EP1840339B1 - Dispositif de fixation de secteurs d'anneau autour d'une roue de turbine dans une turbomachine - Google Patents

Dispositif de fixation de secteurs d'anneau autour d'une roue de turbine dans une turbomachine Download PDF

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Publication number
EP1840339B1
EP1840339B1 EP07290322.2A EP07290322A EP1840339B1 EP 1840339 B1 EP1840339 B1 EP 1840339B1 EP 07290322 A EP07290322 A EP 07290322A EP 1840339 B1 EP1840339 B1 EP 1840339B1
Authority
EP
European Patent Office
Prior art keywords
ring
upstream
wall
fixed element
radially
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
EP07290322.2A
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German (de)
English (en)
French (fr)
Other versions
EP1840339A1 (fr
Inventor
Didier Durand
Dominique Gehan
Valérie Anne Gros
Didier Sotto-Lamy
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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Publication date
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Publication of EP1840339A1 publication Critical patent/EP1840339A1/fr
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Publication of EP1840339B1 publication Critical patent/EP1840339B1/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • 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 device for fixing ring sectors around a turbine wheel in a turbomachine, such as in particular an airplane turbojet or turboprop engine.
  • a turbomachine turbine comprises a plurality of stages, each comprising a distributor formed of an annular row of stationary vanes carried by a casing of the turbine and a rotatably mounted wheel downstream of the distributor in a cylindrical or frustoconical envelope formed by ring sectors. circumferentially attached end-to-end on the turbine casing (see for example the document DE 101 22 464 ).
  • the ring sectors comprise at their upstream ends circumferential flanges engaged with a small axial clearance in a radially inner annular groove of an annular housing rail and held radially in this groove by an annular locking member with a C-section which is engaged axially from upstream on the casing rail and on the circumferential edges of the ring sectors. These sectors are held axially by abutment of their circumferential edges on upstream and downstream faces respectively of the groove of the rail.
  • the flanges of the ring sectors are "convergecambrés" relative to the crankcase rail and the locking member, that is to say that the edges of the ring sectors have a radius of curvature greater than that of the rail of the casing and of the locking member, which makes it possible to mount the flanges of the ring sectors with a certain radial prestressing between the bottom of the groove of the rail and the locking member and thus to limit the axial displacements of the flanges ring areas in the gorge.
  • the edges of the ring sectors can, by moving downstream in the groove, disengage from the locking member, which results in a tilting of the ring sectors to the axis of the turbine and a risk of contact between the ring sectors and the turbine wheel, may cause destruction of the ring sectors and the wheel.
  • the invention aims in particular to provide a simple, effective and economical solution to this problem.
  • each ring sector comprising a frustoconical wall which carries a block of abradable material fixed on its inner surface and which comprises its upstream end a circumferential rim engaged in a radially inner annular groove of an annular housing rail and held radially in this groove by a ring-shaped annular locking member which is engaged axially from upstream on the casing rail and on the circumferential edges of the ring sectors, characterized in that each ring sector comprises at its downstream end an insert and fixed on the frustoconical wall and on the block of abradable material of the ring sector, this piece being able to come in axial support against a fixed element, the turbine to prevent the disengagement of the upstream edge of the wall of the locking member, the game ax ial between the support piece and the fixed element being less than the axial length of the support of the upstream edge of the wall on the locking member.
  • the support piece provided at the downstream end of each ring sector limits the possible retreat of the upstream edge of the ring. ring sector in the groove of the crankcase rail and avoids the disengagement of this rim of the locking member.
  • the ring sectors are maintained axially upstream by pressing their upstream flanges on a corresponding face of the crankcase rail and downstream by bearing the part on the fixed element.
  • the support piece advantageously comprises means that can come into radial abutment on the fixed element.
  • Each ring sector is thus retained in the axial direction and in the radial direction on the fixed element.
  • the support piece is fixed on the downstream end of the wall and on the block of abradable material by brazing or welding.
  • the support piece is on the ring sector, as this avoids modifying the manufacturing molds of these sectors.
  • the device according to the invention makes it possible to hang ring sectors on a casing rail independently of the wear thereof.
  • the axial clearance between the support piece and the fixed element is less than the axial length of the support of the upstream flange of the ring sector on the locking member. This ensures that the maximum recoil position of the ring sector is defined by the axial support of the workpiece on the fixed element.
  • This axial clearance between the support piece and the fixed element is for example between 0.3 and 1.2mm approximately.
  • the support piece has a section F and comprises two flanges in cylinder portion which extend downstream, one of these flanges being fixed on a radially inner surface of the wall of the ring sector and the other of these flanges can bear radially on a radially outer face of a cylindrical rim of the fixed element.
  • the fixed element of the turbomachine is advantageously constituted by a turbine distributor located downstream of the ring sector.
  • the invention also relates to a turbomachine turbine and a turbomachine, such as an airplane turbojet or turboprop, comprising at least one device as described above.
  • the invention finally relates to a ring sector for a turbomachine turbine, comprising a frustoconical wall which carries a block of abradable material fixed on its inner surface and which has at its upstream end a hooking flange on a housing, characterized in that it comprises at its downstream end an axial bearing piece and radial attached and fixed on the wall and on the block of abradable material of the ring sector.
  • the support piece is preferably fixed by welding or brazing on the block of abradable material and on the downstream end of the wall of the ring sector.
  • the turbine 10 partially shown in figure 1 comprises several stages each comprising a distributor 12, 13 formed of an annular row of fixed blades 14 carried by a housing 16 of the turbine, and a wheel 18 mounted downstream of the distributor 12, 13 and rotating in a substantially frustoconical casing formed by ring sectors 20 carried circumferentially end to end by the casing 16 of the turbine.
  • the distributors 12, 13 comprise walls of external revolution 22 and internal (not visible), respectively, which delimit between them the annular stream of gas flow in the turbine and between which the vanes extend radially 14.
  • the distributor fixing means comprise at least one outer cylindrical rim 24 oriented upstream and intended to be engaged in an annular groove 26 facing downstream of the casing 16.
  • the wheels 18 are carried by a turbine shaft (not shown). They comprise external and internal (not visible) ferrules 28, respectively, the outer ferrule 28 of each wheel comprising external annular ribs 30 externally surrounded with a small clearance by the ring sectors 20.
  • Each ring sector 20 comprises a frustoconical wall 32 and a block 34 of abradable material fixed by soldering and / or welding on the radially inner surface of the wall 32, this block 34 being of the honeycomb type and intended for wear by friction on the ribs 30 of the wheel to minimize the radial clearances between the wheel and the ring sectors 20.
  • the downstream ends of the ring sectors 20 are engaged from upstream in an annular space 36 delimited by a cylindrical rim 38 facing upstream of the outer wall 22 of the distributor 13 located downstream of the ring sectors, on the one hand, and by a cylindrical rim 39 of the casing on which this distributor is hooked, on the other hand.
  • the ring sectors 20 are held radially at their downstream ends by radial support towards the outside of their walls 32 on a radially inner cylindrical face of the flange 39 of the casing, and by radial support towards the inside of their blocks 34 of material abradable on a radially outer cylindrical face of the cylindrical rim 38 of the distributor.
  • the walls 32 of the ring sectors each comprise at their downstream ends a tab 40 extending axially downstream and intended to be engaged in a corresponding cavity 42 of the downstream distributor 13 to immobilize in rotation the ring sectors 20 around of the turbine axis.
  • the frustoconical walls 32 of the ring sectors 20 also comprise at their upstream ends cylindrical rims 44 facing upstream which are engaged with a small axial clearance in a radially inner annular groove 46 of an annular rail 48 of the casing 16. These flanges 44 are held radially in this groove by means of a locking member 50 formed of a split ring C section engaged from upstream on the annular rail 48 of the housing and on the upstream edges 44 of the sectors of ring.
  • the locking member 50 comprises two cylindrical branches 52 and 54 extending downstream, radially outer and radially inner respectively, which are interconnected at their upstream ends by a radial wall 56, and which are respectively applied to a radially outer cylindrical face of the rail 48 and on the circumferential edges 44 of the ring sectors 20.
  • the locking member 50 is prevented from moving axially upstream by axial support of its radial wall 56 on a radial annular flange 58 of the outer wall 22 of the distributor 12 located upstream of the sectors. ring 20.
  • the radius of curvature of the locking member 50 and of the rail 48 is less than that of the flanges 44 of the ring sectors 20, which makes it possible to mount with a certain radial prestress the flanges 44 of the ring sectors in the groove. 46 of the rail, these ring sectors being locally in radial support on the bottom of the groove and on the radially inner arm 54 of the locking member, respectively.
  • the flanges 44 of the ring sectors 20 vibrate axially and frictionally wear the upstream and downstream faces of the groove 46 of the rail.
  • the flanges 44 can move downstream by sliding on the radially inner arm 54 of the locking member, and disengage of the locking member, which can in particular, to cause the blocks 34 of abradable material to be destroyed from the ring sectors which come into contact with the annular ribs 30 of the wheel 18.
  • the invention makes it possible to provide a simple solution to this problem by means of a support piece attached and fixed on the downstream end of each ring sector.
  • the support piece 70 has a section F and comprises two flanges 72 and 74 in cylinder portion oriented downstream, radially outer and radially inner respectively, which are interconnected at their upstream ends by a radial wall 76 .
  • the radially outer face of the outer flange 72 is applied and fixed by welding or brazing on a downstream end portion of the radially inner surface of the wall 32 of the ring sector, and the radial wall 76 is applied and fixed by brazing or welding on a radial face of the block 34 of abradable material of the ring sector 20.
  • Each ring sector is held radially at its downstream end by radial support of the internal flange 74 of the part 70 on the cylindrical flange 38 of the downstream distributor, and by radial support of its wall 32 on the radially inner face of the cylindrical flange 39 of the casing 16.
  • the ring sectors are held axially at their upstream ends as previously described with reference to the figure 1 , and at their downstream ends by axial support downstream of the radial wall 76 of the part on the upstream end of the cylindrical flange 38 of the downstream distributor 13.
  • the radial walls 76 of the parts 70 are separated from the cylindrical flange 38 of the distributor 13 by an axial clearance 78 which is smaller than the axial length 80 on which the flanges 44 of the ring sectors bear on the locking member 50, so that, in the event of significant wear of the downstream face of the groove 46 of the rail, the radial walls 76 of the part 70 come to bear axially on the cylindrical flange 38 of the distributor and limit the possible retraction of the flanges 44 ring areas in the groove preventing them from disengaging from the locking member 50.
  • the axial play is for example between 0.3 and 1.2mm approximately.
  • the ring sectors 20 are held axially on the housing 16, as previously described with reference to FIG. figure 1 , that is to say by axial support of the flanges 44 of the ring sectors on the upstream and downstream faces respectively of the groove 46 of the rail.
  • the ring sectors 20 are held axially downstream by axial support of the radial walls 76 of the parts. 70 on the cylindrical rim 38 of the downstream distributor.
  • Part 70 may be attached and secured to the downstream end of an existing ring sector of the prior art. It is sufficient for this purpose to remove a downstream end portion of the block 34 of abradable material of the ring sector and to fix there instead by brazing or welding a piece 70 of axial and radial support.
  • the support piece may comprise only axial bearing means on the upstream flange 38 of the distributor, the ring sectors being held radially inwards at their downstream ends by radial support of the blocks 34 on this flange. upstream, as is the case in the prior art.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07290322.2A 2006-03-30 2007-03-14 Dispositif de fixation de secteurs d'anneau autour d'une roue de turbine dans une turbomachine Active EP1840339B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0602746A FR2899274B1 (fr) 2006-03-30 2006-03-30 Dispositif de fixation de secteurs d'anneau autour d'une roue de turbine d'une turbomachine

Publications (2)

Publication Number Publication Date
EP1840339A1 EP1840339A1 (fr) 2007-10-03
EP1840339B1 true EP1840339B1 (fr) 2018-01-03

Family

ID=37401478

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07290322.2A Active EP1840339B1 (fr) 2006-03-30 2007-03-14 Dispositif de fixation de secteurs d'anneau autour d'une roue de turbine dans une turbomachine

Country Status (9)

Country Link
US (1) US7789619B2 (ko)
EP (1) EP1840339B1 (ko)
JP (1) JP4820321B2 (ko)
KR (1) KR101369067B1 (ko)
CN (1) CN101046161B (ko)
CA (1) CA2582401C (ko)
FR (1) FR2899274B1 (ko)
HK (1) HK1107387A1 (ko)
RU (1) RU2403405C2 (ko)

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US20090014964A1 (en) * 2007-07-09 2009-01-15 Siemens Power Generation, Inc. Angled honeycomb seal between turbine rotors and turbine stators in a turbine engine
FR2923526B1 (fr) * 2007-11-13 2013-12-13 Snecma Etage de turbine ou de compresseur de turbomachine
FR2923527B1 (fr) * 2007-11-13 2013-12-27 Snecma Etage de turbine ou de compresseur, en particulier de turbomachine
FR2923525B1 (fr) * 2007-11-13 2009-12-18 Snecma Etancheite d'un anneau de rotor dans un etage de turbine
FR2930593B1 (fr) * 2008-04-23 2013-05-31 Snecma Piece thermomecanique de revolution autour d'un axe longitudinal, comprenant au moins une couronne abradable destinee a un labyrinthe d'etancheite
FR2931197B1 (fr) * 2008-05-16 2010-06-18 Snecma Organe de verrouillage de secteurs d'anneau sur un carter de turbomachine, comprenant des passages axiaux pour sa prehension
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FR2954400B1 (fr) * 2009-12-18 2012-03-09 Snecma Etage de turbine dans une turbomachine
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RU2534333C1 (ru) * 2013-11-25 2014-11-27 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Статор газовой турбины
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EP2896796B1 (fr) * 2014-01-20 2019-09-18 Safran Aero Boosters SA Stator de turbomachine axiale et turbomachine associée
FR3022578B1 (fr) * 2014-06-23 2016-06-03 Snecma Procede de realisation et de reparation d’un distributeur de turbine d’une turbomachine
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Also Published As

Publication number Publication date
JP4820321B2 (ja) 2011-11-24
EP1840339A1 (fr) 2007-10-03
FR2899274B1 (fr) 2012-08-17
KR20070098660A (ko) 2007-10-05
RU2007111675A (ru) 2008-10-10
CN101046161A (zh) 2007-10-03
US7789619B2 (en) 2010-09-07
HK1107387A1 (en) 2008-04-03
CA2582401C (fr) 2014-01-28
KR101369067B1 (ko) 2014-02-28
JP2007270836A (ja) 2007-10-18
CN101046161B (zh) 2011-06-15
RU2403405C2 (ru) 2010-11-10
US20070231127A1 (en) 2007-10-04
CA2582401A1 (fr) 2007-09-30
FR2899274A1 (fr) 2007-10-05

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