EP3033495B1 - Amelioration pour le verrouillage de pieces de support d'aubage - Google Patents

Amelioration pour le verrouillage de pieces de support d'aubage Download PDF

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Publication number
EP3033495B1
EP3033495B1 EP14786954.9A EP14786954A EP3033495B1 EP 3033495 B1 EP3033495 B1 EP 3033495B1 EP 14786954 A EP14786954 A EP 14786954A EP 3033495 B1 EP3033495 B1 EP 3033495B1
Authority
EP
European Patent Office
Prior art keywords
parts
hook
assembly
crown
housing
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
EP14786954.9A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3033495A1 (fr
Inventor
Patrice Jean-Marc Rosset
Coralie GUERARD
Hélène CONDAT
Sébatien PRESTEL
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
Safran Aircraft Engines 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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3033495A1 publication Critical patent/EP3033495A1/fr
Application granted granted Critical
Publication of EP3033495B1 publication Critical patent/EP3033495B1/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
    • 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 platform and a vane support ring or a mobile blade ring and a ring case.
  • the invention applies in particular to the locking of a turbomachine flow distribution vanes platform to a support ring of said distribution vane, as is known from the document EP 0 967 364 .
  • FIG. 5 An example of a turbomachine has been illustrated in figure 5 .
  • 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.
  • the hot combustion gases from this combustion are then expanded in different turbine stages.
  • a first expansion is made in a high pressure stage 6 immediately downstream of the combustion chamber and which receives gas at the highest temperature.
  • the gases are expanded again by being guided through so-called low pressure turbine stages 7.
  • a turbine, high pressure 6 or low pressure 7 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.
  • 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 invention also relates to a turbomachine comprising such an assembly.
  • an assembly 100 which comprises two support pieces of a turbomachine blade, the two parts being of revolution, and disposed one inside the other concentrically about the axis XX of the turbomachine, visible on the figure 5 .
  • 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.
  • the inner part 10 is a blade platform which has been shown to have a blade A.
  • the platform 10 comprises an upstream spoiler 11 and a downstream spoiler 12 with respect to the air flow, represented in the figure by an arrow F.
  • the spoilers upstream 11 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 11 of the platform, and at its downstream end a flange 22 extending towards the axis and to retain the spoiler downstream of the platform axially downstream.
  • the flange 22 is provided with a notch 23 adapted to be able to pivot 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 11 once the ring is in position on the platform 10.
  • the ring housing 20 has downstream circumferential flanges 22 which are positioned facing 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 crown 40 having a U-shaped section comprising two parallel arms 41, 42 connected together 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 on 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 ring is facing an inner face of the downstream spoiler 12 and an outer arm 42 is opposite of the outer face of the ring.
  • the crown receives the downstream circumferential flanges 12, 22 of the two parts, the inner arm 41 being opposite the internal 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.
  • dog teeth 44 are protuberances of the outer arm 42 of the crown, which project inwardly, 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 locking 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 stop member 50 comprises a hook 51 which is adapted to receive the end of the two parts 10, 20.
  • the ends are as before the end of the downstream spoiler 12 and the flange 22.
  • the ends are their downstream circumferential rims 12, 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 to through an orifice (not shown) provided in the part along which the arm extends.
  • 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. In this way, 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 one inside the other.
  • the pieces are nested together in a manner known to those skilled in the art, to obtain the provisions respectively illustrated in FIG. 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.

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)
EP14786954.9A 2013-08-13 2014-08-11 Amelioration pour le verrouillage de pieces de support d'aubage Active EP3033495B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1357982A FR3009740B1 (fr) 2013-08-13 2013-08-13 Amelioration pour le verrouillage de pieces de support d'aubage
PCT/FR2014/052079 WO2015022468A1 (fr) 2013-08-13 2014-08-11 Amelioration pour le verrouillage de pieces de support d'aubage

Publications (2)

Publication Number Publication Date
EP3033495A1 EP3033495A1 (fr) 2016-06-22
EP3033495B1 true EP3033495B1 (fr) 2018-10-31

Family

ID=49484298

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14786954.9A Active EP3033495B1 (fr) 2013-08-13 2014-08-11 Amelioration pour le verrouillage de pieces de support d'aubage

Country Status (9)

Country Link
US (1) US10247039B2 (ru)
EP (1) EP3033495B1 (ru)
JP (1) JP2016530441A (ru)
CN (1) CN105579670B (ru)
BR (1) BR112016002953A8 (ru)
CA (1) CA2920983C (ru)
FR (1) FR3009740B1 (ru)
RU (1) RU2672208C2 (ru)
WO (1) WO2015022468A1 (ru)

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US9828879B2 (en) * 2015-05-11 2017-11-28 General Electric Company Shroud retention system with keyed retention clips
FR3036436B1 (fr) 2015-05-22 2020-01-24 Safran Ceramics Ensemble d'anneau de turbine avec maintien par brides
FR3041028A1 (fr) * 2015-09-11 2017-03-17 Snecma Distributeur d'une turbine basse pression, turbine basse pression et turbomachine associees
FR3046410B1 (fr) 2016-01-05 2017-12-29 Snecma Assemblage pour turbomachine d'aeronef a helices contrarotatives non carenees, comprenant un fourreau de passage de servitudes a encombrement reduit
CN109653816B (zh) * 2019-01-23 2024-05-10 江苏核电有限公司 一种用于汽轮机自带围带叶片的撑顶工具及其撑顶方法
US11939888B2 (en) * 2022-06-17 2024-03-26 Rtx Corporation Airfoil anti-rotation ring and assembly

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US5201846A (en) * 1991-11-29 1993-04-13 General Electric Company Low-pressure turbine heat shield
JPH06129205A (ja) * 1992-10-20 1994-05-10 Mitsubishi Heavy Ind Ltd ガスタービンの静翼
FR2743603B1 (fr) 1996-01-11 1998-02-13 Snecma Dispositif de jonction de segments d'un distributeur circulaire a un carter de turbomachine
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Also Published As

Publication number Publication date
RU2016108869A3 (ru) 2018-05-21
JP2016530441A (ja) 2016-09-29
CA2920983C (fr) 2021-05-25
FR3009740B1 (fr) 2017-12-15
FR3009740A1 (fr) 2015-02-20
CA2920983A1 (fr) 2015-02-19
WO2015022468A1 (fr) 2015-02-19
EP3033495A1 (fr) 2016-06-22
RU2016108869A (ru) 2017-09-19
CN105579670A (zh) 2016-05-11
US20160245122A1 (en) 2016-08-25
BR112016002953A8 (pt) 2020-02-04
US10247039B2 (en) 2019-04-02
CN105579670B (zh) 2018-01-16
RU2672208C2 (ru) 2018-11-12
BR112016002953A2 (pt) 2017-08-01

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