EP1659266B1 - Dispositif de découplage commun aux premier et deuxième paliers de l'arbre d'entraînement d'une turbomachine, et turbomachine et compresseur comprenant ledit dispositif de découplage - Google Patents

Dispositif de découplage commun aux premier et deuxième paliers de l'arbre d'entraînement d'une turbomachine, et turbomachine et compresseur comprenant ledit dispositif de découplage Download PDF

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Publication number
EP1659266B1
EP1659266B1 EP05110969A EP05110969A EP1659266B1 EP 1659266 B1 EP1659266 B1 EP 1659266B1 EP 05110969 A EP05110969 A EP 05110969A EP 05110969 A EP05110969 A EP 05110969A EP 1659266 B1 EP1659266 B1 EP 1659266B1
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EP
European Patent Office
Prior art keywords
bearing
turbomachine
flange
drive shaft
decoupling device
Prior art date
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Active
Application number
EP05110969A
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German (de)
English (en)
French (fr)
Other versions
EP1659266A1 (fr
Inventor
Michel Brault
Patrick Morel
Zoltan Zsiga
Gaël Bouchy
Pierre Pandelakis
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
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SNECMA SAS
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Publication of EP1659266A1 publication Critical patent/EP1659266A1/fr
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    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings

Definitions

  • the invention relates to the field of turbomachines with a decoupling device common to the first and second bearings of its drive shaft.
  • a turbojet comprises, from upstream to downstream in the direction of the gas flow, a fan, one or more stages of compressors, a combustion chamber, one or more turbine stages and a gas exhaust nozzle.
  • the fan comprises a rotor provided with vanes at its periphery which, when they are rotated, drive the air into the turbojet engine.
  • the fan rotor is supported by the low pressure rotor shaft of the motor. It is centered on the axis of the turbojet engine by a first bearing which is upstream of a second bearing, connected to the fixed structure of the turbojet engine, in particular to the intermediate casing.
  • blower is mounted integral with the compressor shaft, which is the low pressure rotor shaft in a double-body engine, this shaft is designated, or any other shaft that is integral, by the single term compressor shaft.
  • the first bearing is supported by a support piece, forming a casing around the compressor shaft, oriented downstream of the first bearing and fixed to a fixed structure of the turbojet engine.
  • the second bearing is supported by a support piece also attached to a fixed structure of the turbojet engine.
  • This dimensioning entails additional costs and increases the mass of the turbojet engine.
  • the support parts of the first bearing and the second bearing, in this case integral with each other, are fixed to the structure of the turbojet engine by screws said fusible, having a weakened portion causing their rupture in case of efforts too important.
  • the forces induced on the bearings are transmitted to the fusible screws that break, uncoupling the support parts of the bearings of the fixed structure of the turbojet engine.
  • the forces caused by the unbalance are no longer transmitted to the fixed structure of the turbojet engine by these support pieces.
  • the document FR 2, 752, 024 proposes, in order to limit such movements, to provide parts forming a false bearing for the bearing supports, which are rotated and tilted with the shaft when decoupled from the fixed structure; it is in this case a rib, integral with the fixed structure, extending transversely to the axis of the turbojet and ending with pads surrounding the compressor shaft, or a rib surrounding the support of the first landing.
  • a rib integral with the fixed structure, extending transversely to the axis of the turbojet and ending with pads surrounding the compressor shaft, or a rib surrounding the support of the first landing.
  • the tilting of the bearing supports with the drive shaft causes considerable effort, and their inertia, and the lever arm they represent relative to the axis of the turbojet, is large.
  • the invention relates to a turbomachine, comprising a rotor with a drive shaft, centered on the axis of the turbomachine by a first and a second bearing, supported respectively by a support part of the first bearing and a part support of the second bearing, integral with one another and connected to the fixed structure of the turbomachine by a decoupling device, characterized in that it comprises means arranged to cooperate with at least one element of the fixed structure the turbomachine to ensure a dual function, rotational locking of the bearing supports and radial retention of the drive shaft in case of decoupling of the bearings.
  • said means are then arranged to provide a third function, axial retention of the rotor in case of rupture of the drive shaft.
  • the axial retention of the rotor can be done regardless of the positioning of the breaking point of the drive shaft, downstream of the first bearing, since the support parts of the first and second bearings are integral.
  • the means are arranged on the second bearing support piece.
  • said means are arranged not to hinder the longitudinal movements of the drive shaft during the decoupling kinematics.
  • the invention also relates to a decoupling device between a fixed structure of the turbomachine presented above and a first and a second parts, integral with each other and forming supports of a first and second bearings of the drive shaft of the rotor of the turbomachine, characterized in that it comprises means arranged to cooperate with at least one element of the fixed structure of the turbomachine to ensure a dual function of locking in rotation of the supports of bearings and radial retention of the drive shaft in case of decoupling of the bearings.
  • the invention also relates to a turbomachine compressor, comprising a rotor with a drive shaft, centered on the axis of the turbomachine by a first and a second bearing, supported respectively by a support part of the first bearing and a support piece of the second tier, in solidarity with one another and connected to the fixed structure of the turbomachine by a decoupling device, characterized by the fact that it comprises means arranged to cooperate with at least one element of the fixed structure of the turbomachine to ensure a dual function of locking in rotation of the bearing supports and radial retention of the drive shaft in case of decoupling of the bearings.
  • the turbomachine is here a turbojet engine 1 which comprises, in its first embodiment, a rotor, not shown, called a fan, which comprises vanes extending radially around the axis 2 of the turbojet engine.
  • the fan shaft is fixed downstream of the blades to the compressor shaft 3. Upstream and downstream means upstream and downstream in the direction of the gas flow. This is the low pressure compressor shaft.
  • the assembly of the shaft of the fan and of the compressor shaft 3, as well as any other shaft integral thereto, will be designated hereinafter by compressor shaft 3, or drive shaft 3.
  • the shaft compressor 3 is supported by a first bearing 4 and a second bearing 5, located downstream of the first bearing 4.
  • the first bearing 4 comprises an inner ring 6 and an outer ring 7, between which are mounted balls 8 or other rolling members.
  • the inner ring 6 is mounted integral with the compressor shaft 3 and the outer ring 7 integral with a support part 9 of the first bearing, hereinafter referred to as the support of the first bearing 9.
  • the support of the first bearing 9 extends, from the first level 4, downstream. It is generally of frustoconical shape, its diameter increasing downstream, and is connected downstream to the fixed structure of the turbojet 1, as will be seen later.
  • the balls 8 allow the rotation of the inner ring 6, therefore of the compressor shaft 3, with respect to the outer ring 7, thus to the support of the first bearing 9 and to the fixed structure of the turbojet engine 1.
  • the second bearing 5 comprises an inner ring 10 and an outer ring 11, between which are mounted rollers 12 or other rolling members.
  • the inner ring 10 is mounted integral with the compressor shaft 3 and the outer ring 11 is mounted integral with a support part 13 of the second bearing, hereinafter referred to as the support of the second bearing 13, which extends from the second tier 5, upstream.
  • the outer ring 11 of the second bearing 5 comprises for this purpose, on its outer face, a radial flange 14 fixed to an internal flange of the support of the second bearing 13 by screws 15.
  • the support of the second bearing 13 is generally of frustoconical shape, its diameter increasing upstream and comprises, at its upstream end, a flange 16 transverse to the axis 2 of the turbojet engine.
  • the support of the first bearing 9 comprises, at its downstream end, a flange 17 transversely extending radially inwards, on which is fixed, for example by means of screws 18, the flange 16 of the support of the second bearing 13
  • the supports 9, 13 of the first and second bearings 4, 5 are thus integral with each other.
  • the flange 17 of the support of the first bearing 9 is fixed to the fixed structure of the turbojet engine 1, in this case to a flange 19 of a casing, said intermediate casing, by fusible screws 20, situated outside with respect to the fixing screws 18 supports of the first and second bearings 9, 13.
  • These fusible screws 20 comprise a fusible portion 21 forming a preferred tensile break zone, calibrated so as to break in the event of determined tensile forces.
  • This fusible portion 21 is here obtained by calibrated thinning of the screw rod 20.
  • the screws 20 thus form a common decoupling device of the first and second bearings 4, 5, which are integral with the fixed structure of the turbojet engine 1.
  • the rollers 12 of the second bearing 5 are mounted parallel to the axis 2 of the turbojet engine 1, in a groove extending around the circumference of the inner ring 10, and are held spaced from each other by a squirrel cage, of which the description will not be detailed here because it is well known to those skilled in the art. They allow the rotation of the inner ring 10 with respect to the outer ring 11, and therefore via the compressor shaft 3 with respect to the fixed structure of the turbojet engine 1.
  • a flange 22 of generally frustoconical shape From the flange 19 of the intermediate casing extends, downstream of the support of the second bearing 13, radially inwards and slightly downstream, a flange 22 of generally frustoconical shape, its diameter decreasing downstream .
  • a ring 23 of L-shaped section On the flange radial 14 of the outer ring 11 of the second bearing 5 is fixed at its outer end, a ring 23 of L-shaped section, cooperating with the fixed structure of the turbojet 1 to fulfill here a dual function, radial retention of the compressor shaft 3 in case of decoupling the bearings 4, 5 and axial retention of the fan in the event of rupture of the compressor shaft 3.
  • This ring 23 is in this case formed in one piece with the radial flange 14 and comprises a longitudinal portion 24, forming the large bar of the L-shaped section, extending downstream from the outer end of the radial flange 14, and a radial portion 25, extending radially outwardly from the downstream end of the longitudinal portion 24.
  • the ring 23 of L-shaped section is arranged to cooperate with the end portion 26 of the internal flange 22 to ensure its dual function, radial retention of the compressor shaft 3 by its longitudinal portion 24, axial retention of the blower by its radial portion 25.
  • the outer wall of the longitudinal portion 24 of the ring 23 is located at a distance "e" from the inner wall of the end portion 26 of the flange 22, distance "e” calibrated so that these two walls come into contact, in case of decoupling of the bearings, if the radial amplitude of the movements of the compressor shaft 3 exceeds a certain threshold; the movements of the shaft 3 being thus limited, the movements of the fan are limited.
  • the radial portion of the upstream wall 25 of the ring 23 is located at a distance "1" from the downstream wall of the end portion 26 of the flange 22, distance "1" calibrated so that these two walls come into contact, in case of breakage of the compressor shaft 3, to ensure an axial retention function of the fan. It can be noted that the rupture can take place at any point on the compressor shaft 3, downstream of the first bearing 4. In fact, assuming that the bearings 4, 5 are decoupled and that the compressor shaft 3 broken between the two bearings 4, 5, the fan, which continues to rotate, is driven forward with the portion of the compressor shaft 3 which is still secured to it.
  • This portion drives the first bearing 4 forward and therefore, by solidarity of the parts, the support of the first bearing 9, the support of the second bearing 13, the radial flange 14 of the outer ring 11 of the second bearing 5 and thus the ring 23 with L section, the radial portion 25 abuts against the end portion of the flange 22 secured to the fixed structure of the turbojet engine 1.
  • the fan is thus retained.
  • the same is true in the event of a break downstream of the second bearing, the entire portion of the compressor shaft 3 located between the two bearings 4, 5 then being driven forwardly with the ring 23 of the radial flange 14 of the second bearing 5.
  • the distances "1" and “e” are calibrated so that the radial portion 25 of the ring 23 does not abut against the end portion 26 of the flange 22 during the decoupling phase. Indeed, during this phase, the compressor shaft 3 does not rotate on its axis and can perform movements with longitudinal components. In particular, during the breakage of a blade, the unbalance caused translates, temporarily, by a rotational movement of the compressor shaft 3 around the first fusible screw 20 which breaks.
  • the distance "1" is sufficiently large so that the stop of the radial portion 25 of the ring 23 on the flange 22 does not occur in normal operation of the turbojet 1 or during a decoupling phase.
  • Anti-rotation fingers 27 are also arranged on the support of the second bearing 13. They extend longitudinally rearwards from the screws 18 for fixing the supports 9, 13 of the first and second bearings 4, 5 between them. These fingers 27 extend through orifices 28 formed in the flange 22 and cooperate with them, in case of decoupling the bearings 4, 5, to prevent the rotation of the supports of the bearings 9, 13, and therefore the outer rings of the first and second bearings 4, 5, about the axis 2 of the turbojet engine 1; the fingers 27 then come into abutment against the walls of the orifices 28 of the flange 22, which is integral with the fixed structure of the turbojet engine 1. A clearance is provided between the fingers 27 and their orifices 28 of passage, so as not to disturb the dual function of the ring 23 L-section and do not hinder the decoupling kinematics.
  • the induced forces cause the rupture of the fusible screws 20 for fixing the supports 9, 13 of the first and second bearings 4, 5 to the fixed structure of the turbojet 1, at their fuse portion 21.
  • the fusible portion 21 of the screws 20 form a preferred zone of tensile rupture, while the unbalance the compressor shaft 3 is essentially radial; in fact, the radial forces on tree 3 translate into level of the screws 20 by longitudinal forces, in particular through the support of the first bearing 9.
  • the movements of the compressor shaft 3 are radially limited by the cooperation of the longitudinal portion 24 of the L-shaped section ring 23 with the end portion 26 of the flange 22.
  • the portion radial 25 of the ring 23 does not interfere with this decoupling kinematics due to the calibration of the distance "1".
  • the support of the first bearing 9 and the support of the second bearing 13 are decoupled from the flange 19 of the intermediate casing and thus from the fixed structure of the turbojet engine 1.
  • the forces related to the unbalance are not more then transmitted to the latter by the bearing supports 9, 13 and the compressor shaft 3 can freely rotate on its axis 2, its movements being radially limited by the ring 23 of L-section cooperating with the flange 22.
  • the supports Bearings 9, 13 are locked in rotation by the anti-rotation fingers 27 previously described.
  • the ring 23 L-shaped section and the anti-rotation fingers 27 fill, in cooperation with the flange 22, a function of emergency bearing support, since they fulfill a function of radial retention of the shaft of the compressor 3, with a piece, the ring 23, integral with the outer ring 11 of the second bearing 5, locked in rotation about the axis 2 of the turbojet engine via the support of the second bearing 5 and allowing the rotation of the compressor shaft 3.
  • the ring 23 and anti-rotation fingers 27 are arranged to fill, with the flange 22, a backup bearing support function, further ensuring an axial retention function of the fan.
  • the turbojet engine 1 ' also comprises, in its second embodiment, a fan, rotatably mounted around the axis 2 'of the turbojet engine and driven by a shaft 3 ', which is the compressor shaft 3', supported by a first bearing 4 'and a second bearing 5', located downstream of the first bearing 4 '.
  • the first bearing 4 ' comprises an inner ring 6', integral with the drive shaft 3 ', and an outer ring 7', integral with a support of the first bearing 9 ', between which are mounted balls 8' or other running gear.
  • the support of the first bearing 9 ' extends downstream, where it comprises a downstream flange 17' fixed to a flange 19 'of the intermediate casing by fusible screws 20' forming a device for decoupling the bearings 4 ', 5', thanks to their fusible portion 21 'forming a preferred zone of tensile rupture.
  • the second bearing 5 ' comprises an inner ring 10', integral with the compressor shaft 3 ', and an outer ring 11', integral with a support of the second bearing 13 ', between which are mounted rollers 12' or the like running gear.
  • the outer ring 11 ' is fixed to the support of the second bearing 13' by means of a radial flange 14 'projecting from its outer wall, using screws 15'.
  • the support of the second bearing 13 ' slightly frustoconical, comprises, at its upstream outer end, a flange 16' fixed on the downstream flange 17 'of the support of the first bearing 13' by screws 18 ', in the internal position relative to the 20 'fuse screws.
  • This flange 29 ' comprises, from the flange 19' of the intermediate casing to the flange 14 'of the outer ring 11', a portion 30 'transverse to the axis of the turbojet engine and a portion 31' of section U-shaped , with a longitudinal outer branch 32 ', a transverse base 33' and a longitudinal inner leg 34 ', the base 33' of the U being located on the downstream side.
  • the portion 31 'of U-shaped section hereinafter referred to as U' portion 31 ', extends between the inner end of the transverse portion 30' and the outer end of the radial flange 14 'of the ring 11 of which it is solidary.
  • section 31 'of U-shaped section which here provides the triple function of locking rotation of the bearing supports 9', 13 'and radial retention of the compressor shaft 3' during the decoupling of bearings 4 ', 5', and axial retention of the fan, in case of rupture of the compressor shaft 3 '.
  • the flange 29 ' has no influence on the normal operation of the turbojet engine 1'.
  • the portion 31 'in U is calibrated so as to have a certain radial flexibility, which is obtained by elasticity between its two branches 32', 34 ', but having sufficient strength to provide a radial retention function of the 'compressor shaft 3' during the decoupling kinematics of the bearings 4 ', 5'.
  • This portion 31 ' is also torsionally rigid, in order to ensure a rotational locking function of the bearing supports 9', 13 ', and therefore of the outer rings of the first and second bearings 4', 5 ', through the support of the second bearing 13 ', which it is secured by the flange 14' of the outer ring of the second bearing 5 '.
  • this portion is calibrated so as to have a certain axial flexibility, in this case a greater flexibility than the radial flexibility so as not to hinder the longitudinal movements of the drive shaft during the decoupling kinematics of the bearings 4 ', 5', but a sufficient resistance to ensure an axial retention function of the fan in case of rupture of the compressor shaft 3 '.
  • the rotational locking function of the bearing supports 9 ', 13' is here ensured by the flange 29 ', without anti-rotation fingers.
  • the flange 29 'thus provides, in particular thanks to its U-shaped section, a support bearing support function of the second bearing 5', since it ensures the radial retention of the compressor shaft, which can rotate relative to the outer ring 11 ', locked in rotation. It also provides a function of axial retention of the fan in case of breakage of the compressor shaft 3 '.
  • the axial retention of the fan occurs in the event of rupture of the compressor shaft 3 'at any point of this shaft 3', provided that this point is located downstream of the first level 4 '.
  • This portion drives the first bearing 4 'towards the front and therefore, by solidarity of the parts, the support of the first bearing 9', the support of the second bearing 13 ', the radial flange 14' of the outer ring 11 'of the second bearing and therefore the flange 29 'with its portion 31' U, which holds the assembly.
  • the blower is thus retained. The same is true in case of break downstream of the second bearing 5 '.
  • the turbojet 1 also comprises, in its second embodiment, a blower , rotatably mounted around the axis 2 "of the turbojet and driven by a drive shaft 3", which is the compressor shaft 3 ", supported by a first bearing 4" and a second bearing 5 ", located downstream
  • the first bearing 4 has an inner ring 6", integral with the drive shaft 3 ", and an outer ring 7", integral with a support of the first bearing 9 ", between which are mounted on balls 8 "or other rolling members
  • the support of the first bearing 9 of generally frustoconical shape, extends downstream, where it comprises a downstream flange 17 "fixed to a flange 19" of the intermediate casing by fusible screws 20 “forming a device for decoupling the bearings 4 ', 5 ', thanks to their fusible portion 21 "forming a preferred zone of rupture in tension.
  • the second bearing 5 “comprises an inner ring 10", integral with the compressor shaft 3 ", and an outer ring 11", integral with a support of the second bearing 13 ", between which are mounted rollers 12" or other running gear.
  • the outer ring 11 is fixed to the support of the second bearing 13" with a radial flange 14 "projecting on its outer wall, using screws 15".
  • the support of the second bearing 13 “ slightly frustoconical, comprises, at its upstream outer end, an external flange 16", fixed on the downstream flange 17 “of the support of the first bearing 13” by screws 18 ", in the inner position relative to the 20 “fusible screws.
  • the outer flange 16 "of the support of the second bearing 13" is fixed on the flange 17 “of the support of the first bearing 9" so that its outer edge has a radial clearance "E” with the inner wall of the flange 19 " of the intermediate casing, upstream of the rib 35 ", in order to cooperate with it to ensure, by stop, a radial retention function of the compressor shaft 3" in case of decoupling the bearings 4 ', 5'.
  • the anti-rotation fingers 27 “have, on their projecting portion on the downstream side of the rib 35", a flange 36 ", located at a distance” L “from the downstream wall of the rib 35", in order to ensure axial retention function of the fan in case of rupture of the compressor shaft 3 ".
  • the rupture of the compressor shaft 3 " can occur at any point on the compressor shaft 3", provided that it is located downstream 4 ", 5" decoupled bearings, if the compressor shaft 3 "breaks between the two bearings 4", 5 ", the fan, which continues to rotate, is driven forward with the portion of the compressor shaft 3 "which is still integral with it.This portion drives the first bearing 4" forward and therefore, by solidarity of the parts, the support of the first bearing 9 ", the support of the second bearing 13 “And thus the fingers 27" with their flange 36 ", which abut against the rib 35" and hold the assembly.The blower is thus retained.It is the same in case of rupture downstream of the second bearing 5 " .
  • the invention has been described, in its three embodiments, in relation to a turbojet engine, in particular a double-body turbojet engine whose second bearing is a bearing supporting the low-pressure rotor.
  • the invention applies to other types of turbomachines, such as a turboprop, an industrial turbocharger or an industrial turbine, the rotor is not then a fan rotor but simply a rotor.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP05110969A 2004-11-19 2005-11-18 Dispositif de découplage commun aux premier et deuxième paliers de l'arbre d'entraînement d'une turbomachine, et turbomachine et compresseur comprenant ledit dispositif de découplage Active EP1659266B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0412296A FR2878289A1 (fr) 2004-11-19 2004-11-19 Turbomachine avec un dispositif de decouplage commun aux premier et deuxieme paliers de son arbre d'entrainement

Publications (2)

Publication Number Publication Date
EP1659266A1 EP1659266A1 (fr) 2006-05-24
EP1659266B1 true EP1659266B1 (fr) 2008-01-09

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EP05110969A Active EP1659266B1 (fr) 2004-11-19 2005-11-18 Dispositif de découplage commun aux premier et deuxième paliers de l'arbre d'entraînement d'une turbomachine, et turbomachine et compresseur comprenant ledit dispositif de découplage

Country Status (7)

Country Link
US (1) US7195444B2 (ja)
EP (1) EP1659266B1 (ja)
JP (1) JP4818694B2 (ja)
CA (1) CA2527352C (ja)
DE (1) DE602005004239T2 (ja)
FR (1) FR2878289A1 (ja)
RU (1) RU2362888C2 (ja)

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FR2878289A1 (fr) 2006-05-26
EP1659266A1 (fr) 2006-05-24
CA2527352A1 (fr) 2006-05-19
JP2006144794A (ja) 2006-06-08
RU2362888C2 (ru) 2009-07-27
US20060110244A1 (en) 2006-05-25
RU2005135955A (ru) 2007-05-27
DE602005004239D1 (de) 2008-02-21
DE602005004239T2 (de) 2009-04-02
CA2527352C (fr) 2013-03-05
US7195444B2 (en) 2007-03-27
JP4818694B2 (ja) 2011-11-16

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