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
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
  • F01D25/246—Fastening of diaphragms or stator-rings
• • 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
  • F01D9/00—Stators
  • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
  • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
• • 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
  • F01D9/00—Stators
  • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
  • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
  • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
• • 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
• • 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
  • F05D2230/60—Assembly methods
  • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
• • 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
  • F05D2240/10—Stators
  • F05D2240/12—Fluid guiding means, e.g. vanes
  • F05D2240/128—Nozzles
• • 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
  • F05D2240/80—Platforms for stationary or moving blades
• • 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
  • F05D2260/30—Retaining components in desired mutual position
• • 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
  • F05D2260/30—Retaining components in desired mutual position
  • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking

Definitions

• the invention relates to an assembly for locking in relative translation two turbomachine blade support parts, such as, for example, a fixed blade propeller and a blade support ring or a blading ring. mobile and a ring case.
• the invention is particularly applicable to the locking of a turbomachine flow distribution vane platform to a support ring of said vane distribution.
• FIG. 1 An example of a turbomachine has been illustrated in FIG.
• a turbomachine 1 typically comprises a nacelle which forms an opening for the admission of a given flow of air to the engine itself.
• the turbomachine comprises one or more compression sections 3 of the air admitted into the engine (generally a low pressure section and a high pressure section). The air thus compressed is admitted into the combustion chamber 5 and mixed with fuel before being burned.
• Hot combustion gases from. this combustion are then relaxed in different turbine stages.
• a first expansion is made in a high pressure stage 6 immediately downstream of the combustion chamber ei which receives them. gas at the highest temperature.
• the gases are relaxed again by being guided through the turbine stages: said low pressure 7.
• a turbine, high pressure 6 or pressure pass conventionally comprises one or more stages, each consisting of a row of stationary turbine blades, also called distributor, followed by a row of turbine blades, which form the rotor.
• the dispensers are fixed together via a ring.
• Dispenser 2 deflects the gas stream drawn at the combustion chamber to the turbine blades at a suitable angle and speed to drive these rotating blades and the rotor of the turbine in rotation.
• Each distributor is sectorized, that is to say formed of several distributor sectors arranged circumferentially end to end about a longitudinal axis XX of the turbomachine.
• Each distributor sector comprises a plurality of blades extending radially relative to the axis XX of the turbomachine so as to connect a radially inner annular element (or internal platform) and a radially outer annular element (or external platform), which together form an annular vein facing the blades of the turbine.
• a support ring of the distributor On the external platform of the distributor is mounted a support ring of the distributor, which is a part of revolution around the axis of the turbomachine.
• the ring and the distributor must be integral with each other.
• means for blocking a relative translation in the axial or radial direction (relative to the axis of the turbomachine) must be provided.
• Document FR 2 887 920 discloses locks applied in a similar manner to a turbomachine casing section extending around a mobile blade ring.
• the locks are in the form of crown sectors having a U-shaped cross-section to be able to receive a downstream end of the ring and a distributor sector, each lock being mounted tight, that is to say without play, on the ring and the casing to hold them together.
• the invention aims to overcome the problem mentioned above.
• an object of the invention is to provide an assembly for keeping together two pieces of turbomachine vane support reliably while having a long service life.
• Another object of the invention is to provide an assembly that is easy to assemble.
• the subject of the invention is an assembly comprising: two pieces of turbomachine blade support, the parts being of revolution, disposed one inside the other concentrically about a turbomachine axis, and
• the locking system comprising a split ring comprising a U-shaped cross section adapted to receive one end of the two parts, the assembly being characterized in that the crown and one of the parts are shaped to allow a engagement by interconnection of the crown on the part,
• the locking system further comprises a rotational stop member of the ring relative to the part with which it is engaged by interconnection.
• the invention also comprises at least one of the following characteristics:
• the inner part is a fixed blade platform or a vane ring
• the outer part is respectively a fixed vane support ring or a ring case.
• the U-shaped section of the crown comprises two arms interconnected by a transverse bar, such that each arm is opposite one of the parts when the crown receives the end of the parts, one of the arms and the workpiece facing said arm having dog teeth adapted to cooperate to allow engagement by interconnection of the crown on said piece.
• the outer part and the arm opposite said part are provided with dog teeth.
• the rotational stop member comprises:
• a hook positioned at the slot of the ring and adapted to receive the end of the two parts, the hook comprising, on an arm extending along one of the parts, a through hole forming a housing, and o a hook fixing pin, passing through the piece along which extends the hook arm, said pin being received in the housing of the hook.
• the hook further comprises a through groove adjacent the housing and opening on one side of the hook to allow the insertion of the pin in the housing by the groove.
• the groove has convergent edges towards the housing to prevent the exit of the pin once inserted into the housing.
• the hook further comprises a cavity adjacent to the housing, allowing elastic deformation of the hook during the insertion of the pin into the housing.
• the cavity has a width less than the width of the pin.
• the hook arm extends along the outer piece and the pin passes through said piece.
• the invention also relates to a turbomachine comprising such an assembly.
• the invention also relates to a method of mounting such an assembly comprising the steps of:
• the step of positioning the rotational stop member comprises the steps of:
• Figures 1a and 1b show a cross-sectional view of an assembly according to an embodiment, respectively at a dog tooth and at a stop member in rotation of the crown on the parts .
• Figure 1c shows a cross-sectional view of an assembly according to another embodiment, at a dog tooth.
• Figure 1d shows a cross-sectional view of an assembly according to another embodiment, at a dog tooth.
• Figure 2a shows a partial perspective view of a vane support ring that may be part of the assembly shown in Figures 1a and 1b.
• Figure 2b shows a partial front view of a coin lock ring.
• Figures 3a to 3c are views from different perspectives of an assembly according to one embodiment of the invention.
• Figure 3d shows a hook used for stopping rotation of a ring.
• Figure 4 schematically shows the main steps of the assembly method of an assembly according to the invention.
• Figure 5 is a sectional view of an example of a turbomachine on which the assembly according to the invention can be implemented.
• a set 100 which comprises two support parts of a turbomachine blade, the two parts being of revolution, and arranged one inside the other concentrically around the axis XX of the turbomachine, visible in Figure 5.
• a support part of a turbomachine blade is meant:
• a flow distribution vane an external vane platform interconnecting the blades of the vane, or a support ring of a vane, which is arranged around of said platform, or a vane ring casing disposed around said ring.
• a moving vane for example a compressor vane: a ring surrounding the vane, or a ring housing, which is arranged around said ring.
• the assembly 100 thus comprises two blade support pieces, a radially inner piece 10 and a radially outer piece 20 disposed around the first.
• the inner part 10 is a turbine engine fixed blade platform as a flow distribution vane (also called distributor), the outer part 20 then being a fixed vane support ring.
• a flow distribution vane also called distributor
• the inner part 10 is a mobile blade ring, and the outer part 20 is then a ring housing.
• the inner part 10 is a fixed vane support ring and the outer part 20 is a ring casing.
• FIG. 1a and 1b there is shown the assembly 100 in the first case.
• the inner part 10 is a blade platform which has been shown to have a blade A.
• the platform 10 comprises an upstream spoiler 1 1 and a downstream spoiler 12 with respect to the air flow, represented in FIG. arrow F.
• the spoilers upstream 1 1 and downstream 12 respectively form the upstream and downstream ends of the platform.
• the support ring 20 of the vane comprises, at its upstream end, a U-shaped hook 21 adapted to receive the upstream spoiler 1 1 of the platform, and at its downstream end a flange 22 extending towards the axis and for retaining the spoiler downstream of the platform axially downstream.
• the flange 22 is provided with a notch 23 adapted to be able to rotate the corner of the downstream spoiler 12 in this notch during the positioning of the ring 20 on the platform.
• the ring support thus pivots around the platform (the pivot being at the level of the downstream spoiler), and comes to receive at the hook 21 the upstream spoiler. This results in an axial clearance between the hook 21 and the upstream spoiler 1 1 once the ring is in position on the platform 10.
• the ring casing 20 has downstream circumferential flanges 22 which are positioned opposite downstream circumferential flanges 12 of the blading ring 10.
• a protuberance 13 on said flange makes it possible to prevent displacement of the casing upstream with respect to the blading ring 10. However, in the opposite direction downstream, and in the radial direction, the relative movements of the casing 20 and the blading ring 10 are not blocked.
• the assembly 100 thus comprises a locking system 30 parts to prohibit their relative axial and radial translation (relative to the axis of the turbomachine).
• this system 30 comprises a ring 40 having a U-shaped section comprising two arms 41, 42 parallel, interconnected at one end by a transverse bar 43.
• the length of the transverse bar 43 defines the spacing between the arms, which must be sufficient to receive one end of the two parts 10, 20.
• the crown receives, as illustrated in Figures 1a and 1b, the downstream spoiler 12 of the platform and the flange 22 of the ring, so that an inner arm 41 of the crown is facing an inner face of the downstream spoiler 12 and an outer arm 42 facing the outer face of the ring.
• the crown receives the downstream circumferential rims 12, 22 of the two parts, the internal arm 41 being opposite the inner face of the downstream flange 12 of the ring, and the outer arm 42 facing the outer face of the downstream flange 22 of the housing.
• the ring 40 is shaped so as to be mounted by interconnection on one of the parts.
• the ring 40 and one of the parts, preferably the outer part 20, are shaped so as to cooperate together by interconnection.
• they comprise dog teeth 44, 24, complementary, that is to say that the dog teeth of each piece are of equal length and distributed at constant angular interval, and the angular interval between two teeth dog 24, 44 of a piece corresponding to or greater than the length of a dog tooth 44, 24 of the other piece.
• FIGS. 1a, 1c According to a preferred embodiment, which is illustrated in FIGS. 1a, 1c,
• the dog teeth 44 are protuberances of the outer arm 42 of the crown, which project inwards, that is to say towards the axis of revolution of the crown.
• the outer part 20 comprises on its outer surface the dog teeth 24, extending radially in the opposite direction of the axis of revolution of the workpiece.
• the crown can thus be mounted by interconnection on the parts 10, 20 by receiving the end of the two parts, which makes it possible to stop in translation in the radial direction of the two parts 10, 20 relative to each other. the other (because the inner part 10 is held by the ring against the outer part), and in axial relative translation, because the dog teeth 44 and the transverse bar 43 of the crown deprive the outer member 20 of axial movement.
• the assembly by interconnection of the crown on the parts allows to allow the presence of clearances between the ring and the parts 10,20, which allow the parts to expand, especially because of the thermal stresses involved, without reducing on their life span.
• the inner part 10 may comprise dog teeth, positioned on its radially inner surface and extending radially.
• the crown 40 then comprises dog teeth 44 on its inner arm 41, the teeth then protruding outwardly.
• the ring 40 is advantageously split, that is to say that it extends over an angular sector less than 360 °, but advantageously greater than 350 °.
• the slot 45 of the ring 40 also allows the parts to expand under thermal stress without damaging the crown or the parts themselves.
• the locking system 30 of the parts further comprises a rotational stop member 50 of the ring 40 relative to the two parts 10, 20.
• This rotational stop member is advantageously positioned at the slot 45 of the crown. 40.
• the rotational stopper 50 comprises a hook 51 which is adapted to receive the end of the two parts 10, 20.
• the parts are a platform fixed blade 10 and a support ring 20
• the ends are as before the end of the downstream spoiler 12 and the flange 22.
• the hook 51 comprises in particular an arm 52 extending along one of the parts 10, 20, advantageously along the outer part 20.
• the arm 52 comprises a through hole 53 forming a housing for a pin 59 extending through an orifice (not shown) provided in the part along which s 'extend the arm.
• the orifice 53 advantageously has the same shape as the section of the pin 59, namely advantageously a circular shape.
• the crown 40 When the crown 40 is mounted on the parts by interconnection, it is positioned so that the dog teeth 24, 44 are opposite and thus the crown fulfills its role of radial and axial stop.
• the hook 51 is mounted at the slot 45 to receive the pieces, and the pin 59 is inserted into the housing 53 of the hook, thus maintaining the angular position of the hook of the ring 40 constant.
• the hook 51 occupying the slot 45 of the crown, it can not pivot around the parts 10, 20 until the dog teeth are no longer facing and the ring 40 can be removed.
• the hook 51 further comprises a groove 54 therethrough adjacent the housing 53, and opening on one side of the hook.
• the pin can be inserted into the housing by sliding in the groove until it reaches the housing 53.
• the groove preferably has edges converging towards the housing, the housing itself having a diameter greater than the spacing of the edges of the groove at its end adjacent to the housing, so that the pin, once inserted into the housing by displacement in the groove, can not come out again.
• the hook 51 then advantageously comprises a cavity 55, preferably through, and adjacent to the housing, this cavity 55 being preferably opposite the groove with respect to the housing, thus allowing the hook 51 to deform elastically when the insertion of the peg 59 into the housing 53.
• This cavity 55 advantageously has a width less than the diameter of the housing 53, to prevent a movement of the pin from the housing 53 to the cavity 55 once inserted into the housing 53.
• a first step 1100 the two blade support pieces 10 are positioned concentrically within each other.
• the parts are nested together in a manner known to those skilled in the art, to obtain the provisions respectively illustrated in Figures 1a, 1b in one case and 1c in the other case.
• 1200 is then positioned a ring 40 by interconnection on the parts.
• 1210 is brought a crown 40 by shifting the dog teeth 44 of the ring relative to the dog teeth 24 of one of the parts, and by engaging the ring 40 to the pieces so that the ends of the pieces are received between the arms 41, 42 of the crown.
• the crown 40 is then pivoted with respect to the parts 10, 20, so that the clutch teeth 44 of the ring face the clutch teeth 24 of the part, for example the outer piece 20, and that thus the crown forms a stop in axial translation of the workpiece.
• a member 50 for stopping rotation of the ring relative to the parts.
• a hook 51 comprising a groove 54 adjacent to the housing 53. 1310 is engaged an anti-rotation pin 59 through one of the parts, and 1320 is brought to the hook 51 at of the slot, so that it receives the end of the pieces and that the pin 59 is received in the groove. The hook 51 is progressively displaced so that the pin 59 moves in the groove until it reaches the housing 53.
• the pin 59 is advantageously locked in the housing by the converging edges of the groove.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

Applications Claiming Priority (2)

Publications (2)

Family

ID=49484298

Family Applications (1)

Country Status (9)

Families Citing this family (6)

Family Cites Families (17)

• 2013
  • 2013-08-13 FR FR1357982A patent/FR3009740B1/fr active Active
• 2014
  • 2014-08-11 CA CA2920983A patent/CA2920983C/fr active Active
  • 2014-08-11 EP EP14786954.9A patent/EP3033495B1/de active Active
  • 2014-08-11 US US14/911,424 patent/US10247039B2/en active Active
  • 2014-08-11 CN CN201480052865.0A patent/CN105579670B/zh active Active
  • 2014-08-11 RU RU2016108869A patent/RU2672208C2/ru active
  • 2014-08-11 WO PCT/FR2014/052079 patent/WO2015022468A1/fr active Application Filing
  • 2014-08-11 BR BR112016002953A patent/BR112016002953A8/pt not_active Application Discontinuation
  • 2014-08-11 JP JP2016533940A patent/JP2016530441A/ja active Pending

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