the stator (24, 45); and a controller (44) adapted to receive operating parameter values and/or vibrational parameter values and to provide control signals to the at least two active devices (41A-41C) based on the operating parameter values and/or the vibrational parameter values, and the position of the respective active device (41A-41C).

3. The system (1) according to claim 1 or 2, wherein the controller (44) is adapted to provide the control signals to the one or more active devices (41A-41C) based on a ratio of two values associated with the two different positions, wherein, optionally, the two values are the vibrational parameter values, or values of a stiffness of the rotor (26) and/or the stator (24, 45).

4. The system (1) according to any of the previous claims, wherein the rotor (26) and/or the stator (24, 45) has at least one mode shape (M1-M10) with at least one deflection maximum at a position along the rotational axis (9), wherein at least one of the active devices (41A-41C) is arranged at this position along the rotational axis (9).

5. The system (1) according to any of the previous claims, wherein the rotor (26) is rotatably mounted with respect to the stator (24, 45) about the rotational axis (9) by means of contact bearings (43), wherein the contact bearings (43) are adapted for supporting the entire load of the rotor (26) in operation.

6. The system (1) according to any of the previous claims, wherein the controller (11) is further adapted to receive and/or determine an indication of a change of the operating parameter versus time, to determine a point in time when a resonance condition will be met based on the operating parameter and the change of the operating parameter, and to control at least one of the active devices (41A-41C) at a predetermined time offset prior to the determined point in time.

7. The system (1) according to any of the previous claims, comprising at least two active devices (41A-41C), wherein the controller (4) is adapted to detect and identify a resonance condition, to select a subset of the at least two active devices (41A-41C) based on the identified resonance condition, and to provide control signals to the subset of the at least two active devices (41A-41C), the subset including at least one active device (41A-41C).

8. The system (1) according to any of the previous claims, comprising at least two active devices (41A-41C), wherein the controller (44) is further adapted to select a subset of the at least two active devices (41A-41C) based on the operating parameter value, and to provide control signals to the subset of the at least two active devices (41A-41C), the subset including at least one active device (41A-41C).

9. The system (1) according to any of the previous claims, wherein the controller (44) is adapted to provide control signals to at least one of the active devices (41A-41C) to excite a vibration of the rotor (26).

10. The system (1) according to any of the previous claims, wherein the controller (44) is adapted to provide control signals to at least one of the active devices (41A-41C) to apply the forces on the rotor (26) and/or on the stator (24, 45) based on a target stiffness of the rotor (26) and/or of the stator (24, 45).

11. The system (1) according to any of the previous claims, wherein the forces that the one or more active devices (41A-41C) are adapted to apply are non-contact forces.

12. The system (1) according to any of the previous claims, wherein at least one of the one or more active devices (41A, 41B) is adapted to exert radial and/or axial forces with respect to the rotational axis (9).

13. The system (1) according to any of the previous claims, wherein at least one of the one or more active devices (41C) is adapted to exert tangential forces with respect to the rotational axis (9).

14. The system (1) according to claim 13, wherein each of two or more active devices (41C) is adapted to exert tangential forces on the rotor (9) with respect to the rotational axis (9).

15. An engine (10) for an aircraft (8) comprising the system (1) according to any of the previous claims.

Description

[0029] Embodiments will now be described by way of example only, with reference to the schematic Figures, in which:

[0030] FIG. 1 is an aircraft having a plurality of engines;

[0031] FIG. 2 is a sectional side view of a gas turbine engine;

[0032] FIG. 3 is a close up sectional side view of an upstream portion of a gas turbine engine;

[0033] FIG. 4 is a partially cut-away view of a gearbox for a gas turbine engine;

[0034] FIGS. 5A and 5B are views of a system for vibration management;

[0035] FIG. 6 is a view of the system of FIGS. 5A and 5B;

[0036] FIGS. 7 and 8 are diagrams for illustrating a performance of the system according to FIGS. 5A-6;

[0037] FIG. 9 illustrates the function of the system according to FIGS. 5A-6;

[0038] FIG. 10 is a diagram showing oscillation frequencies of an example rotor of the system of FIGS. 5A-6 at various modes; and

[0039] FIG. 11 is a diagram of vibration amplitudes versus time.

[0040] FIG. 1 shows an aircraft 8 in the form of a passenger aircraft. The aircraft 8 comprises several (i.e., two) gas turbine engines 10 in accordance with FIG. 2.

[0041] FIG. 2 illustrates a gas turbine engine 10 having a principal rotational axis 9. The engine 10 comprises an air intake 12 and a propulsive fan 23 that generates two airflows: a core airflow A and a bypass airflow B. The gas turbine engine 10 comprises a core 11 that receives the core airflow A. The engine core 11 comprises, in axial flow series, a low pressure compressor 14, a high-pressure compressor 15, combustion equipment 16, a high-pressure turbine 17, a low pressure turbine 19 and a core exhaust nozzle 20. A nacelle 21 surrounds the gas turbine engine 10 and defines a bypass duct 22 and a bypass exhaust nozzle 18. The bypass airflow B flows through the bypass duct 22. The fan 23 is attached to and driven by the low pressure turbine 19 via a shaft 26 and an epicyclic gearbox 30.

[0042] In use, the core airflow A is accelerated and compressed by the low pressure compressor 14 and directed into the high pressure compressor 15 where further compression takes place. The compressed air exhausted from the high pressure compressor 15 is directed into the combustion equipment 16 where it is mixed with fuel and the mixture is combusted. The resultant hot combustion products then expand through, and thereby drive, the high pressure and low pressure turbines 17, 19 before being exhausted through the nozzle 20 to provide some propulsive thrust. The high pressure turbine 17 drives the high pressure compressor 15 by a suitable interconnecting shaft 27. The fan 23 generally provides the majority of the propulsive thrust. The epicyclic gearbox 30 is a reduction gearbox.

[0043] An exemplary arrangement for a geared fan gas turbine engine 10 is shown in FIG. 3. The low pressure turbine 19 (see FIG. 2) drives the shaft 26, which is coupled to a sun wheel, or sun gear, 28 of the epicyclic gear arrangement 30. Radially outwardly of the sun gear 28 and intermeshing therewith is a plurality of planet gears 32 that are coupled together by a planet carrier 34. The planet carrier 34 constrains the planet gears 32 to precess around the sun gear 28 in synchronicity whilst enabling each planet gear 32 to rotate about its own axis. The planet carrier 34 is coupled via linkages 36 to the fan 23 in order to drive its rotation about the engine axis 9. Radially outwardly of the planet gears 32 and intermeshing therewith is an annulus or ring gear 38 that is coupled, via linkages 40, to a stationary supporting structure 24.

[0044] The stationary support structure 24 serves as a stator, the shaft 26 serves as a rotor. As shown in FIGS. 2 and 3, the gas turbine engine 10 also comprises contact bearings 43 and active devices 41A for the shaft 26. The active devices 41A are adapted to apply forces on the shaft 26, in the present example axial forces.

[0045] A controller 44 is adapted to provide control signals to the active devices 41A based on vibrational parameter values of one or more sensors arranged at the gas turbine engine, and on the position of the respective sensor along the rotational axis. In this example, the active devices 41A themselves serve as sensors. The active devices 41A comprises electric coils to create magnetic fields, and these coils are also used to detect vibrations of the nearby shaft 26.

[0046] Further, the controller 44 is adapted to receive operating parameter values, namely speed of the shaft 26 and transmitted power and/or torque, and to provide control signals to the active devices 41A based on the operating parameter values and/or the vibrational parameter values, and based on the position of the respective active device.

[0047] The shaft 26, stationary support structure 24, active devices 41A (which in this example also act as sensors while alternatively dedicated sensors may be provided instead or in addition) and the controller 44 together serve as a system for vibration management.

[0048] Note that the terms “low pressure turbine” and “low pressure compressor” as used herein may be taken to mean the lowest pressure turbine stages and lowest pressure compressor stages (i.e. not including the fan 23) respectively and/or the turbine and compressor stages that are connected together by the interconnecting shaft 26 with the lowest rotational speed in the engine (i.e. not including the gearbox output shaft that drives the fan 23). In some literature, the “low pressure turbine” and “low pressure compressor” referred to herein may alternatively be known as the “intermediate pressure turbine” and “intermediate pressure compressor”. Where such alternative nomenclature is used, the fan 23 may be referred to as a first, or lowest pressure, compression stage.

[0049] The epicyclic gearbox 30 is shown by way of example in greater detail in FIG. 4. Each of the sun gear 28, planet gears 32 and ring gear 38 comprise teeth about their periphery to intermesh with the other gears. However, for clarity only exemplary portions of the teeth are illustrated in FIG. 4. There are four planet gears 32 illustrated, although it will be apparent to the skilled reader that more or fewer planet gears 32 may be provided within the scope of the claimed invention. Practical applications of a planetary epicyclic gearbox 30 generally comprise at least three planet gears 32.

[0050] The epicyclic gearbox 30 illustrated by way of example in FIGS. 3 and 4 is of the planetary type, in that the planet carrier 34 is coupled to an output shaft via linkages 36, with the ring gear 38 fixed. However, any other suitable type of epicyclic gearbox 30 may be used. By way of further example, the epicyclic gearbox 30 may be a star arrangement, in which the planet carrier 34 is held fixed, with the ring (or annulus) gear 38 allowed to rotate. In such an arrangement the fan 23 is driven by the ring gear 38. By way of further alternative example, the gearbox 30 may be a differential gearbox in which the ring gear 38 and the planet carrier 34 are both allowed to rotate.

[0051] It will be appreciated that the arrangement shown in FIGS. 3 and 4 is by way of example only, and various alternatives are within the scope of the present disclosure. Purely by way of example, any suitable arrangement may be used for locating the gearbox 30 in the engine 10 and/or for connecting the gearbox 30 to the engine 10. By way of further example, the connections (such as the linkages 36, 40 in the FIG. 3 example) between the gearbox 30 and other parts of the engine 10 (such as the input shaft 26, the output shaft and the fixed structure 24) may have any desired degree of stiffness or flexibility. By way of further example, any suitable arrangement of the bearings between rotating and stationary parts of the engine (for example between the input and output shafts from the gearbox and the fixed structures, such as the gearbox casing) may be used, and the disclosure is not limited to the exemplary arrangement of FIG. 3. For example, where the gearbox 30 has a star arrangement (described above), the skilled person would readily understand that the arrangement of output and support linkages and bearing locations would typically be different to that shown by way of example in FIG. 3.

[0052] Accordingly, the present disclosure extends to a gas turbine engine having any arrangement of gearbox styles (for example star or planetary), support structures, input and output shaft arrangement, and bearing locations.

[0053] Optionally, the gearbox may drive additional and/or alternative components (e.g. the intermediate pressure compressor and/or a booster compressor).

[0054] Other gas turbine engines to which the present disclosure may be applied may have alternative configurations. For example, such engines may have an alternative number of compressors and/or turbines and/or an alternative number of interconnecting shafts. By way of further example, the gas turbine engine shown in FIG. 2 has a split flow nozzle 20, 22 meaning that the flow through the bypass duct 22 has its own nozzle that is separate to and radially outside the core engine nozzle 20. However, this is not limiting, and any aspect of the present disclosure may also apply to engines in which the flow through the bypass duct 22 and the flow through the core 11 are mixed, or combined, before (or upstream of) a single nozzle, which may be referred to as a mixed flow nozzle. One or both nozzles (whether mixed or split flow) may have a fixed or variable area. Whilst the described example relates to a turbofan engine, the disclosure may apply, for example, to any type of gas turbine engine, such as an open rotor (in which the fan stage is not surrounded by a nacelle) or turboprop engine, for example. In some arrangements, the gas turbine engine 10 may not comprise a gearbox 30.

[0055] The geometry of the gas turbine engine 10, and components thereof, is defined by a conventional axis system, comprising an axial direction (which is aligned with the rotational axis 9), a radial direction (in the bottom-to-top direction in FIG. 2), and a circumferential direction (perpendicular to the page in the FIG. 2 view). The axial, radial and circumferential directions are mutually perpendicular.

[0056] Turning now to FIGS. 5A and 5B, a system 1 for vibration management will be described. The system may be part of the gas turbine engine 10 described above. Further, the system may be part of an electrical engine, e.g., for the aircraft 8 of FIG. 1. As will be described below, optionally, the system 1 may be simply equipped with a propeller to serve as engine.

[0057] The system 1 comprises a stator comprising stationary support structure 24. Contact bearings 43 rotatably support a rotor in the form of a shaft 26. In the present example, the rotor comprises a major section and a further rotor section 46. The rotor section 46 is coupled to the major section via a gearbox 47, or, more generally, by means of one or more flexible or teethed couplings. Optionally, more than the two contact bearings 43 shown in FIGS. 5A and 5B are provided, e.g., two for each section of the shaft 26.

[0058] The stator of system 1 further comprises a housing 45 mounted on the stationary support structure 24. In the present example, the housing 45 is cylindrical. The housing is arranged coaxially with the shaft 26. The housing 45 surrounds the shaft 26. The housing 45 is connected to the stationary support structure via reinforcements 48, but this is just an example. Optionally, the reinforcements 48 may be or comprise active devices, such as active devices 41A, 41B or 41C. Optionally, active devices 41A, 41B are arranged on the housing 45. Stationary support structure 24 may correspond the stationary support structure 24 shown in FIG. 2. Alternatively, it is different therefrom. Stationary support structure 24 may be a frame of the aircraft 8, e.g., of wing thereof. The housing 45 may be an engine housing, e.g., a turbine case or a fan case.

[0059] Further, the system comprises several active devices 41A-41C. Namely, the system 1 comprises active devices 41A for creating radial forces on the shaft 26 (and/or on the housing 45). These active devices 41A are arranged at different positions along the rotational axis 9. Some of the active devices 41A-41C may form an active device arrangement, among which, e.g., several active devices 41A-41C are arranged at the same axial position.

[0060] Further, the system 1 comprises an active device 41B for creating axial forces on the shaft 26 (and/or on the housing 45). One or more further active devices of this kind may be provided, particularly at other positions along the shaft 26.

[0061] The system 1 also comprises several, namely two, active devices 41C for creating tangential forces on the shaft 26 (and/or on the housing 45). These active devices 41C are arranged at different positions along the rotational axis 9.

[0062] In the present example, each of the active devices 41A-41C comprises one or more electric coils mounted on the housing 45. Alternatively or in addition, electric coils may be mounted on the shaft 26. Further, for example, permanent magnets can be mounted on or in the shaft adjacent the coils. An optional rotor lamination mounted around the shaft 26 rotates with the shaft 26, and comprises a ferromagnetic material such as iron. Hence, activation of the coils exerts a force on the shaft 26. For the axially acting active device 41B a disc including a ferromagnetic material as iron and/or one or more permanent magnets is fixed to the shaft 26, and coils are fixed to the housing 45 axially before and behind the disc. Thus, activation of the coils in front of or behind the disc exerts a force in one of the two directions along the rotational axis 9. An active device and/or a coil of an active device can also be located between two coaxial rotors (e.g., shafts), e.g., in order to variate the stiffness between rotor and stator.

[0063] The tangentially acting active devices 41C of the present example are designed in the form of electric motors. Indeed, the system 1 can be used as an electric engine, e.g., for aircraft 8 of FIG. 1.

[0064] The system may be part of an electric engine of a hybrid engine.

[0065] FIG. 6 shows four of the radially acting active devices 41A of FIG. 5B, which together form an active device arrangement. Each of the active devices 41A comprises an electromagnet. Each electromagnet comprises a coil 49 wound around an (optional) core, e.g., iron core. The cores are U shaped. The open ends of the U face the shaft 26. The electromagnets are arranged equidistantly around the shaft 26. Thus, in the present example, four electromagnets are provided.

[0066] Each coil 49 is electrically coupled to a current supply 50. The current supplies 50 are operatively coupled to the controller 44. The control signals of the controller 44 to the current supplies 50 result in magnetic forces acting on the shaft 26.

[0067] In FIG. 6, the shaft 26 is shown in three different deflections to illustrate a bending of the shaft 26 due to vibrations. Such bending can be counteracted by the active device 41A arrangement. If desired, however, such bending can also be effected by means of the active device 41A arrangement.

[0068] A mode of vibration is characterized by a modal frequency and a mode shape. It is numbered according to the number of half waves in the vibration. It is worth noting that different mode shapes can be exited at the same time (by multiple resonances). Also the system is able to measure the real shape of the modes in operational conditions (operational mode shapes).

[0069] It is worth noting that instead of providing an active device arrangement as shown in FIG. 6, the electromagnets can be applied in one single active device that is controlled as a whole. As another alternative, each two opposing electromagnets may be part of one active device and controlled together, independently of the other active device(s) at the same axial location.

[0070] FIG. 7 shows the first three mode shapes of the shaft 26 with respect to its longitudinal extension. On top, the first mode shape M1 is shown, towards the bottom of the figure mode shapes M2 and M3. The shaft 26 is shown rotatably mounted on the contact bearings 43. The shaft 26 may vibrate in these (and higher) modes of vibration, and it may be in a resonance with a frequency at or close to the corresponding modal frequency. Such vibration may lead to comparably large amplitudes.

[0071] Such vibrations can be effectively counteracted when applying forces to those locations on the shaft 26 along the rotational axis 9 which are at or closest to the maxima of the deflections of the shaft 26 in the corresponding mode. In FIG. 7, three axially acting active devices 41A are shown as examples. One of these active devices 41A is arranged at the center, i.e., at the maximum deflection in mode M1. Further, sensors 42 are arranged at different locations along the rotational axis 9. Here, five sensors 42 are shown as an example. At each of the active devices 41A, one of the sensors 42 is arranged. Two further sensors 42 are arranged further towards the bearings 43. Specifically, two active devices 41A, and sensors 42, correspondingly, are arranged at the nodes of the third mode shape M3. The two further sensors 42 are arranged at the locations of the maxima of the second mode shape M2.

[0072] Thus, it becomes clear that all three active devices 41A may be used to counteract the first mode shape M1, but the middle active device 41A will have the strongest effect, so this active device 41A is selected by the controller 44 to counteract the first mode shape M1.

[0073] However, that middle active device 41A is arranged at the node of the second mode shape M2. Therefore, it will have a diminishing effect for counteracting the second mode shape M2. For this purpose, the other two active devices 41A shown in FIG. 7 will be selected as a subset of the active devices 41A and controlled to exert forces on the shaft 26 to counteract the second mode shape M2.

[0074] In case of the third mode shape M3, the situation is opposite to the second mode shape M2. The two active devices 41A at the nodes of this mode shape M3 will have a diminishing effect against this mode shape M3. However, the middle active device 41A is arranged at the center maximum deflection of this mode shape M3 and is selected as a subset for counteracting this mode shape M3 by the controller 44.

[0075] FIG. 8 illustrates, in a further simplified manner, which of the mode shapes M1-M3 can be counteracted by which of the active devices 41A, as described above. It is worth considering that in practice several mode shapes can be excited from different driving forces.

[0076] In other words, the shaft 26 has mode shapes, and the active devices 41A (as well as the sensors 42) are located at characteristic points of these mode shapes, particularly the lowest 2, 3, 4 or 5 mode shapes. The characteristic points generally are maxima and/or nodes. Maxima and nodes have the character of extreme displacements and include radial, axial and rotative displacements.

[0077] The sensors 42 in this example are proximity probes measuring the distance to the shaft 26.

[0078] FIG. 9 illustrates that one or more of the bearings 43 may also be designed so as to allow rotation of the shaft 26 around an axis vertical to its longitudinal axis (corresponding to the rotational axis 9), as the bearing 43 shown in left in the figure. Alternatively or in addition one or more of the bearings 43 may be designed, as in FIG. 9, as a sliding bearing allowing an axial movement of the shaft 26, as the bearing 43 shown in the right in the figure. The bearings are displaced by a distance L. Between the bearings, an active device 41A is shown schematically as an example. The active device 41A exerts a non-contact force on the shaft 26, in this case a magnetic force. This force has the effect of a modified stiffness of the shaft 26, illustrated by K in the figure. The active device 41A is displaced from one of the bearings 43 (the left in FIG. 9) by a distance a. Therein, a is smaller than L. For example, a=L/2.

[0079] Above, the radially acting active devices 41A have been described, but the control of the axially and tangentially acting active devices 41B, 41C is correspondingly.

[0080] By modifying the stiffness of the shaft 26, its modes are mistuned, and therefore resonances can be counteracted. It is worth noting that during operation, the mode shapes may be detected by means of the sensors 42 measuring a characteristic deflection pattern. Alternatively, the controller 44 may store certain operating conditions, e.g., speed and/or power, at which certain mode shapes would occur when not counteracted by the active devices 41A-41C. Hence, the controller may selectively activate the corresponding active device 41A-41C to counteract a given mode shape M1-M3. Therefore, for example, when increasing the speed, the shaft 26 traverses several modal frequencies. By selective activation of the corresponding active device(s) 41A-41C, the corresponding mode shapes are mistuned. Thus, the system 1 allows a resonance mistuning on multiple modes.

[0081] FIG. 10 shows the lowest ten mode shapes M1-M10 and the corresponding frequencies. The system 1 allows to ride through these frequencies without exciting corresponding resonances, or only at strongly reduced amplitudes. This is possible by the distributed magnetic loads (by the active devices 41A-41C) obtained by coils integrated in the statoric cylinder housing 46 coaxial to the shaft 26. The controller 44 may perform a modal analysis, e.g., in the speed range of interest.

[0082] Optionally, the stiffness ratio between rotor (e.g., shaft 26) and stator (e.g., housing 45), or between two different parts of the rotor (shaft 26) may be used as the dimensionless most significant parameter to be modified to achieve the natural frequency mistuning by the controller 44. Further, using the tangentially acting active devices 41C, a torsional stiffness variation is possible. Even further, it is possible to use a torsional stiffness ratio between two different rotating parts as a parameter for mistuning natural frequencies. It is further worth noting that the system 1 can also be used to mistune cross-shaft resonances between the shaft 26 and another shaft. Stiffness ratio targets may be achieved by a control loop of the controller 44 using a displacement ratio of displacements (e.g. radially, axially and/or torsionally) measured by sensors 42 at two different positions (e.g., along the rotational axis 9).

[0083] In detail, the controller 44 may first define a mistuning target, e.g., multiple mode shapes. By this, a stiffness demand at several locations is calculated. Then, one or more stiffness ratios between the locations are calculated. The shaft 26 locations are measured at the sensor 42 locations. Ratios between the shaft locations at the sensor locations are calculated to identify the current mode. Optionally, a temperature correction is performed.

[0084] Further, more than one mode shape may be mistuned by the system 1 at the same time, e.g. a radial mode shape and a torsional mode shape.

[0085] It is worth noting that a damping is not the primary effect of the application of the system 1 in order to reduce vibration. Rather, the stiffness modification is the target, while damping is a secondary effect. Further, besides the conventional resonances, the system 1 can also be used to reduce rotor orbits/vibration due to gap-dependent forces. Also the monitoring of the gap dependent forces is possible.

[0086] FIG. 11 illustrates an example of transient residual oscillation in resonance. An additional improvement is possible by activating the corresponding active device 41A-41C (or active device arrangement) already before the resonance sets in, as illustrated in FIG. 11. Therefore, by analysis of the operating conditions, and the change of the operating conditions (e.g., speed and acceleration), the controller 44 predicts an approximate point in time at which a resonance will set in, and activates the corresponding active device(s) 41A-41C at a prior point in time tau. Here, the corresponding active device(s) 41A-41C are activated for a time period delta tau. The time period delta tau may be predetermined, or it may be calculated based on the operating conditions and their change.

[0087] It is worth noting that the active devices 41A-41C do not carry the shaft 26. The active devices 41A-41C may be switched off and the shaft 26 will be carried by its mechanical bearings 43.

[0088] Thus, with the system 1 it is possible to reduce the effects of a main source, and of several sources acting at the same time, of vibration without additional heavy dampers.

[0089] Further, in addition to reducing vibrations, the system 1 can be used to excite vibrations, e.g. to de-ice the shaft and/or blades mounted thereon, e.g., a fan, or the housing 45, e.g. a fan case. Other possible applications are to counteract a combustor rumble, and to generate static and modulated loads on a test article, for instance to simulate the effect of gap-dependent forces and vibration on a journal bearing under test on a full scale rig for rig testing.

[0090] It will be understood that the invention is not limited to the embodiments above-described and various modifications and improvements can be made without departing from the concepts described herein. Except where mutually exclusive, any of the features may be employed separately or in combination with any other features and the disclosure extends to and includes all combinations and sub-combinations of one or more features described herein.

LIST OF REFERENCE NUMBERS

[0091] 1 system [0092] 8 airplane [0093] 9 principal rotational axis [0094] 10 gas turbine engine [0095] 11 engine core [0096] 12 air intake [0097] 14 low-pressure compressor [0098] 15 high-pressure compressor [0099] 16 combustion equipment [0100] 17 high-pressure turbine [0101] 18 bypass exhaust nozzle [0102] 19 low-pressure turbine [0103] 20 core exhaust nozzle [0104] 21 nacelle [0105] 22 bypass duct [0106] 23 propulsive fan [0107] 24 stationary supporting structure [0108] 26 shaft [0109] 27 interconnecting shaft [0110] 28 sun gear [0111] 30 gearbox [0112] 32 planet gears [0113] 34 planet carrier [0114] 36 linkages [0115] 38 ring gear [0116] 40 linkages [0117] 41A-41C active device [0118] 42 sensor [0119] 43 bearing [0120] 44 controller [0121] 45 housing [0122] 46 rotor section [0123] 47 gearbox [0124] 48 reinforcement [0125] 49 coil [0126] 50 current supply [0127] A core airflow [0128] B bypass airflow [0129] M1-M10 mode shape