EP3097266B1 - Organe mobile de turbomachine qui comporte des moyens pour changer sa fréquence de résonance - Google Patents

Organe mobile de turbomachine qui comporte des moyens pour changer sa fréquence de résonance Download PDF

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Publication number
EP3097266B1
EP3097266B1 EP15704057.7A EP15704057A EP3097266B1 EP 3097266 B1 EP3097266 B1 EP 3097266B1 EP 15704057 A EP15704057 A EP 15704057A EP 3097266 B1 EP3097266 B1 EP 3097266B1
Authority
EP
European Patent Office
Prior art keywords
rotor
speed
rotational speed
critical speed
critical
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.)
Active
Application number
EP15704057.7A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3097266A1 (fr
Inventor
Julien Michel Patrick Christian AUSTRUY
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Services SA
SNECMA SAS
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by SNECMA Services SA, SNECMA SAS filed Critical SNECMA Services SA
Publication of EP3097266A1 publication Critical patent/EP3097266A1/fr
Application granted granted Critical
Publication of EP3097266B1 publication Critical patent/EP3097266B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/10—Anti- vibration means
    • 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
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • 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
    • F05D2240/24—Rotors for 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
    • F05D2240/00—Components
    • F05D2240/50—Bearings
    • 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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity

Definitions

  • the invention proposes an aircraft turbomachine rotor which comprises means for modifying its critical speed, as a function of the operating conditions of the turbomachine.
  • the critical speed is defined as the coincidence between the rotational and resonant frequencies of the rotor.
  • a movable turbomachine member such as a turbomachine rotor, has a critical speed of its own. When the rotor rotates at a speed of rotation very close to this critical speed, the vibrations of the rotor are amplified, which affects the efficiency of the turbomachine.
  • the document US 2005/152626 discloses a device for modifying the critical speed of a rotor guide bearing support having two mechanical structures bearing different stiffnesses combined to carry the bearing, whose resonance frequencies are distinct.
  • the support also comprises means for modifying the angular position of the structures relative to one another so that the critical speed of the support is equal to one or the other of two critical speeds of the structures.
  • the object of the invention is to propose a rotor which is able to rotate at a speed of rotation which is always different from the critical speed of the rotor.
  • the modification of the critical speed of the rotor of the turbomachine, in operation, makes it possible to switch from one critical speed to another, when the rotational speed of the rotor is approaching one of the critical speeds.
  • the component consists of an inverted flexible cage type system, whether or not providing flexibility to the means for modifying the critical speed of the rotor according to whether it is in one or the other of its two operating states.
  • the drive means comprise at least one actuating member which is movably mounted and is able to move radially by centrifugal action when the rotational speed of the rotor is greater than said predefined rotation speed.
  • the drive means comprise an insert movable along the main axis of the rotor and which is able to be coupled with the component to change the state of the component.
  • the drive means comprise means for transforming the radial displacement of the actuating member into an axial displacement of the insert.
  • the means for transforming the radial displacement of the actuating member comprise two portions of revolution facing each other and movable relative to one another, between which the actuating member is arranged and the bearing faces vis-à-vis the portions of revolution are inclined relative to each other.
  • the drive means comprise elastic means for driving the insert to a position corresponding to the state of the component associated with a critical speed of the rotor less than the predefined rotational speed.
  • the drive means comprise a radial main orientation wall which is axially convex, which is connected to the insert, and said wall curved is elastically deformable and is able to occupy two stable shapes distributed on each side of a radial plane passing through a radially outer edge of the curved wall.
  • the means for changing the critical speed of the rotor are made so as to reduce the critical speed of the rotor when the rotation speed of the rotor is greater than the predefined rotation speed and so as to increase the critical speed of the rotor when the rotational speed of the rotor is lower than the predefined rotation speed.
  • the invention also proposes an aircraft turbomachine comprising a rotor according to the invention, which is provided with means able to change the critical speed of the rotor when the rotational speed of the rotor is greater or less than a predefined rotational speed.
  • figure 1 a portion of an aircraft turbine engine rotor 10 such as a turboprop.
  • the invention is not limited to a rotor 10 and that the invention can also be applied to another component of the turbomachine which is rotatable, such as for example a power transmission shaft.
  • the rotor 10 comprises a shaft 12 mounted to rotate with respect to the stator (not shown) of the turbomachine about the main axis A of the rotor 10.
  • the shaft 12 carries a plurality of components (not shown) of the rotor 10 such as for example compressor blades or turbine blades.
  • the rotor 10 and the shaft 12 vibrate at a frequency corresponding to the speed of rotation.
  • the amplitude of these vibrations of the rotor 10 and of the shaft 12 depends on the speed of rotation of the rotor 10.
  • the amplitude of the vibrations increases as the speed of rotation of the rotor 10 approaches a critical speed of the rotor.
  • the critical speed is defined as the coincidence between the rotational and resonant frequencies of the rotor.
  • This critical speed of the rotor 10 depends on the design of the turbomachine, it depends in particular on the mass of the components of the rotor 10, as well as the position of the guide surfaces of the shaft 12 in rotation in the stator.
  • the vibrations of the rotor 10 have a large amplitude which can damage the rotor 10 or the stator.
  • the rotor comprises means 14 making it possible to modify the critical speed of the rotor 10 when the speed of rotation of the rotor 10 approaches the critical speed of the rotor 10.
  • the means 14 for modifying the critical speed of the rotor 10 are made so as to change the critical speed of the rotor 10 in a manner that is almost instantaneous, when the speed of rotation of the rotor becomes greater than a predefined rotational speed or when the speed of rotation of the rotor 10 becomes lower than the predefined rotation speed.
  • the means 14 for modifying the critical speed then form a so-called "bistable" system, capable of occupying two stable operating states, each stable operating state being associated with a range of rotational speed of the rotor 10 greater or less than the speed predefined rotation.
  • This predefined rotation speed is between a first so-called lower critical speed, which is the critical speed of the rotor 10 when the means 14 for modifying the critical speed are in a first state, and a second so-called higher critical speed, which is the critical speed of the rotor 10 when the means 14 for modifying the critical speed are in their second state.
  • the means 14 for modifying the critical speed are designed so that when the rotor 10 rotates at a speed lower than the predefined speed of rotation, the means 14 for modifying the critical speed are in their second state, the critical speed of the rotor 10 is then the higher critical speed. The rotation speed of the rotor 10 is then always lower than the higher critical speed defined above.
  • the critical speed of the rotor 10 is then the lower critical speed.
  • the rotational speed of the rotor 10 is then always higher than its lower critical speed defined above.
  • the rotor 10 can not reach a rotational speed corresponding to its critical speed.
  • the means 14 for modifying the critical speed comprise a component 16 whose state varies according to whether the means 14 for modifying the critical speed are in their first state or in their second state.
  • the component 16 is an inverted flexible cage type system, that is to say that the flexible cage is coupled to the rotor 10.
  • the flexible cage is coupled to the stator.
  • the change of state of the flexible cage 16 is achieved by coupling it or not with an insert 40.
  • the insert 40 consists of a member integral with the rotor 10, which is axially movable relative to the rotor 10 and relative to the flexible cage 16 between a coupling position with the flexible cage 16 represented at figures 1 and 2 , and a position of non-coupling with the flexible cage 16.
  • the flexible cage 16 is designed so that when it is coupled with the insert 40, forces between the rotor 10 and the stator are transmitted at the level of the flexible cage by the flexible cage 16 and guide surfaces of the rotor 10 These two paths of effort create a stiffness of the flexible cage 16, which gives the rotor 10 its critical speed higher or lower.
  • the means 14 for modifying the critical speed are in their first state.
  • the flexible cage 16 is integral with the shaft 12, it is for example fixed to the shaft 12 by welding.
  • the means 14 for modifying the critical speed of the rotor 10 comprise a device 18 for driving the insert 40, which causes the displacement of the insert 40 between a coupling position with the flexible cage 16 and a position in which the The insert is not coupled with the flexible cage 16 when the rotational speed of the rotor 10 becomes greater or less than the predefined rotational speed.
  • the drive device 18 of the insert 40 causes the displacement of the insert 40 under the effect of the centrifugal action.
  • the drive device 18 is not connected to any control device, which makes it possible to simplify the integration of the means 14 to modify the critical speed of the rotor 10.
  • the drive device 18 comprises a cage 20 which is mounted on the shaft 12, and a cylindrical sleeve 22 which is connected to the insert 40.
  • the cylindrical sleeve 22 is mounted to move relative to the cage 20 in translation along the main axis A of the rotor 10.
  • the cage 20 and the sleeve 22 are integral with the shaft 12 in rotation and they are traversed by the axis 12.
  • the cylindrical sleeve 22 is able to occupy, with respect to the cage 20, a first position represented in FIG. figure 2 corresponding to the coupling position of the insert 40 with the flexible cage 16 and a second position shown in FIG. figure 3 , corresponding to the position in which the insert 40 is not coupled with the flexible cage 16.
  • the guiding of the cylindrical sleeve 22 in displacement relative to the cage 20 is carried out by a first bearing surface 24 integral with the cage 20.
  • the first surface 24 is connected to the rest of the cage 20 via a wall 34 which extends in a radial plane with respect to the axis A.
  • the means 14 for modifying the critical speed of the rotor 10 have a bistable character, that is to say that they have two stable operating positions.
  • the transition between each of the two stable operating positions of the means 14 for modifying the critical speed is performed by means for driving the cylindrical sleeve 22, which change the position of the sleeve 22 when the speed of rotation of the rotor 10 becomes greater or lower than the preset speed.
  • the bistable character of the means 14 for modifying the critical speed of the rotor 10 is furthermore reinforced by a wall 38 of the cage 20 which is axially curved and which is connected at its center to the cylindrical sleeve 22 via a second bearing. 26.
  • the second bearing surface 26 is integral with the cylindrical sleeve 22 in translation axially and the wall 38 is able to deform elastically during the axial displacement of its center.
  • the wall 38 is able to occupy only two stable shapes represented by Figures 2 and 3 , which are distributed on each side of a radial plane passing through the radially outer edge of the wall 38. In each of these stable shapes, the wall 38 is axially convex in one direction or the other.
  • the wall 38 causes the cylindrical sleeve 22 to move very rapidly towards one of its two positions, so that the sleeve 22, and consequently the insert 40, remain very briefly in an intermediate axial position.
  • the curved wall 38 gives the means 14 for modifying the critical speed of the rotor 10 a discontinuous character.
  • the actuating device 18 is designed to drive the cylindrical sleeve 22 in axial displacement so that the second span 26 crosses this hard point when the rotational speed of the rotor 10 becomes equal to the predefined rotation speed for which the means 14 for change the critical speed of the rotor 10 change state.
  • the securing means of the second bearing 26 with the cylindrical sleeve 22, in axial displacement relative to the cage 20 comprise a shoulder 28 of the cylindrical sleeve 22 which is supported in a first direction, here to the left, against an axial end opposite the second bearing 26.
  • the shoulder 28 is here located at one end 22a of the cylindrical sleeve located closest to the component 16.
  • the securing means of the second bearing surface 26 with the cylindrical sleeve 22 also comprise elastic means which constantly exert a bearing force of the second bearing surface 26 against the shoulder 28 in the second direction, that is to say here to the right.
  • These elastic means 30 also exert a permanent drive action of the second bearing 26 towards the stable position of the curved wall 38 shown in FIGS. figures 1 and 2 , corresponding to the second state of the means 14 for modifying the critical speed of the rotor 10, for which the critical speed of the rotor 10 is the higher critical speed.
  • the elastic means 30 consist of a compression spring which is compressed between the two bearing surfaces 24, 26.
  • the actuating device 18 comprises means for driving the cylindrical sleeve 22 in axial displacement towards its second position shown in FIG. figure 3 when the rotational speed of the rotor 10 becomes greater than the predefined speed, corresponding to the first state of the means 14 for changing the critical speed of the rotor 10, for which the critical speed of the rotor 10 is the lower critical speed.
  • These drive means are of the centrifugal effect type, that is to say that they comprise at least one element 32 movable radially with respect to the axis A, which moves radially away from the axis A as the speed of rotation of the rotor 10 increases, by centrifugal effect.
  • the drive means comprise several moving elements 32, which consist of balls interposed axially between the radial wall 34 which carries the first bearing surface 24, and a portion of revolution 36 carried by the second end 22b of the cylindrical sleeve 22.
  • This portion of revolution 36 extends radially outwardly from the second end 22b of the cylindrical sleeve 22 and has a bearing face 36a located opposite a support face 34a of the radial wall 34 which carries the first bearing surface 24, on which the balls 32 bear axially.
  • the facing faces 36a, 34a of the revolution portion 36 and of the radial wall 34 are inclined with respect to each other, that is to say that at least one of these two bearing faces 36a, 34a is of conical shape, and the distance between the bearing faces 36a, 34a decreases away from the main axis A.
  • the cylindrical sleeve 22 drives the second bearing 26 and causes the elastic deformation of the curved wall 38.
  • the angle defined by the bearing faces 34a, 36a, the dimensions and the mass of the balls 32, as well as the dimensions of the spring 30 are defined according to the predefined rotational speed.
  • the curved wall 38 When the curved wall 38 changes state, the elastic return force it exerts changes direction, the curved wall 38 then cooperates with the centrifugal drive means to drive the cylindrical sleeve 22, against the return force exerted by the spring 30.
  • the cylindrical sleeve 22 is driven towards its second position for which the insert 40 is not coupled with the flexible cage 16 which is in its state with games.
  • the means 14 for modifying the critical speed are in their first state, associated with the low critical speed of the rotor 10.
  • the rotor 10 rotates at a speed greater than the critical speed of the rotor 10.
  • the cylindrical sleeve 22 is driven towards its position. for which the insert 40 is coupled with the flexible cage 16 which is in its state without games.
  • the means 14 for modifying the critical speed are in their second state, associated with the higher critical speed of the rotor 10.
  • the rotor 10 rotates at a speed of rotation lower than the critical speed of the rotor 10.
  • centrifugal action drive means with the rapid deformation of the convex wall 38 makes it possible to rapidly drive the cylindrical sleeve 22 towards its position shown in FIG. figure 3 . This therefore allows for a rapid withdrawal of the insert 40 from the flexible cage 16, to change the critical speed of the rotor 10.
  • the rotor 10 also contains guide bearings 42, which are here three in number, and which rotate the shaft 12, means 14 to change the critical speed of the rotor 10, and the flexible cage 16 .
  • a first bearing 42 is arranged at an upstream portion of the shaft 12, according to the flow direction of the gas in the turbomachine, here on the right side of the figures. This first bearing 42 is located at the inlet casing of the turbomachine.
  • the two other bearings 42 are arranged on either side of a low-pressure turbine of the turbomachine.
  • the second bearing 42 which is arranged at a downstream portion of the shaft 12. Is connected to an exhaust casing of the low pressure turbine.
  • the third bearing 42 which is located between the two other bearings 42, is connected to the flexible cage 16 and is connected to an inter-turbine casing.
  • the component 16 is a mobile mass, which can be selectively coupled or not to the shaft 12 via the means 14 for modifying the critical speed or which can be moved axially by the means 14 for modifying the critical speed.
  • the change of state of the mobile mass 16 then consists of a selective coupling, or a displacement of the moving mass 16, and makes it possible to modify the critical speed of the rotor 10 as described above.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP15704057.7A 2014-01-20 2015-01-19 Organe mobile de turbomachine qui comporte des moyens pour changer sa fréquence de résonance Active EP3097266B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1450424A FR3016659B1 (fr) 2014-01-20 2014-01-20 Organe mobile de turbomachine qui comporte des moyens pour changer sa frequence de resonance
PCT/FR2015/050118 WO2015107310A1 (fr) 2014-01-20 2015-01-19 Organe mobile de turbomachine qui comporte des moyens pour changer sa fréquence de résonance

Publications (2)

Publication Number Publication Date
EP3097266A1 EP3097266A1 (fr) 2016-11-30
EP3097266B1 true EP3097266B1 (fr) 2017-11-15

Family

ID=50290156

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15704057.7A Active EP3097266B1 (fr) 2014-01-20 2015-01-19 Organe mobile de turbomachine qui comporte des moyens pour changer sa fréquence de résonance

Country Status (8)

Country Link
US (1) US9624777B2 (lt)
EP (1) EP3097266B1 (lt)
CN (1) CN105917079B (lt)
BR (1) BR112016016336B1 (lt)
CA (1) CA2936772C (lt)
FR (1) FR3016659B1 (lt)
RU (1) RU2683334C1 (lt)
WO (1) WO2015107310A1 (lt)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3064764B1 (fr) * 2017-03-28 2019-06-28 Hutchinson Generateur d'efforts dynamiques comprenant au moins deux balourds et actionneur comprenant de tels generateurs

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3032985A (en) * 1960-07-27 1962-05-08 Gen Motors Corp Dual rotor governor
FR2336550A1 (fr) * 1975-12-24 1977-07-22 Europ Propulsion Montage d'arbre long, notamment pour turbomachine
US4117742A (en) * 1977-07-29 1978-10-03 Stein Philip C Permanent automatic rotor balancer for shafts operating above critical speed
RU1828166C (ru) * 1989-11-09 1995-09-10 Научно-производственное предпри тие "Завод им.В.Я.Климова" Роторная машина (ее варианты)
FR2864995B1 (fr) * 2004-01-12 2008-01-04 Snecma Moteurs Support de palier a double raideur
EP1892379B1 (de) * 2006-08-16 2015-11-18 Siemens Aktiengesellschaft Rotor für eine Strömungsmaschine
FR2918107B1 (fr) * 2007-06-26 2013-04-12 Snecma Dispositif amortisseur adapte aux arbres de turbomachine.
US8013481B2 (en) * 2009-03-27 2011-09-06 General Electric Company Detuner for tuning torsional mode of a rotating body

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
BR112016016336B1 (pt) 2022-08-09
CN105917079B (zh) 2018-01-26
FR3016659A1 (fr) 2015-07-24
EP3097266A1 (fr) 2016-11-30
BR112016016336A2 (lt) 2017-08-08
CA2936772A1 (fr) 2015-07-23
US9624777B2 (en) 2017-04-18
CN105917079A (zh) 2016-08-31
RU2016129585A (ru) 2018-01-24
FR3016659B1 (fr) 2016-03-04
WO2015107310A1 (fr) 2015-07-23
US20160333696A1 (en) 2016-11-17
RU2683334C1 (ru) 2019-03-28
CA2936772C (fr) 2023-03-14

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