EP2300688B1 - Turbine haute pression d'une turbomachine avec montage ameliore du boitier de pilotage des jeux radiaux d'aubes mobiles - Google Patents

Turbine haute pression d'une turbomachine avec montage ameliore du boitier de pilotage des jeux radiaux d'aubes mobiles Download PDF

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Publication number
EP2300688B1
EP2300688B1 EP09753846.6A EP09753846A EP2300688B1 EP 2300688 B1 EP2300688 B1 EP 2300688B1 EP 09753846 A EP09753846 A EP 09753846A EP 2300688 B1 EP2300688 B1 EP 2300688B1
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EP
European Patent Office
Prior art keywords
pressure turbine
high pressure
annular
shock absorbing
fixed
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
EP09753846.6A
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German (de)
English (en)
French (fr)
Other versions
EP2300688A1 (fr
Inventor
Alain Dominique Gendraud
Delphine Leroux
Jean-Luc Le Strat
Pascal Tatiossian
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication of EP2300688A1 publication Critical patent/EP2300688A1/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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the present invention relates to a high-pressure turbine in a turbomachine such as an airplane turbojet or turboprop.
  • a turbomachine high-pressure turbine comprises at least one stage comprising a distributor formed of an annular row of stationary vanes for rectification and a rotor wheel rotatably mounted downstream of the distributor in a cylindrical or frustoconical assembly of ring sectors arranged butt circumferentially. These ring sectors comprise at their upstream and downstream ends hooking means on an annular support which is fixed to an outer casing of the turbine.
  • the radial clearances between the moving blades of the wheel and the ring sectors must be minimized to improve the efficiency of the turbomachine while avoiding friction of the ends of the blades on the ring sectors, which would result in wear of these parts. extremes and degradation of the efficiency of the turbomachine at all operating speeds.
  • FIG. Figures 1 and 1A An example of mounting of the control box on the outer casing of the turbomachine high-pressure turbine is shown in FIG. Figures 1 and 1A .
  • a wall 400 of the control box 40 is fixed to the outer casing 22 of the turbine 10 at two diametrically opposite points via a threaded ring 45.
  • control box is subjected to vibrations that can be damaging at its attachment points. Indeed, it appears a risk of cracks at its attachment points.
  • the object of the invention is then to propose a solution which makes it possible to avoid troublesome solicitations at the fixing points of the housing of piloting to the outer casing, during the operation of the high-pressure turbine of a turbomachine.
  • the document EP-17-892153 describes a "V" sheet for fixing a game control box.
  • control box that can be used in the invention is that disclosed in the embodiment of the patent application FR 2,865,237 .
  • the content of this earlier application is therefore fully included in this application.
  • a dissipation of the energy of the vibrations of the case generated by modes of excitations of the turbomachine by combination of friction at the level of the axial support and braking of the control box is provided by the bending of the casing. additional annular element.
  • the damping annular element is a metal section obtained by machining or sheet metal forming.
  • the geometric shape of the damping annular element is composed of a continuous ring fixed to the annular support and extended by a plurality of identical blades, regularly spaced and inclined with respect to the ring and whose curved end constitutes the pressing by pressure with the upstream of the box.
  • the number of blades of the annular damping element is preferably equal to a multiple of eighteen. Studies have shown that such a choice, as for example a number of seventy-two blades distributed regularly circumferentially for a diameter of 0.680m gave full satisfaction.
  • control box and the damping annular element are made of the same material.
  • an anti-wear material is interposed in the bearing zone between the damping annular element and the upstream of the housing in order to reduce the frictional wear of the damper or housing.
  • a layer of anti-wear material is deposited on the upstream of the housing in the bearing zone with the damping element.
  • the damping element consists of at least two angular sectors fixed end-to-end and forming the complete annular shape of the damper.
  • the damping element consists of a number of two, six or eighteen angular sectors fixed end to end and realizing the complete annular shape of the damper.
  • the annular damping element is fixed to the annular support by means of screws which are also used for fixing axial abutment spacer pieces. These parts are usually called stop plates.
  • the metal profile may comprise at least one continuous crown angular sector extended by a plurality of identical blades, regularly spaced and inclined relative to the crown sector and whose end is bent.
  • the invention finally relates to a turbomachine comprising a high-pressure turbine described above.
  • the figure 1 schematically represents a portion of a turbomachine such as a turbojet or an airplane turboprop comprising a high-pressure turbine 10 arranged downstream of a combustion chamber 12, and upstream of a low-pressure turbine 14 of the turbomachine.
  • a turbomachine such as a turbojet or an airplane turboprop comprising a high-pressure turbine 10 arranged downstream of a combustion chamber 12, and upstream of a low-pressure turbine 14 of the turbomachine.
  • the combustion chamber 12 comprises a wall of external revolution 50 connected at its downstream end to a radially inner end of a frustoconical wall 58 which has at its radially outer end a radially outer annular flange 60 for fixing on a corresponding annular flange 62 of an outer casing 64 of the chamber.
  • the high-pressure turbine 10 comprises a single turbine stage comprising a distributor 16 formed of an annular row of stationary vanes for rectification, and a vane wheel 18 rotatably mounted downstream of the distributor 16.
  • the low-pressure turbine 14 comprises several turbine stages, each of these stages also comprising a distributor and a paddle wheel, only the distributor 47 of the upstream low-pressure stage being visible in FIG. figure 1 .
  • the impeller 18 of the high-pressure turbine 10 rotates within a substantially cylindrical assembly of ring sectors 20 which are circumferentially end-to-end and suspended from an outer turbine casing 22 via a annular support 24.
  • This annular support 24 comprises at its inner periphery means 26 for attaching the ring sectors 20 and comprises a wall 28 which extends upstream and outwards and which is connected at its radially outer end to a radially outer annular flange 30 for fixing the outer casing of turbine 22.
  • the flange 60 is interposed axially between the flange 30 and the flange 62 of the turbine casing 22 and is clamped axially between these flanges by appropriate means of the screw-nut type 7.
  • the annular support 24 comprises at its inner periphery two radial annular walls 34, 36, respectively upstream and downstream, which are connected to one another by a cylindrical wall 38.
  • the radial walls 34, 36 comprise at their radially internal ends downstream cylindrical flanges 90 which cooperate with circumferential hooks 92, 94 provided at the upstream and downstream ends of the ring sectors 20.
  • An annular locking member 96 with a C-section is engaged axially from downstream on the downstream cylindrical flange 90 of the support and on the downstream hooks 94 of the ring sectors to ensure the locking of the assembly.
  • the wall 28 of the annular support 24 defines with the frustoconical wall 58 of the chamber an annular enclosure 80 which is supplied with ventilation and cooling air through orifices 82 formed in the frustoconical wall 58. Unrepresented orifices are formed in the wall radial upstream 34 of the annular support 24 to establish fluid communication between the enclosure 80 and an annular cavity 86 for cooling the ring sectors 20 delimited externally by the cylindrical wall 38 of the support annular.
  • the outer wall 66 of the distributor comprises at each of its upstream and downstream ends an annular groove 74 opening radially outwards.
  • Annular sealing gaskets 76 are housed in these grooves 74 and cooperate with cylindrical ribs 78 formed on the frustoconical wall 58 and on the upstream radial wall 34 of the annular support 24, respectively, to prevent the passage of gas from the flow duct.
  • the turbine radially outwardly of the outer wall 66, and conversely, the passage of air from the enclosure 80 radially inward in the vein of the turbine.
  • This device D comprises a circular control box 40 surrounding the fixed ring 20, and more precisely the annular support 24.
  • control unit 40 is intended to cool or heat the upstream fins 240 and downstream 242 of the annular support 24 by discharge (or impact) of air thereon. Under the effect of this air discharge, the annular support 24 retracts or expands, which decreases or increases the diameter of the fixed ring segments 20 of the turbine in order to adjust the clearance at the top of blades 18.
  • the control box 40 supports at least three annular air circulation ramps 41, 42 and 43 which surround the annular support 24 of the fixed ring assembly. These ramps are spaced axially from one another and are substantially parallel to each other. They are arranged on either side of the lateral faces of each of the fins 240, 242 whose shape they roughly conform to.
  • the control unit 40 also comprises an unrepresented air collection tube for supplying air to the air circulation ramps 41, 42 and 43.
  • This air collection tube surrounds the ramps 41, 42 and 43 and supplies them with air. air through air ducts 44.
  • such a control box 40 consists of two half-shells clamped together and is fixed to the outer casing 22 by means of threaded rings 45 at two diametrically opposite points ( figure 1 ).
  • the inventors have found that during the operation of the turbomachine comprising the high pressure turbine 10 as illustrated above, there could be a risk of occurrence of cracks at the attachment points 45. They have shown that this was due to the fact that the control box 40 is subjected to harmful vibrations which can be damaging at its attachment points 45.
  • annular element 5 with predetermined flexibility is implanted in the cavity delimited by the annular support 24 and the outer casing 22 upstream of the control box 40 ( figures 2 and 4 ).
  • This annular element 5 with predetermined flexibility and support with given pressure thus constitutes a damper of at least a portion of the vibrations of the control box 40 generated during operation of the turbine.
  • the damping thus provided according to the invention is a dissipation of energy of the vibrations of the case 40 generated during the operation of the turbomachine by combination of friction at the level of the axial support 51 and braking of the control box 40 thanks to the bending the annular element between its ends 51, 52 during operation of the turbomachine.
  • the damping element 5 improves the energy dissipation and the dynamic damping of the ramps 41, 42, 43 for controlling the radial clearance of the rotary vanes 18.
  • the damping element 5 thus provided makes it possible to avoid the vibratory mechanical stresses of the control box 40 without having to modify its mode of attachment to the outer casing 22 ( figure 4 ).
  • each angular sector constituting the damping element 5 is a metal section obtained by forming sheet metal.
  • the geometric shape of the damping element 5 is composed of a continuous ring 51 fixed to the annular support and extended by a plurality of identical blades 510, regularly spaced and inclined with respect to the ring 51 and whose end 52 bent constitutes pressure support with the upstream 401 of the housing.
  • These blades 510 which make it possible to obtain pressure support on the upstream end of the housing can for example be made in a continuous metal section by machining of the "saw-cut" type, schematized by the spacing 53 between two consecutive blades 510. .
  • the number of blades 510 around the circumference can be adapted by changing the width of the kerf made.
  • the number of blades of the damping element 5 is equal to a multiple of eighteen. For example, a number of seventy-two blades is desirable. It is also possible to implant thirty-six or one hundred and forty-four blades.
  • the control unit 40 and the damping element 5 are preferably made of the same material. It may be a Hastelloy type alloy X.
  • an anti-wear material into the zone d. 52 support between the damping element 5 and the upstream 401 of the housing 40.
  • It may be a Tribaloy type alloy 800 or Tribaloy 800 with CoCrAlYSi.
  • the intercalated material may advantageously be a layer of anti-wear material deposited on the upstream 401 of the housing 40 in the bearing zone 52 with the damping element 5.
  • the damping element 5 consists of at least two angular sectors fixed end to end and forming the complete annular shape of the damper.
  • a minimum of two angular sectors meets the mounting and differential expansion constraints encountered at attachment zone 51 with the annular support 24 of the high pressure turbine.
  • the number of angular sectors can be increased as desired. It may for example consist of a number of two, six or eighteen angular sectors fixed end to end and realizing the complete annular shape of the damper.
  • a number of eighteen identical angular sectors is particularly advantageous since it allows the attachment of each of them to the annular support by means of screws / nuts. which are also used for fixing axial stop pieces of the spacers 88. These parts are generally called stop plates.
  • the number of angular sectors and the number of blades must be a multiple of the number of fixing screws in order to have identical sectors.
  • any embodiment of angular sectors that allows their attachment by screw / nut systems 29 already existing to fix the axial abutment pieces is advantageous because no additional fastening means of the damping element is to be expected in the context of the 'invention.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP09753846.6A 2008-05-28 2009-05-25 Turbine haute pression d'une turbomachine avec montage ameliore du boitier de pilotage des jeux radiaux d'aubes mobiles Active EP2300688B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0853471A FR2931872B1 (fr) 2008-05-28 2008-05-28 Turbine haute pression d'une turbomachine avec montage ameliore du boitier de pilotage des jeux radiaux d'aubes mobiles.
PCT/EP2009/056279 WO2009144191A1 (fr) 2008-05-28 2009-05-25 Turbine haute pression d'une turbomachine avec montage ameliore du boitier de pilotage des jeux radiaux d'aubes mobiles

Publications (2)

Publication Number Publication Date
EP2300688A1 EP2300688A1 (fr) 2011-03-30
EP2300688B1 true EP2300688B1 (fr) 2013-08-28

Family

ID=40158650

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09753846.6A Active EP2300688B1 (fr) 2008-05-28 2009-05-25 Turbine haute pression d'une turbomachine avec montage ameliore du boitier de pilotage des jeux radiaux d'aubes mobiles

Country Status (9)

Country Link
US (1) US8662828B2 (zh)
EP (1) EP2300688B1 (zh)
JP (1) JP5615808B2 (zh)
CN (1) CN102046926B (zh)
BR (1) BRPI0912994B1 (zh)
CA (1) CA2725864C (zh)
FR (1) FR2931872B1 (zh)
RU (1) RU2503822C2 (zh)
WO (1) WO2009144191A1 (zh)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2921410B1 (fr) * 2007-09-24 2010-03-12 Snecma Organe de verrouillage de secteurs d'anneau sur un carter de turbomachine, comprenant des moyens permettant sa prehension
CN104956035B (zh) * 2013-02-08 2017-07-28 通用电气公司 基于抽吸装置的主动间隙控制系统
US9976436B2 (en) * 2013-03-28 2018-05-22 United Technologies Corporation Movable air seal for gas turbine engine
FR3038655B1 (fr) 2015-07-06 2017-08-25 Snecma Ensemble comprenant un carter rainure et des moyens de refroidissement du carter, turbine comprenant ledit ensemble, et turbomachine comprenant ladite turbine
JP6563312B2 (ja) * 2015-11-05 2019-08-21 川崎重工業株式会社 ガスタービンエンジンの抽気構造
FR3081027B1 (fr) * 2018-05-09 2020-10-02 Safran Aircraft Engines Turbomachine comportant un circuit de prelevement d'air
KR102579798B1 (ko) * 2018-10-15 2023-09-15 한화에어로스페이스 주식회사 터보기기
FR3096395B1 (fr) * 2019-05-21 2021-04-23 Safran Aircraft Engines Turbine pour une turbomachine, telle qu’un turboréacteur ou un turbopropulseur d’avion
US11788425B2 (en) * 2021-11-05 2023-10-17 General Electric Company Gas turbine engine with clearance control system
FR3140115A1 (fr) * 2022-09-22 2024-03-29 Safran Aircraft Engines Pièce d'amortissement des déformations d'un carter de récupération d'huile, ensemble qui le comporte et turbomachine ainsi équipée

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US3759038A (en) 1971-12-09 1973-09-18 Westinghouse Electric Corp Self aligning combustor and transition structure for a gas turbine
GB2129880A (en) * 1982-11-09 1984-05-23 Rolls Royce Gas turbine rotor tip clearance control apparatus
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GB2310255B (en) * 1996-02-13 1999-06-16 Rolls Royce Plc A turbomachine
FR2766231B1 (fr) * 1997-07-18 1999-08-20 Snecma Dispositif d'echauffement ou de refroidissement d'un carter circulaire
FR2816352B1 (fr) * 2000-11-09 2003-01-31 Snecma Moteurs Ensemble de ventilation d'un anneau de stator
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
US6732530B2 (en) 2002-05-31 2004-05-11 Mitsubishi Heavy Industries, Ltd. Gas turbine compressor and clearance controlling method therefor
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FR2922589B1 (fr) 2007-10-22 2009-12-04 Snecma Controle du jeu en sommet d'aubes dans une turbine haute-pression de turbomachine

Also Published As

Publication number Publication date
EP2300688A1 (fr) 2011-03-30
FR2931872B1 (fr) 2010-08-20
CN102046926A (zh) 2011-05-04
WO2009144191A1 (fr) 2009-12-03
RU2010153596A (ru) 2012-07-10
FR2931872A1 (fr) 2009-12-04
US8662828B2 (en) 2014-03-04
JP5615808B2 (ja) 2014-10-29
RU2503822C2 (ru) 2014-01-10
CN102046926B (zh) 2014-11-05
JP2011522150A (ja) 2011-07-28
BRPI0912994A2 (pt) 2015-10-13
CA2725864C (fr) 2016-07-12
BRPI0912994B1 (pt) 2019-11-26
US20110076135A1 (en) 2011-03-31
CA2725864A1 (fr) 2009-12-03

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