EP3976929A1 - Ensemble pour turbomachine - Google Patents
Ensemble pour turbomachineInfo
- Publication number
- EP3976929A1 EP3976929A1 EP20732122.5A EP20732122A EP3976929A1 EP 3976929 A1 EP3976929 A1 EP 3976929A1 EP 20732122 A EP20732122 A EP 20732122A EP 3976929 A1 EP3976929 A1 EP 3976929A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- bearing
- rotor
- assembly according
- assembly
- support part
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/16—Form or construction for counteracting blade vibration
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/04—Antivibration arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/04—Antivibration arrangements
- F01D25/06—Antivibration arrangements for preventing blade vibration
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/027—Arrangements for balancing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/10—Anti- vibration means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/662—Balancing of rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
Definitions
- the present invention relates to an assembly for a turbomachine.
- the invention more specifically relates to an assembly for a turbomachine comprising a damper.
- a turbomachine known from the state of the art comprises a casing and a fan capable of being rotated relative to the casing, about a longitudinal axis, by means of a fan shaft.
- the fan comprises a disc centered on the longitudinal axis, and a plurality of vanes distributed circumferentially at the outer part of the disc.
- the range of operation of the blower is limited. More precisely, the evolution of a fan compression ratio as a function of the air flow rate that it draws in when it is rotated is restricted to a predetermined range.
- the fan is in fact subjected to aeroelastic phenomena which destabilize it. Specifically, the air flowing through the running blower supplies energy to the blades, and the blades respond in their own modes at levels that may exceed the endurance limit of the material they are made of. This fluid-structure coupling therefore generates vibrational instabilities which accelerate the wear of the fan and reduce its life.
- shock absorbers have been described in documents FR 2 949 142, EP 1 985 810 and FR 2 923 557, in the name of the Applicant. These dampers are all configured to be housed between the platform and the root of each blade, within the housing delimited by the respective stilts of two successive blades. Moreover, such dampers operate during a relative movement between two successive blade platforms, by dissipation of the vibrational energy, for example by friction. Therefore, these shock absorbers are only attached to damping a first vibratory mode of the blades which characterizes a synchronous response of the blades to aerodynamic stresses. In this first vibratory mode, the inter-vane phase shift is non-zero.
- this second vibratory mode is coupled between the vanes, the disc, and the fan shaft.
- the amplitude of this second vibratory mode is all the more important as the blades are large.
- An object of the invention is to damp a mode of vibration of a rotor in which the phase shift between the blades of said rotor is zero.
- Another object of the invention is to influence the damping of vibration modes of a rotor in which the phase shift between the blades of said rotor is non-zero.
- Another aim of the invention is to provide a simple and easy to implement damping solution.
- an assembly for a turbomachine comprising:
- o including:
- a damper configured to damp a movement of the first rotor relative to the second rotor, in a plane orthogonal to the longitudinal axis, the movement being caused by a beating of at least one blade among the plurality of blades, the damper including: o a first support part:
- the second vibratory mode is characterized by a zero inter-vane phase shift. Therefore, placing a damper between two successive blades of a rotor, as has already been proposed in the prior art, has no effect on the second vibratory mode.
- the shock absorber disturbs the cause, that is, dampens the second vibratory mode.
- the first vibratory mode also participates in the displacement of the first rotor relative to the second rotor, in the plane orthogonal to the longitudinal axis. Therefore, by opposing this effect, the damper also contributes to disturbing another cause, that is, damping the first vibratory mode.
- the second support part improves the stability of
- the assembly according to the invention can further comprise one of the following characteristics, taken alone or in combination with one or more of the other of the following characteristics:
- the first support part has a radially outer surface coming into contact with a radially inner surface of the first rotor
- the third support part has a radially outer surface coming into contact with a radially inner surface of the second rotor
- the shock absorber includes a connecting part:
- the first bearing portion has a first bearing surface arranged to apply a first force on the second rotor, the first force having a first longitudinal component in a first direction parallel to the longitudinal axis, and a first radial component in a second direction orthogonal to the longitudinal axis, the first longitudinal component being greater than the first radial component
- the third bearing part has a second bearing surface arranged to apply a second force to the second rotor, the second force having a second
- a slot is provided in the first support part, the assembly further comprising a metal insert inserted into the slot, the second sacrificial plate being fixedly mounted on the metal insert,
- the second support part is configured to apply a third centrifugal force on the first rotor
- the second support part has a radially outer surface coming into contact with a radially inner surface of the first rotor
- the shock absorber includes:
- the third bearing zone extending over a third angular sector around the 'longitudinal axis, the third angular sector being smaller than the first angular sector
- each of the second bearing parts has a radially outer surface, coming into contact with a radially inner surface of the first rotor
- At least one of the second bearing parts comprises a portion thinned with respect to the rest of said second bearing part
- At least one of the second bearing parts comprises a groove configured to promote radial deformation of said second bearing part
- the second bearing parts form lateral sections extending on either side, in a circumferential direction, of the first bearing part
- each of the blades among the plurality of blades comprises:
- the second rotor comprises a ferrule, the ferrule comprising an extension
- the third bearing part resting on the circumferential extension.
- a turbomachine comprising an assembly as described above, and in which the first rotor is a fan, and the second rotor is a low pressure compressor.
- Figure 1 schematically illustrates a turbomachine
- FIG. 2 comprises a sectional view of part of a turbomachine, and a curve indicating a tangential displacement of various elements of this part of the turbomachine as a function of the position of said elements along a longitudinal axis of the turbomachine
- Figure 3 is a sectional view of part of an exemplary embodiment of an assembly according to the invention
- Figure 4 is a perspective view of part of an exemplary embodiment of an assembly according to the invention.
- Figure 5 is a perspective view of part of an exemplary embodiment of an assembly according to the invention.
- Figure 6 is a perspective view of a shock absorber of an exemplary embodiment of an assembly according to the invention.
- FIG. 7 is a perspective view of a damper of an exemplary embodiment of an assembly according to the invention.
- Figure 8 is a perspective view of a shock absorber of an exemplary embodiment of an assembly according to the invention.
- FIG. 9 is a perspective view of part of an exemplary embodiment of an assembly according to the invention.
- Figure 10 is a perspective view of part of an exemplary embodiment of an assembly according to the invention.
- Figure 11 is a perspective view of a shock absorber of an exemplary embodiment of an assembly according to the invention.
- Figure 12 is a perspective view of part of an exemplary embodiment of an assembly according to the invention.
- Figure 13 is a perspective view of part of an exemplary embodiment of an assembly according to the invention.
- Figure 14 is a perspective view of part of an exemplary embodiment of an assembly according to the invention.
- Figure 15 is a perspective view of a section of part of an exemplary embodiment of an assembly according to the invention.
- FIG. 16 is a perspective view in perspective of part of an exemplary embodiment of an assembly according to the invention
- FIG. 17 is a perspective view of part of an exemplary embodiment of an assembly according to the invention.
- a turbomachine 1 comprises a housing 10, a fan 12, a low pressure compressor 140, a high pressure compressor 142, a combustion chamber 16, a high pressure turbine 180 and a low pressure turbine 182.
- Each of the blower 12, the low pressure compressor 140, the high pressure compressor 142, the high pressure turbine 180, and the low pressure turbine 182, is rotatable relative to the housing 10 about a longitudinal axis X-X.
- the fan 12 and the low pressure compressor 140 are integral in rotation, and are capable of being rotated by a low pressure shaft 13 which is itself capable of being rotated by the low pressure turbine 182.
- the high pressure compressor 142 is itself capable of being rotated by a high pressure shaft 15, which is itself susceptible to rotation. to be rotated by the high pressure turbine 180.
- the blower 12 draws in an air flow 110 which separates between a secondary flow 112, circulating around the casing 10, and a primary flow 111, successively compressed within the low pressure compressor 140 and the high pressure compressor 142, ignited within the combustion chamber 16, then successively expanded within the high pressure turbine 180 and the low pressure turbine 182.
- Upstream and downstream are here defined relative to the direction of normal flow of air 110, 111, 112 through the turbomachine 1.
- an axial direction corresponds to the direction of the longitudinal axis XX
- a radial direction is a direction which is perpendicular to this longitudinal axis XX and which passes through said longitudinal axis XX
- a circumferential, or tangential direction corresponds to the direction of a flat and closed curved line, all the points of which are at equal distance from the longitudinal axis XX.
- the terms “internal (or internal)” and “external (or external)”, respectively, are used with reference to a radial direction such that the part or the internal face (ie radially internal) d an element is closer to the longitudinal axis XX than the part or the external face (ie radially external) of the same element.
- the fan 12 comprises a disc 120 and a plurality of vanes 122 distributed circumferentially at an outer part of the disc 120.
- each of the blades 122 of the plurality of blades 122 includes:
- the paddle wheel 1220 may be integral with the disc 120 when the blower 12 is a one-piece bladed disc. Alternatively, as shown in Figure 3, the paddle wheel 1220 can be configured to be housed in a recess 1200 of the disc 120 provided for this purpose.
- the low pressure compressor 140 also comprises a plurality of vanes 1400 fixedly mounted at an outer part of a ferrule 1402, said ferrule 1402 comprising a circumferential extension 1404 at the outer end from which radial sealing lips 1406 extend.
- the radial sealing wipers 1406 come opposite the platforms 1226 of the vanes 122 of the fan 12, so as to guarantee the internal sealing of the flow stream within which the primary flow 111 circulates.
- the shell 1402 of the low pressure compressor 140 is fixed to the disc 120 of the fan 12, for example by bolting.
- Each of the vanes 122 of the plurality of fan blades 122 12 is capable of beating, vibrating relative to the disc 120 during a rotation of the fan 12 relative to the housing 10. More precisely, during the coupling between the. air 110 circulating within the fan 12 and the profiled blades 1222, the blades 122 are the site of aeroelastic floating phenomena on different vibratory modes, and whose amplitude can be such that it exceeds the endurance limits of the materials constituting the fan 12. These vibratory modes are also coupled to the opposing forces of compression upstream of the turbomachine 1, and of expansion downstream of the latter.
- a first vibratory mode characterizes a synchronous response of the blades 122 to aerodynamic stresses, in which the inter-blade phase shift is non-zero.
- a second vibratory mode characterizes an asynchronous response of the blades 122 to aerodynamic stresses, in which the inter-blade phase shift is zero.
- the amplitude of the beats of the second vibratory mode is moreover as great as the blades 122 of the fan 12 are large.
- this second vibratory mode is coupled between the blades 122, the disc 120, and the fan shaft 13.
- the frequency of the second mode vibration is, moreover, one and a half times greater than that of the first vibratory mode.
- the second vibratory mode has a nodal deformation at mid-height of the blades 122 of fan 12.
- the The length of the vanes 122 of the fan 12 is greater than the length of the vanes 1400 of the low pressure compressor 140. Therefore, the tangential bending moment caused by the flapping of a vane 122 of the fan 12 is greater than the tangential bending moment driven by beats of a blade 1400 of the low pressure compressor 140.
- the blades of the blades 122 of the fan 12 and of the blades 1400 of the low pressure compressor 140 then have very different behaviors.
- the mounting stiffness within the fan 12 is different from the mounting stiffness within the low pressure compressor 140.
- the amplitude of this displacement for the second vibratory mode is for example between 0.01 and 0.09 millimeter, typically of the order of 0.06 millimeter, or, in another example, is of the order of a few tenths of a millimeter, for example 0.1 or 0.2 or 0.3 millimeter.
- a damper 2 is used to damp these vibrations from the fan 12 and / or the low pressure compressor 140.
- the damper 2 is in particular configured to damp a movement of the fan 12 relative to the low pressure compressor 140, in a plane orthogonal to the longitudinal axis XX, the movement being caused by a fluttering of at least one blade 122 among the plurality of blades 122 of the fan 12.
- the damper 2 comprises:
- the first bearing portion 21 has a radially outer surface, corresponding to the first bearing zone, coming into contact with a radially inner surface of the fan 12, typically a radially inner surface of the platform 1226.
- the second bearing zone extends over a second angular sector A2, A4 around the longitudinal axis X-X, the second angular sector A2, A4 being smaller than the first angular sector A1.
- All or part of the blades 122 of the fan 12 can moreover be equipped with such a damper 2, depending on the desired damping, but also the mounting and / or maintenance characteristics.
- the first support part 21 is fixedly mounted on the fan 12, for example by gluing. This facilitates the integration of the damper 2 within the turbomachine 1, and guarantees the support of the first bearing part 21 on the fan 12.
- the first angular sector A1 corresponds to the angular sector occupied by the platform 1226 of a blade 122 of the fan 12.
- the first bearing part 21 extends over the entire circumferential dimension of the blade. platform 1226 of vane 122, at the level of an internal surface of said platform 1226. The support of the damper 2 on the fan 12 is thus improved.
- the damper 2 comprises a material from the range having the trade name “SMACTANE® ST” and / or “SMACTANE® SP”, for example a material of the type “SMACTANE® ST 70” and / or “SMACTANE® SP 50”. It has in fact been observed that such materials exhibit suitable damping properties.
- the shock absorber 2 comprises a third support part 23:
- the third bearing portion 23 has a radially outer surface, coming into contact with a radially inner surface of the low pressure compressor 140, typically a radially inner surface of the circumferential extension 1404, for example a radially inner surface of sealing lips 1406.
- the third bearing part 23 bears on the low pressure compressor 140 in a third bearing zone extending over a third angular sector A3 around the longitudinal axis XX.
- the third support part 23 is fixedly mounted on the low pressure compressor 140, for example by gluing.
- the first support part 21 can then be mounted free to rub on the blower 12.
- the damper 2 further comprises a connecting part 20:
- the first bearing portion 21 has a first radial thickness E1 in a section plane which includes the longitudinal axis XX
- the third bearing part 23 has a third radial thickness E3 in the section plane
- the connecting part 20 has a radial connecting thickness E0 in the cutting plane.
- FIG. 3 provides an example of a view in such a section plane.
- the radial link thickness E0 is smaller than the first radial thickness E1 and than the third radial thickness E3.
- the connecting part 20 is therefore thinned in relation to the first support part 21 and to the third support part 23.
- the first support part 21 and the third support part 23 are massive. Consequently, in operation, each of the first bearing portion 21 and of the third bearing portion 23 exerts a respective centrifugal force C1, C2 on the fan 12 and the low pressure compressor 140, on which said bearing portions 21, 23 support.
- the bearing parts 21, 23 are each dynamically coupled respectively to the fan 12 and to the low pressure compressor 140 on which each bears, so as to undergo the same vibrations as each of the fan 12 and of the compressor. low pressure 140.
- the bearing parts 21, 23 are stiffer than the connecting part 20, in particular in a tangential direction.
- the third radial thickness E3 is greater than the first radial thickness E1, so as to better guarantee the support of the third support part 23.
- the thinner connecting part 20 is more flexible, in particular in a tangential direction. It therefore allows the blower 12 to transmit the vibrations to which it is subject to the low pressure compressor 140 and, conversely, it allows the low pressure compressor 140 to transmit the vibrations to which it is subject to the blower 12. Indeed, for frequencies high vibration, damping is provided in particular by the shear work of the connecting part 20, that is to say by viscoelastic dissipation For low vibratory frequencies, the damping is provided in particular by friction of one or the other of the first support part 21 or of the third support part 23 respectively against the fan 12 or against the low compressor pressure 140.
- the third bearing portion 23 comes to bear on the circumferential extension 1404 of the shell 1402 of the low pressure compressor 140, at the level of an internal surface of the radial sealing wipers 1406. Indeed, it is in this position that the displacement of the fan 12 relative to the low pressure compressor 140, in the plane orthogonal to the longitudinal axis XX, is of greater amplitude, typically a few millimeters. Therefore, the damper 2 is particularly effective there.
- the damper 2 is particularly effective there.
- the thinning of the connecting portion 20 provides clearance which allows the shock absorber 2 to avoid rubbing on a corner of the radial sealing wipers 1406.
- the second bearing portion 22, 24 is configured to apply a third centrifugal force C3, C4 on the fan 12.
- the second bearing part 22, 24 has a radially outer surface coming into contact with a radially inner surface of the fan 12.
- the second bearing part 22 further bears on a downstream surface of the fan. stilts 1224 of the blade 122, as visible in Figures 4 and 5.
- the second bearing portion 22, 24 comes to rest under the platform 1226 of a blade 122 of the fan 12, at an internal surface of the platform 1226.
- a sacrificial plate 230 bears on the low pressure compressor 140.
- the sacrificial plate 230 is fixedly mounted on the third bearing part 23, for example by gluing, and / or by being housed within a groove 2300 of the third bearing part 23 provided for this purpose, as visible in FIG. 6.
- the sacrificial plate 230 is configured to guarantee the bearing of the third bearing part 23 on the low-pressure compressor 140.
- the mechanical stresses in operation are such that slight tangential, axial and radial movements of the damper 2 are to be expected. These movements are due in particular to the vibrations to be damped, but also to the centrifugal loading of the damper 2. It is necessary that these movements do not wear out the low pressure compressor 140.
- the sacrificial plate 230 comprises an anti- wear, for example of the Teflon type and / or any type of composite material.
- the sacrificial wafer 230 is further treated by dry lubrication, in order to perpetuate the value of the coefficient of friction between the damper 2 and the low pressure compressor 140.
- This material with lubricating properties is for example of the type MoS2.
- the sacrificial wafer 230 can also include a coating additional, configured to reduce the friction and / or wear of the low pressure compressor 140.
- This additional coating is fixedly mounted on the sacrificial plate 230, for example by gluing.
- the additional coating is of the dissipative and / or viscoelastic and / or damping type. It can in fact comprise a material from the range having the trade name “SMACTANE® ST” and / or “SMACTANE® SP”, for example a material of the “SMACTANE® ST 70” and / or “SMACTANE® SP 50” type. .
- the additional coating material advantageously has a coefficient of friction of between 0.3 and 0.07.
- the sacrificial plate 230 is optionally combined by juxtaposition with its additional coating.
- the first bearing part 21 has a first bearing surface 2100 arranged to apply a first force F1 on the low pressure compressor 140, the first force F1 having a first longitudinal component F1 L in a first direction parallel to the axis longitudinal XX, and a first radial component F1 R in a second direction orthogonal to the longitudinal axis XX, the first longitudinal component F1 L being greater than the first radial component F1 R,
- the third bearing portion 23 has a second bearing surface 2320 arranged to apply a second force F2 on the low pressure compressor 140, the second force F2 having a second longitudinal component F2L in the first direction, and a second radial component F2R in the second direction, the second radial component F2R being greater than the second longitudinal component F2L.
- the first bearing surface 2100 provides the axially positioned support of the damper 2 since it is a downstream axial surface of the damper 2 coming into contact with an upstream axial surface. of the low-pressure compressor 140.
- the second bearing surface 2320 provides the radially positioned support of the damper 2 since it is a radially outer surface of the damper 2 coming into contact with a radially internal surface of the low pressure compressor 140.
- the second bearing surface 2320 participates in the application of the second centrifugal force C2 on the low pressure compressor 140.
- a first sacrificial plate 210 is fixedly mounted on the first support part 21, for example by gluing, and has the first support surface 2100, and
- a second sacrificial plate 232 is fixedly mounted on the third bearing part 23, for example by gluing, and has the second bearing surface 2320.
- the first sacrificial wafer 210 and the second sacrificial wafer 232 advantageously have the same characteristics as those described with reference to the sacrificial wafer 230 of the embodiment illustrated in FIG. 6, with the same benefits for the damping of a displacement of the fan. 12 relative to the low pressure compressor 140, in the plane orthogonal to the longitudinal axis XX.
- a slot 213 is formed in the first bearing part 21, a metal insert 233 being inserted into the slot 213, the second sacrificial plate 232 being fixedly mounted on the insert metallic 233, for example by gluing.
- the metal insert 233 makes it possible to stiffen the shock absorber 2.
- the metal insert 233 facilitates the deformation of the first sacrificial plate 210 and of the second sacrificial plate 232.
- a weight 3 is fixedly mounted on the damper 2, for example by gluing.
- the weight 3 makes it possible to adjust the centrifugal forces C1, C2, C3, C4 exerted by the damper 2 on the fan 12 and on the low pressure compressor 140, so as to improve the dynamic coupling between the first support part 21 and the fan 12, and between the third bearing part 23 and the low pressure compressor 140.
- the weight 3 comprises an elastomeric material. Referring to Figure 9, the weight 3 can then be mounted fixed both on the first support part 21 and on the third support part 23, for example by gluing.
- the weight 3 is mounted fixedly on the first bearing part 21, for example by gluing, preferably only on the first bearing part 21.
- the weight is shifted upstream of the first bearing part 21, so as to leave the connecting part 20 free so that, in operation, it can work effectively in shear to damp a movement of the fan 12 by relative to the low pressure compressor 140, in a plane orthogonal to the longitudinal axis XX.
- the weight 3 is fixedly mounted on the third bearing part 23, for example by gluing, preferably only on the third bearing part 23.
- the weight 3 is offset downstream from the third bearing portion 23.
- the weight 3 is mounted fixed only on the first support part 21 if the third support part 23 is fixedly mounted on the low pressure compressor 140.
- a second flyweight 32 is fixedly mounted on the third support part 23.
- the damper 2 comprises:
- the second bearing zone o resting on the fan 12 in a second bearing zone, different from the first bearing zone, the second bearing zone extending over a second angular sector A2 around the longitudinal axis XX, the second angular sector A2 being smaller than the first angular sector A1, and
- the third bearing zone extending over a third angular sector A4 around the longitudinal axis XX, the third angular sector A4 being smaller than the first angular sector A1, and
- each of the second bearing parts 22, 24 has a radially external surface, coming into contact with a radially internal surface of the fan 12, typically a radially internal surface of the 1226 platform.
- the two second bearing portions 22, 24 form lateral sections extending on either side, in a circumferential direction, of the first bearing portion 21.
- the two second bearing parts 22, 24 promote coupling with the fan 12, and the damping of a displacement of the fan 12 relative to the low pressure compressor 140, by increasing the overall stiffness of the first bearing part 21
- the rigidity of the first bearing part 21 is increased at its circumferential ends. The damping of the damper 2, in particular in a tangential direction, is then generally improved.
- At least one of the first bearing portion 21 and the two second bearing portions 22, 24, is mounted fixedly on the blower 12, for example by gluing. This facilitates the integration of the shock absorber 2 within the turbomachine 1, and guarantees the support of said bearing parts 21, 22, 24 on the fan 12.
- each of the first bearing portion 21, and of the two second bearing portions 22, 24 bears on the blade platform 122 of the fan 12, at an internal surface of the 1226 platform.
- At least one of the two second bearing zones 22, 24 extends along an entire axial length of the platform 1226.
- at least one of the two second parts 22, 24 extends all along the platform 1226.
- at least one of the two second parts of support 22, 24 is flush with an edge of the platform 1226.
- a radial surface of the platform 1226 at a circumferential end of said platform 1226 is extended by a radial surface of the second support portion 22, 24 at a circumferential end of said second bearing part 22, 24 which corresponds to the circumferential end of the platform 1226.
- the second bearing parts 22, 24 of shock absorbers 2 circumferentially adjacent to the breast of the blower 12 come in ap then against each other. This participates in the damping by friction of the vibrations of the fan 12.
- these supports of the second bearing parts 22, 24 of shock absorbers 2 circumferentially adjacent to one another improve the sealing of the flow stream d. 'air 110.
- only one of the second bearing parts 22, 24 extends all along the platform 1226, flush with one edge of the platform 1226, while the other of the second bearing portions 22, 24 extends only along a portion of the platform 1226.
- the second bearing portion 22, 24 which is the longest axially participates in the sealing while the other participates more in damping.
- At least one of the second bearing portions 22, 24 comprises a portion thinned with respect to the rest of said second bearing portion 22, 24 More precisely, as visible in FIG. 15, a first circumferential thickness e1 of the second support part 22, 24 is different from a second circumferential thickness e2 of the second support part 22 24, said second circumferential thickness e2 being taken at a radial position different from a radial position of the first circumferential thickness e1.
- at least one of the second bearing parts 22, 24 is thicker at the level of an internal surface of the platform 1226 than at a distance from the internal surface distance of the platform. 1226.
- first circumferential thickness e1 facilitates the holding, for example by gluing, of the second bearing part 22, 24 on the internal surface of the platform 1226.
- second circumferential thickness e2 improves the seal between the second circumferentially adjacent bearing parts 22, 24.
- At least one of the second bearing parts 22, 24 comprises a groove 241.
- the groove 241 is configured to promote radial deformation of said second bearing portion 22, 24 during the application of the corresponding centrifugal force C3, C4. This promotes in particular the sealing between the platforms 1226 of the successive blades 122 of the fan 12.
- the bearing parts 21, 22, 23, 24 are massive. Consequently, in operation, each of said bearing parts 21, 22, 23, 24 exerts a respective centrifugal force C1, C2, C3, C4 on the fan 12 and the low pressure compressor 140, on which said bearing parts 21 , 22, 23, 24 support.
- the bearing parts 21, 22, 23, 24 are indeed each dynamically coupled respectively to the fan 12 and to the low-pressure compressor 140 on which each bears, so as to undergo the same vibrations as each of the blower 12 and low-pressure compressor 140.
- the damper 2 comprises a connecting part 20
- the bearing parts 21, 22, 23, 24 are stiffer than the part. link 20, in particular in a tangential direction.
- the damper 2 is configured to damp a displacement of the fan 12 relative to the low pressure compressor 140, in the plane orthogonal to the longitudinal axis X-X.
- the damper 2 is also configured to damp a displacement of any first rotor 12 relative to any second rotor 140, in a plane orthogonal to the longitudinal axis XX, as long as the first rotor 12 is movable in rotation relative to the housing 10 about the longitudinal axis XX and comprises a disc 120 as well as a plurality of blades 122 capable of beating while vibrating relative to the disc 120 during a rotation of the first rotor 12 relative to the housing 10, and that the second rotor 140 is also movable in rotation relative to the housing 10 about the longitudinal axis XX.
- the first rotor 12 can be a first stage of the high pressure compressor 142 or of the low pressure compressor 140, and the second rotor 140 be a second stage of said compressor 140, 142, successive to the first stage of compressor 140, 142, upstream or downstream of the latter.
- the first rotor 12 can be a first stage of high pressure turbine 180 or low pressure turbine 182, and the second rotor 140 being a second stage of said turbine 180, 182, successive to the first turbine stage 180, 182, upstream or downstream of the latter.
- the shock absorber 2 has a small footprint. Therefore, it can easily be integrated into existing turbomachines.
- the damper 2 provides significant tangential stiffness between the first rotor 12 and the second. rotor 140. It thus differs from an excessively flexible damper which would only come to deform during a displacement of the first rotor 12 relative to the second rotor 140, in the plane orthogonal to the longitudinal axis XX. On the contrary, shock absorber 2 dissipates such a displacement:
- the shock absorber 2 remains flexible enough to maximize the contact surfaces between said shock absorber 2 and the rotors 12, 140 on which it bears. To do this, the shock absorber 2 has a tangential rigidity greater than an axial rigidity and a radial rigidity.
- the contact forces between the damper 2 and the rotors 12, 140 can in particular be adjusted by means of weights 3 and / or sacrificial plates 230, 210, 232 and / or additional coatings on said sacrificial plates 230, 210, 232 At low frequencies, it is in fact necessary to ensure that the centrifugal forces C1, C2, C3, C4 exerted by the damper 2 on the rotors 12, 140 are not too great, in order to guarantee that the damper 2 can oscillate between a stuck state and a sliding state on the rotors 12, 140, and thus damping by friction.
- the wear of the rotors 12, 140 is in particular limited by treating the surfaces of
- damper 2 resting on the rotors 12, 140, for example to provide them with a coating with a low coefficient of friction.
Abstract
Description
Claims
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1905733A FR3096729B1 (fr) | 2019-05-29 | 2019-05-29 | Ensemble pour turbomachine |
FR1905755A FR3096733B1 (fr) | 2019-05-29 | 2019-05-29 | Ensemble pour turbomachine |
PCT/EP2020/064645 WO2020239803A1 (fr) | 2019-05-29 | 2020-05-27 | Ensemble pour turbomachine |
Publications (1)
Publication Number | Publication Date |
---|---|
EP3976929A1 true EP3976929A1 (fr) | 2022-04-06 |
Family
ID=71083583
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP20732122.5A Pending EP3976929A1 (fr) | 2019-05-29 | 2020-05-27 | Ensemble pour turbomachine |
Country Status (4)
Country | Link |
---|---|
US (1) | US11828191B2 (fr) |
EP (1) | EP3976929A1 (fr) |
CN (1) | CN114080490A (fr) |
WO (1) | WO2020239803A1 (fr) |
Family Cites Families (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2517779B1 (fr) * | 1981-12-03 | 1986-06-13 | Snecma | Dispositif d'amortissement des aubes d'une soufflante de turbomachine |
FR2585069B1 (fr) * | 1985-07-16 | 1989-06-09 | Snecma | Dispositif de limitation du debattement angulaire d'aubes montees sur un disque de rotor de turbomachine |
US5156528A (en) * | 1991-04-19 | 1992-10-20 | General Electric Company | Vibration damping of gas turbine engine buckets |
US5820346A (en) * | 1996-12-17 | 1998-10-13 | General Electric Company | Blade damper for a turbine engine |
GB0109033D0 (en) * | 2001-04-10 | 2001-05-30 | Rolls Royce Plc | Vibration damping |
FR2896289B1 (fr) * | 2006-01-13 | 2008-03-28 | Snecma Sa | Masselotte d'equilibrage, disque de rotor en etant equipe, rotor et moteur d'aeronef les comportant |
EP1925781A1 (fr) * | 2006-11-23 | 2008-05-28 | Siemens Aktiengesellschaft | Agencement d'aubes |
FR2915510B1 (fr) | 2007-04-27 | 2009-11-06 | Snecma Sa | Amortisseur pour aubes de turbomachines |
US8182228B2 (en) * | 2007-08-16 | 2012-05-22 | General Electric Company | Turbine blade having midspan shroud with recessed wear pad and methods for manufacture |
FR2923557B1 (fr) * | 2007-11-12 | 2010-01-22 | Snecma | Ensemble d'une aube de soufflante et de son amortisseur, amortisseur d'aube de soufflante et methode de calibrage de l'amortisseur |
GB0814018D0 (en) * | 2008-08-01 | 2008-09-10 | Rolls Royce Plc | Vibration damper |
FR2949142B1 (fr) * | 2009-08-11 | 2011-10-14 | Snecma | Cale amortisseuse de vibrations pour aube de soufflante |
FR2970033B1 (fr) | 2011-01-04 | 2015-10-16 | Turbomeca | Procede d'amortissement de pale de turbine a gaz et amortisseur de vibration de mise en oeuvre |
CN103982250B (zh) * | 2014-05-12 | 2015-07-22 | 天津大学 | 具有冷却功能的金属橡胶减振器 |
CN204312143U (zh) * | 2014-11-14 | 2015-05-06 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | 一种涡轮叶片振动阻尼器装置 |
CN104329123B (zh) * | 2014-11-28 | 2015-11-11 | 哈尔滨广瀚燃气轮机有限公司 | 涡轮机动叶与轮盘固定结构 |
CN105156155B (zh) * | 2015-07-06 | 2017-06-06 | 西安交通大学 | 一种动叶片叶根平台减振承压阻尼结构 |
US10584597B2 (en) * | 2015-09-03 | 2020-03-10 | General Electric Company | Variable cross-section damper pin for a turbine blade |
CN204941612U (zh) * | 2015-09-16 | 2016-01-06 | 中国航空工业集团公司沈阳发动机设计研究所 | 一种可压缩阻尼块 |
FR3047512B1 (fr) | 2016-02-05 | 2019-11-15 | Safran Aircraft Engines | Dispositif d'amortissement de vibrations pour aubes de turbomachine |
CN106593545A (zh) * | 2017-01-23 | 2017-04-26 | 中国航发沈阳发动机研究所 | 一种涡轮转子叶片缘板封严结构及具有其的发动机 |
-
2020
- 2020-05-27 EP EP20732122.5A patent/EP3976929A1/fr active Pending
- 2020-05-27 US US17/614,226 patent/US11828191B2/en active Active
- 2020-05-27 WO PCT/EP2020/064645 patent/WO2020239803A1/fr unknown
- 2020-05-27 CN CN202080047903.9A patent/CN114080490A/zh active Pending
Also Published As
Publication number | Publication date |
---|---|
US11828191B2 (en) | 2023-11-28 |
WO2020239803A1 (fr) | 2020-12-03 |
CN114080490A (zh) | 2022-02-22 |
US20220228491A1 (en) | 2022-07-21 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP3724455B1 (fr) | Dispositif amortisseur | |
CA2842088C (fr) | Roue a aubes de turbomachine | |
CA2931768C (fr) | Soufflante, en particulier pour une turbomachine | |
CA2860540C (fr) | Secteur angulaire de redresseur a amortissement de vibrations par coin pour compresseur de turbomachine | |
CA2635002A1 (fr) | Roue mobile pour un turboreacteur et turboreacteur la comportant | |
FR3075284A1 (fr) | Dispositif amortisseur | |
FR2927357A1 (fr) | Dispositif d'amortissement des vibrations entre deux aubes de roue aubagee de turbomachine | |
EP3976926B1 (fr) | Ensemble pour turbomachine avec amortisseur | |
CA2977896C (fr) | Disque aubage monobloc comportant un moyeu ayant une face evidee a laquelle est rapporte un organe de comblement | |
EP3976929A1 (fr) | Ensemble pour turbomachine | |
FR3075253B1 (fr) | Dispositif amortisseur | |
EP3976928B1 (fr) | Ensemble pour turbomachine et turbomachine | |
FR3096733A1 (fr) | Ensemble pour turbomachine | |
FR3096732A1 (fr) | Ensemble pour turbomachine | |
FR3096729A1 (fr) | Ensemble pour turbomachine | |
EP3728794B1 (fr) | Dispositif amortisseur | |
EP3935265B1 (fr) | Rotor de turbomachine d'aéronef comprenant un dispositif d'amortissement | |
FR3096730A1 (fr) | Ensemble pour turbomachine | |
FR3075283B1 (fr) | Dispositif amortisseur | |
FR2712631A1 (fr) | Ailette de rotor et ensemble ailettes-disque de rotor comportant une telle ailette. | |
FR3075254B1 (fr) | Dispositif amortisseur | |
FR2962481A1 (fr) | Amortisseur de vibrations a bras de levier pour aube d'un rotor de moteur a turbine a gaz | |
FR3106615A1 (fr) | Ensemble pour turbomachine | |
WO2022079360A1 (fr) | Ensemble d'attache pour une aube de turbomachine | |
FR3099213A1 (fr) | Rotor de soufflante pour une turbomachine d’aeronef |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: UNKNOWN |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE |
|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE |
|
17P | Request for examination filed |
Effective date: 20211224 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
DAV | Request for validation of the european patent (deleted) | ||
DAX | Request for extension of the european patent (deleted) | ||
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: EXAMINATION IS IN PROGRESS |
|
17Q | First examination report despatched |
Effective date: 20230509 |