EP3180497B1 - Module de turbomachine - Google Patents

Module de turbomachine Download PDF

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Publication number
EP3180497B1
EP3180497B1 EP15757535.8A EP15757535A EP3180497B1 EP 3180497 B1 EP3180497 B1 EP 3180497B1 EP 15757535 A EP15757535 A EP 15757535A EP 3180497 B1 EP3180497 B1 EP 3180497B1
Authority
EP
European Patent Office
Prior art keywords
sectors
foil
ring
hooks
walls
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
EP15757535.8A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3180497A1 (fr
Inventor
Cyril LOISEAU
Alain Dominique Gendraud
Sébastien Jean Laurent 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
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Safran Aircraft Engines SAS
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Publication date
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Publication of EP3180497A1 publication Critical patent/EP3180497A1/fr
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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • 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
    • F05D2240/11—Shroud seal segments

Definitions

  • the present invention relates to a turbomachine module, which may be a turbine or be part of a turbine for example.
  • the state of the art includes the documents WO-A1-98 / 53228 , EP-A2-2,612,998 and EP-A2-2 508 715 .
  • a turbomachine turbine comprises one or more stages each comprising a distributor formed of an annular row of stationary vanes carried by a casing of the turbine, and a rotor wheel rotatably mounted generally downstream of the distributor.
  • the wheel is surrounded by a sealing ring which is sectored and formed by sectors which are arranged circumferentially end to end and which are hooked on the casing of the turbine.
  • Each ring sector generally comprises a circumferentially oriented metal plate which carries a block of abradable material attached to the inner surface of the plate.
  • This block is for example of the honeycomb type and is intended to wear by friction on external annular wipers of the vanes of the wheel, to form a labyrinth seal and minimize the radial clearances between the wheel and the ring areas.
  • Each ring sector comprises at its upstream and downstream ends hooking means on the housing.
  • Each ring sector may comprise at its upstream end a circumferential hook which defines an annular groove in which is engaged, on the one hand, an annular rail of the housing, and on the other hand, a downstream circumferential hook of the distributor located upstream.
  • the downstream circumferential hook of the distributor is held tight radially against the casing rail by means of the upstream circumferential hook of the ring, which comprises two coaxial annular walls, extending one inside the other, and which extend respectively inside the distributor hook and outside the casing rail. This allows to participate in the radial maintenance of the distributor vis-à-vis the housing.
  • the circumferential or tangential maintenance of the distributor can be provided by means of an anti-rotation pin which is carried by the housing and is engaged in a notch of the distributor. Its downstream axial retention is generally ensured by a split annular ring which is mounted in an annular groove of the aforementioned casing rail, which opens radially inwards.
  • the downstream circumferential hook of the distributor is in axial support downstream on the rod which is held radially in the groove of the crankcase rail by the inner walls of the hooks of the ring sectors, which extend radially inside the ring.
  • the axial stop function of this rod can be provided directly by the casing rail.
  • the opening of the hooks of the ring sectors is oriented axially upstream and receives the foil sectors which are configured so that their walls lining those of the hooks of the ring sectors.
  • the inner walls of the foil sectors are intended to extend on the radially outer faces of the inner walls of the hooks of the ring sectors, the outer walls of the foil sectors are intended to extend on the radially inner faces of the outer walls.
  • hooks of the ring sectors, and the bottom walls of the foil sectors are intended to extend on radial faces upstream of the bottom walls of the hooks of the ring sectors.
  • the inner walls of the foil sectors are interposed between the inner walls of the hooks of the ring sectors and the hooks of the distributor, or even the annular ring, the outer walls.
  • foil sectors are interposed between the outer walls of the hooks of the ring sectors and the sump rail, and the bottom walls of the foil sectors are interposed between the bottom walls of the hooks of the ring sectors and the rail of the ring sectors. casing.
  • the foil sectors are made of sheet metal and make it possible to avoid direct contact between the hooks of the ring sectors and the casing rail, which makes it possible on the one hand to protect the latter against frictional wear and other to protect it thermally from the ring which can be very hot in operation because of its proximity to the combustion gases flowing in the turbine vein.
  • the longitudinal edges of the circumferential ends of two adjacent sectors of the foil are opposite one another and are separated from each other by a circumferential clearance.
  • the circumferential gaps between the foil sectors are aligned axially with the circumferential gaps between the ring sectors, and in particular with the circumferential gaps between the hooks of the ring sectors at which it is not possible to mount tabs of the aforementioned type for reasons of space in particular. Hot gases can thus pass through the circumferential gaps between the hooks of the ring sectors and between the foil sectors and heat the casing rail, which may reduce its service life.
  • the present invention aims in particular to provide a simple, effective and economical solution to this need by improving the thermal protection of the crankcase rail in the aforementioned case.
  • the present invention thus proposes a turbomachine module, comprising a mobile wheel rotatably mounted inside a housing of the module and surrounded by a sectorized sealing ring which comprises an annular row of ring sectors arranged so that that circumferential end edges of two adjacent sectors are substantially facing each other, each ring sector having at least one circumferential hook which is configured to cooperate with an annular fastening rail of the housing, the module further comprising an annular sectorized protection foil which is interposed between the hooks of the ring sectors and the crankcase rail and which comprises an annular array of sectors of foil arranged so that circumferential end edges of two adjacent sectors are substantially opposite one another, characterized in that the number of ring sectors is equal to the number of foil sectors and the foil sectors comprise rotational positioning and / or locking means configured so that the edges of the circumferential ends of the foil sectors are not aligned with the edges of the circumferential ends of the ring sectors along the longitudinal axis. of the module.
  • the invention makes it possible to better protect the casing rail because the gases that could pass between the edges of the circumferential ends of the ring sectors would then be blocked by the foil sectors (because of their angular offset with respect to ring sectors) and would not reach the crankcase rail.
  • the present invention also relates to a turbomachine, comprising at least one module as described above.
  • the present invention finally relates to an annular sectorized protection foil for a module as described above, comprising an annular row of foil sectors, in which each foil sector has a generally U-shaped or C-shaped cross-section, of which aperture is oriented axially, and comprises a median bottom wall which connects two respectively radially inner and outer coaxial annular walls, said inner walls comprising radial notches substantially in their middle, which open on free circumferential edges of the sectors.
  • FIGs 1 and 2 represent a turbine 10, here low-pressure, of a turbomachine such as a turbojet engine or an airplane turboprop, this turbine having several stages (only one of which is shown here) each comprising a distributor 12 formed of a row annular fixed vanes carried by a casing 14 of the turbine, and a impeller 16 mounted downstream of the distributor 12 and rotating in a ring 18 attached to the casing 14.
  • a turbomachine such as a turbojet engine or an airplane turboprop
  • the ring 18 is sectored and formed of several sectors which are worn circumferentially end to end by the casing 14 of the turbine.
  • Each ring sector 18 comprises a frustoconical wall 20 and a block 22 of abradable material fixed by soldering and / or welding on the radially inner surface of the wall 20, this block 22 being of the honeycomb type and intended for wear by friction on external annular wipers 24 of the vanes of the wheel 16 to minimize the radial clearances between the wheel and the ring sectors 18.
  • Each ring sector 18 comprises, at its upstream end, a circumferential hook 32 with a C or U section whose opening opens upstream and which is engaged axially downstream on a cylindrical hook 34 facing downstream of the distributor 12 located upstream of the ring sectors 18, on the one hand, and on a cylindrical rail 36 of the casing 14 on which is hooked this distributor, on the other hand.
  • each ring sector 18 comprises two circumferential walls 38 and 40 extending upstream, radially outer and radially inner respectively, which are interconnected at their upstream ends by a substantially radially medial bottom wall 42 , and which respectively extend radially outside and inside the rail 36, the inner wall 40 holding the hook 34 of the distributor radially against the rail 36.
  • the circumferential maintenance of the distributor 12 is provided by means of an anti-rotation pin 44 which is carried by the housing 14 and is engaged in a notch of the distributor 12. Its downstream axial retention is ensured by an annular ring 46 which is mounted in an annular groove 48 of the rail 36, which opens radially inwards.
  • the hook 34 of the distributor 12 bears axially downstream on the rod 46 which is held radially in the groove of the casing rail by the inner wall 40, which extends radially inside the rod 46. , the axial stop function of the rod 46 can be provided directly by the casing rail 36.
  • the downstream ends of the ring sectors 18 are clamped radially on a cylindrical rail 30 of the housing by the distributor located downstream of the ring sectors. Ring sectors 18 are supported radially outwardly on a radially inner cylindrical face of the rail 30 of the housing, and inwardly on a radially outer cylindrical face of a cylindrical rim 28 of the downstream distributor.
  • annular foil 50 which is sectored and comprises an annular row of circumferentially end-to-end foil sectors. It has a generally C or U-shaped cross section and comprises two coaxial annular walls, respectively internal 52 and external 54, interconnected by a median bottom wall 56.
  • the foil 50 is mounted on the housing rail 36 and on the hook 34 of the distributor 12 so that the inner walls 52 of the foil sectors 50 are interposed between the inner walls 40 of the hooks 32 of the ring sectors 18, on the one hand, and the hooks 34 of the distributor 12 and the ring ring 46, on the other hand, that the outer walls 54 of the foil sectors are interposed between the outer walls 38 of the hooks 32 of the ring sectors and the casing rail 36, and that the bottom walls 56 of the foil sectors are interposed between the bottom walls 42 of the hooks of the ring sectors and the casing rail 36 ( figure 2 ).
  • the foil sectors 50 are made of sheet metal and make it possible to avoid direct contact between the hooks 32 of the ring sectors 18 and the casing rail 36, which makes it possible on the one hand to protect the latter against frictional wear. and on the other hand to thermally protect it from the ring which can be very hot in operation because of its proximity to the combustion gases flowing in the turbine duct.
  • the longitudinal edges 58 of the circumferential ends of the ring sectors 18 are separated from each other by circumferential clearances through which hot gases from the turbine stream can pass.
  • the longitudinal edges 60 of the circumferential ends of the foil sectors 50 are also separated from each other by circumferential gaps that are aligned axially with the clearances between the ring sectors 18.
  • the aforementioned hot gases can pass through the circumferential gaps between the hooks 32 of the ring sectors 18 and between the foil sectors 50 and heating the casing rail 36 (arrow 62 in FIG. figure 2 ), which may reduce its life.
  • the tabs 64 which are mounted between the longitudinal edges 58 of the circumferential ends of the ring sectors 18 do not extend to the hooks 32 of the ring sectors 18 and do not prevent the passage of gas at this point. level.
  • figure 4 represents an embodiment of the invention in which the foil sectors 50 are arranged in staggered relation with the ring sectors 18. The gases which are capable of passing through the circumferential gaps between the hooks 32 of the sectors 18 are then blocked by the sectors of foil 50 and do not reach the sump rail 36 which has a longer life.
  • the walls 38, 40 of the ring sectors 18 are "pre-arched" with respect to the casing rail 36, that is to say that they have radii curvature greater than that of the casing rail 36, which allows to mount them with some radial prestressing on the rail. Due to this pre-bending, the ring sector 18 represented in figure 5 has support areas C1, C2, C3 little extended on the rail 36.
  • the median portion of the inner face of the wall 38 of the sector 18 is supported C1 on the outer face of the rail 36 (via the walls 54 of the foil sectors 50 when they are used) and the end portions of the outer face of the wall 40 are supported at C1 and C3 on the internal face of the rail 36 or on the hook 34 of the distributor 12 and the ring 46, as in the example shown (via the walls 52 of the foil sectors 50 when they are used).
  • FIGS. Figures 6 to 8 proposes a particular conformation of the foil sectors and in particular of their internal walls 52. In the absence of such a conformation, the risk would be to prematurely wear the sectors of foil 50 and to create zones of initiation of creeks in the support zones C1, C3.
  • each clicking sector 50 comprises a notch 66 substantially in its middle.
  • This notch 66 opens on the free and upstream circumferential edge of the wall 52 and here has a general V shape.
  • Each notch 66 has a circumferential extent of between 30 and 60% of the circumferential extent of the foil sector 50 and a dimension longitudinal between 10 and 50% of the longitudinal dimension of the foil sector 50.
  • the foil sectors 50 may furthermore be equipped with means for locking in rotation.
  • these locking means comprise a notch 70 formed at a circumferential end of the inner wall 52 of each foil sector 50.
  • This notch 70 opens on the free and upstream circumferential edge of the wall 52 as well as on the longitudinal edge of the corresponding end of the wall. It has a general rectangular shape here.
  • Each notch 70 has a circumferential extent of between 10 and 30% of the circumferential extent of the foil section 50 and a longitudinal dimension of between 20 and 70% of the longitudinal dimension of the foil section 50.
  • the notch 70 of each foil sector 50 is aligned radially with a notch 72 of the inner wall 40 of the hook of the ring sector 18, which is located substantially in the middle of this wall.
  • the notches 70, 72 are intended to receive a lug (not shown) of the distributor 12 to immobilize in rotation the ring sector 18 and the foil sector vis-a-vis the other as well as with respect to the casing 14.
  • FIGS. 9 and 10 represent an alternative embodiment of the locking means which comprise here a tab 74 foldable.
  • a tab 74 is here carried by the outer wall 54 of each foil sector 50 '. It is located substantially in the middle of the sector 50 'and extends at rest radially outwards and downstream. Its outer radial end 76 is intended to be deformed and folded radially inwards so as to engage in an outer radial slot 78 of the outer wall 38 of the hook of the ring sector 18 '. This ensures immobilization in rotation of the foil sector 50 'vis-à-vis the ring sector 18'.
  • each foil sector may comprise more than one anti-rotation lug of this type.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)
  • Supercharger (AREA)
  • Centrifugal Separators (AREA)
EP15757535.8A 2014-08-14 2015-08-04 Module de turbomachine Active EP3180497B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1457829A FR3024883B1 (fr) 2014-08-14 2014-08-14 Module de turbomachine
PCT/FR2015/052151 WO2016024060A1 (fr) 2014-08-14 2015-08-04 Module de turbomachine

Publications (2)

Publication Number Publication Date
EP3180497A1 EP3180497A1 (fr) 2017-06-21
EP3180497B1 true EP3180497B1 (fr) 2019-10-02

Family

ID=51862465

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15757535.8A Active EP3180497B1 (fr) 2014-08-14 2015-08-04 Module de turbomachine

Country Status (9)

Country Link
US (1) US10344610B2 (ja)
EP (1) EP3180497B1 (ja)
JP (1) JP6625611B2 (ja)
CN (1) CN106574511B (ja)
BR (1) BR112017002041B1 (ja)
CA (1) CA2956882C (ja)
FR (1) FR3024883B1 (ja)
RU (1) RU2700847C2 (ja)
WO (1) WO2016024060A1 (ja)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3022944B1 (fr) * 2014-06-26 2020-02-14 Safran Aircraft Engines Ensemble rotatif pour turbomachine
KR101675277B1 (ko) * 2015-10-02 2016-11-11 두산중공업 주식회사 가스터빈의 팁간극 조절 조립체
FR3058458B1 (fr) * 2016-11-09 2020-11-20 Safran Aircraft Engines Etage de turbine de turbomachine pourvu de moyens d'etancheite
US11199104B2 (en) * 2017-05-15 2021-12-14 Raytheon Technologies Corporation Seal anti-rotation
EP3412871B1 (en) * 2017-06-09 2021-04-28 Ge Avio S.r.l. Sealing arrangement for a turbine vane assembly
FR3083563B1 (fr) 2018-07-03 2020-07-24 Safran Aircraft Engines Module d'etancheite de turbomachine d'aeronef
FR3084103B1 (fr) * 2018-07-18 2020-07-10 Safran Aircraft Engines Ensemble d'etancheite pour un rotor de turbine de turbomachine et turbine de turbomachine comprenant un tel ensemble
FR3100838B1 (fr) * 2019-09-13 2021-10-01 Safran Aircraft Engines Anneau d’etancheite de turbomachine
FR3113923B1 (fr) * 2020-09-04 2023-12-15 Safran Aircraft Engines Turbine pour turbomachine comprenant des clinquants de protection thermique
FR3140112A1 (fr) * 2022-09-22 2024-03-29 Safran Aircraft Engines Amélioration de l’étanchéité dans une turbine de turbomachine

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US5201846A (en) * 1991-11-29 1993-04-13 General Electric Company Low-pressure turbine heat shield
FR2743603B1 (fr) * 1996-01-11 1998-02-13 Snecma Dispositif de jonction de segments d'un distributeur circulaire a un carter de turbomachine
US6076835A (en) * 1997-05-21 2000-06-20 Allison Advanced Development Company Interstage van seal apparatus
FR2819010B1 (fr) * 2001-01-04 2004-05-28 Snecma Moteurs Secteur d'entretoise de support d'anneau de stator de la turbine haute pression d'une turbomachine avec rattrapage de jeux
US7207771B2 (en) * 2004-10-15 2007-04-24 Pratt & Whitney Canada Corp. Turbine shroud segment seal
FR2941488B1 (fr) * 2009-01-28 2011-09-16 Snecma Anneau de turbine a encoche anti-rotation
FR2961849B1 (fr) * 2010-06-28 2013-07-05 Snecma Etage de turbine dans une turbomachine
GB201105788D0 (en) * 2011-04-06 2011-05-18 Rolls Royce Plc Stator vane assembly
US8651497B2 (en) * 2011-06-17 2014-02-18 United Technologies Corporation Winged W-seal
US8899914B2 (en) * 2012-01-05 2014-12-02 United Technologies Corporation Stator vane integrated attachment liner and spring damper
US20130177411A1 (en) * 2012-01-05 2013-07-11 General Electric Company System and method for sealing a gas path in a turbine
FR2989724B1 (fr) * 2012-04-20 2015-12-25 Snecma Etage de turbine pour une turbomachine
US9828865B2 (en) * 2012-09-26 2017-11-28 United Technologies Corporation Turbomachine rotor groove
FR3026430B1 (fr) * 2014-09-29 2020-07-10 Safran Aircraft Engines Roue de turbine dans une turbomachine

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Also Published As

Publication number Publication date
BR112017002041B1 (pt) 2022-08-09
CN106574511B (zh) 2019-04-12
US20170218785A1 (en) 2017-08-03
RU2017103314A (ru) 2018-09-14
RU2700847C2 (ru) 2019-09-23
WO2016024060A1 (fr) 2016-02-18
CA2956882A1 (fr) 2016-02-18
JP2017529481A (ja) 2017-10-05
JP6625611B2 (ja) 2019-12-25
FR3024883B1 (fr) 2016-08-05
FR3024883A1 (fr) 2016-02-19
CN106574511A (zh) 2017-04-19
RU2017103314A3 (ja) 2019-02-19
EP3180497A1 (fr) 2017-06-21
BR112017002041A2 (pt) 2018-01-30
CA2956882C (fr) 2022-03-15
US10344610B2 (en) 2019-07-09

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