EP2817491B1 - Joint linéaire de plateforme inter- aubes, plateforme inter- aubes, rotor et turboréacteur associés - Google Patents

Joint linéaire de plateforme inter- aubes, plateforme inter- aubes, rotor et turboréacteur associés Download PDF

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Publication number
EP2817491B1
EP2817491B1 EP13710460.0A EP13710460A EP2817491B1 EP 2817491 B1 EP2817491 B1 EP 2817491B1 EP 13710460 A EP13710460 A EP 13710460A EP 2817491 B1 EP2817491 B1 EP 2817491B1
Authority
EP
European Patent Office
Prior art keywords
blade
linear
inter
lip
gasket
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
EP13710460.0A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2817491A1 (fr
Inventor
Anne-Laure RAVIER
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 Services SA
SNECMA 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.)
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Publication date
Application filed by SNECMA Services SA, SNECMA SAS filed Critical SNECMA Services SA
Publication of EP2817491A1 publication Critical patent/EP2817491A1/fr
Application granted granted Critical
Publication of EP2817491B1 publication Critical patent/EP2817491B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • 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
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms

Definitions

  • the invention relates to a linear inter-blade platform joint.
  • a linear joint is disposed between a blade and an inter-blade platform separate from the blade, and is intended to limit the flow of air between the blade and the inter-blade platform.
  • Such a seal is particularly used, but not only, in the blowers (or "fan” in English) of a jet engine, between the fan blades and the inter-blade platforms.
  • a linear inter-blade platform joint having a length, comprising a linear base for attachment to the inter-blade platform, and a linear lip extending from the linear base, said linear lip having a linear distal end portion. configured to contact a wall on the side of a lower surface or a wall on the side of an upper surface of a blade, a linear groove being formed between the linear base and the linear lip over at least a portion of the length of said joint.
  • This type of seal extends along the intrados or extrados of a blade, including the leading edge and / or the trailing edge.
  • the lip of this type of known joint does not make it possible to marry correctly the blade in the areas of sudden discontinuity or small radius of curvature, such as for example in the vicinity of the leading edge or the trailing edge of the dawn .
  • the tightness of the air stream (or gas) is imperfect, which deteriorates the performance of the turbojet engine.
  • the object of the present invention is to remedy at least substantially the disadvantage mentioned above.
  • the invention achieves its object by providing a linear seal of the aforementioned type wherein the linear distal end portion has at least one linear groove extending over at least a portion of the length of said seal.
  • joint may be used in place of "linear joint", “linear base”, “Linear lip”, “linear groove”, “linear groove” and “linear distal end portion” while designating the same entity.
  • platform can be used instead of “inter-blade platform” while designating the same entity.
  • the linear joint extends in a preferred direction, the longitudinal direction.
  • This longitudinal direction is not necessarily rectilinear, and is preferably configured to follow the contours of the dawn, especially in the vicinity of the discontinuities of the dawn.
  • the direction of the length follows the neutral fiber of the joint.
  • the length of the joint is thus defined and measured parallel to this longitudinal direction.
  • the linear lip, the linear base and the linear groove extend in this longitudinal direction.
  • the length of the lip, the length of the base and the length of the groove are defined and measured also parallel to this longitudinal direction. It is understood that the lip extends in width in a direction transverse to the longitudinal direction from the base.
  • the groove is defined between the base and the lip in the joint portions where the base and the lip form an angle less than 90 ° (eighty ten degrees of angle), the angle being measured in a section transverse to the longitudinal direction.
  • the linear distal end portion is a portion that extends in length in the longitudinal direction, and in width a distance of about 20% of the width of the lip. It is therefore understood that the linear distal end portion is disposed opposite the junction zone between the lip and the base. At least one linear groove is provided in the linear distal end portion and extends in the longitudinal direction.
  • the distal end portion is locally more flexible than the same distal end portion not having such a groove.
  • the groove thus allows the lip to better fit the contour of a blade, especially in areas of sharp discontinuity or low radius of curvature of the blade, compared to the joints of the state of the art.
  • the seal being locally more flexible thanks to this groove, it adapts to the shape of the blade undergoing less mechanical stress and wear than the joints of the state of the art, which improves the lifetime of the seal according to the invention compared to the joints of the state of the art.
  • the at least one linear groove is formed in a lip segment configured to contact the blade in the vicinity of a leading edge of the blade and / or in the vicinity of a trailing edge of the blade.
  • a lip segment is a portion of the lip considered in the longitudinal direction.
  • the leading edge and the trailing edge of a blade are the regions with the most abrupt discontinuities.
  • the linear groove extends over the entire length of the linear lip.
  • the distal end portion has a local flexibility allowing the lip to conform to the contact surface of the blade over its entire length. This ensures a better ability of the seal to make a sealed contact with the walls of the blade.
  • the inter-blade linear joint has an evolutive cross section along the length of the joint.
  • the shape of the cross section of the linear joint i.e. a section perpendicular to the longitudinal direction of the joint
  • the seal is adapted to marry the dawn as best as possible according to the shape of the blade.
  • the cross section of the platform is scalable and / or the cross section of the lip is scalable.
  • the base has a shoulder configured to cooperate with an inter-blade platform edge.
  • the linear joint is generally disposed along an edge of a platform, said edge being intended to come opposite the side of the intrados or extrados of the blade.
  • a shoulder allows to correctly position the seal relative to the platform during the assembly of the seal to the platform. With such a shoulder, the seal thus has a protective portion covering said edge of the platform. Such a portion of protection makes it possible to damp any shocks between the blade and the platform (or portions facing two adjacent platforms), if the latter came into contact.
  • the inter-blade linear joint comprises at least one lip stiffener.
  • Such a stiffener makes it possible to rigidify the lip generally on a lip segment, the lip thus being better pressed against the wall of the blade.
  • the lip is pressed against the wall of the blade while thanks to the groove, the distal end of the lip perfectly matches the shape of the wall of the blade and makes a tight contact.
  • the invention also relates to an inter-blade platform comprising a linear inter-blade platform joint according to the invention.
  • the invention furthermore relates to a rotor comprising a disk on the periphery of which are mounted a plurality of blades and a plurality of inter-blade platforms, an inter-blade platform being disposed between each pair of adjacent blades, at least one of inter-blade platforms comprising at least one linear inter-blade platform joint according to the invention.
  • the lip of said linear seal is configured to cooperate with a blade root under a leading edge of said blade, in the vicinity of said leading edge.
  • a blade successively presents, in a direction of height, a foot and an aerodynamic profile, the foot being the part by which the blade is fixed to the disk.
  • the aerodynamic profile is the part of the blade that mixes the air, this profile comprising a leading edge, a trailing edge, a lower surface and an upper surface.
  • the foot has an intermediate portion that is not engaged with the disc. It is understood that the seal cooperates with the blade in this intermediate part.
  • the term "below" is relative to the direction of height of the blade, the blade root defining the bottom of the blade and the aerodynamic profile defining the top of the blade.
  • the seal is placed below the leading edge it is understood that the seal is placed, in the direction of the height, the bottom side of the blade relative to the transition zone between the foot and the aerodynamic profile of the dawn, directly above the leading edge.
  • neighborehood means that the joint is disposed in the direction of height in an area extending about 10% of the total height dawn below the leading edge, and in the longitudinal direction in an area centered on the leading edge and extending about 20% of the length of the blade.
  • At least two inter-blade platforms each comprise at least one linear inter-blade platform joint according to the invention, the at least two inter-blade platforms being adjacent to one and the same blade, said at least one linear joint of one inter-blade platform among the at least two inter-blade platforms being disposed opposite said at least one linear joint of the other inter-blade platform among the at least two inter-blade platforms upstream of an edge driving and / or downstream of a trailing edge of said blade, said linear seals cooperating in support upstream of the leading edge and / or downstream of the trailing edge of said blade.
  • Upstream and downstream refer to the direction of flow of air (or gases) along the blade, the air flowing generally from the leading edge to the trailing edge. It is understood that two adjacent platforms which enclose a blade each comprise a seal according to the invention on their edge vis-à-vis said blade. These joints extend beyond the leading edge and the trailing edge with respect to the blade (ie the joints are longer than the blade), and cooperate directly with each other in support in these areas beyond the leading edge and the trailing edge.
  • the invention furthermore relates to a turbojet engine comprising a rotor according to the invention.
  • the figure 1 represents a turbojet engine 100, comprising a fan 80 forming a rotor according to the invention.
  • the blower 80 comprises a disc 82, on the periphery of which are mounted a plurality of blades 50 and a plurality of inter-blade platform 40, each blade 50 being interposed between two inter-blade platform 40.
  • each platform 40 is disposed between a pair of adjacent blades 50.
  • each edge 42a and 42b of each platform 40 respectively vis-à-vis the side of the lower surface 52a and the side of the upper surface 52b of a blade 50, is respectively equipped with a linear joint 10 and a linear joint 10 'according to the invention.
  • Each linear joint 10 and 10 'respectively has a linear base 12 and 12' and a linear lip 14 and 14 ', a linear groove 16 and 16' being respectively formed between the base 12 and the lip 14 and the base 12 'and the base 14 '.
  • the seal 10 is configured to cooperate with the blade 50 on the side of the lower surface 52a while the seal 10 'is configured to cooperate with the blade 50 on the side of the upper surface 52b.
  • Each blade 50 successively has, according to the height H, a foot 51 and an airfoil 52.
  • the foot 51 has a portion 51a engaged in the disc 82 and an intermediate portion 51b.
  • the aerodynamic profile 52 has the lower surface 52a, the upper surface 52b, a leading edge 52c and a trailing edge 52d (cf. fig.4 ).
  • the wall on the underside side and the wall on the underside side are substantially continuous (ie does not show any noticeable difference) between the intermediate portion 51b of the foot 51 and the airfoil 52, so that the wall on the side of the intrados and the wall on the side of the upper surface of the blade at the root of the blade are sometimes also called intrados and extrados.
  • the lip 14 of the seal 10 cooperates with the root 51 of the blade 50, below the leading edge 52c of the blade 50, in the vicinity of said leading edge 52c.
  • the seal 10 also cooperate with the root 51 of the blade 50, below the leading edge 52c of the blade 50, in the vicinity of said leading edge 52c.
  • the figure 3 is a partial view which represents the blade 50 only in part (a part of the intermediate part 51a and a part of the aerodynamic profile 52) and a part of the platform 40 and the seal 10.
  • the figure 4 is a view of a blade 50 and two platforms 40 according to the arrow IV of the figure 2 .
  • the seals 10 and 10 ' extend from upstream of the leading edge 52c of the blade 50 to the downstream of the trailing edge 52d of the blade 50.
  • each seal 10 and 10' presents a segment 10a, 10'a extending upstream of the trailing edge 52c, a segment 10b, 10'b extending respectively opposite the side of the lower surface 52a and the side of the extrados 52b of the blade 50, and a segment 10c, 10'c which extends downstream of the trailing edge 52d of the blade 50.
  • the upstream and downstream are considered according to the flow of air, represented by the arrow C, along the blade 50, the arrow C being oriented from upstream to downstream.
  • Each segment of seal extends over a longitudinal portion of the seal.
  • the longitudinal direction of the joints 10 and 10 ' is respectively represented by a discontinuous line L and L'.
  • the upstream segments 10a and 10'a are arranged facing each other so that the lips 14 and 14 'of the seals 10 and 10' cooperate in support with each other in the upstream zone of the dawn 50 (cf. fig.5 ).
  • the downstream segments 10c and 10'c are arranged vis-à-vis one another so that the lips 14 and 14 'of the seals 10 and 10' cooperate in support one with the other in the downstream zone of dawn 50 (cf. fig.9 ).
  • the seals 10 and 10 ' have a linear groove 120 and 122, and 120' and 122 '(cf. Figures 5, 6, 8 and 9 ).
  • These grooves 120, 122 and 120 ', 122' respectively extend in the directions substantially parallel to the longitudinal directions L and L '. It will be noted that along the contour of the blade 50, the longitudinal directions L and L'are substantially parallel to the walls of the blade 50.
  • the linear distal end portions 14a and 14'a comprise a linear groove 120 and 120 '.
  • These Figures 5 and 6 each represent a section of the whole dawn and platforms of the figure 4 in the vicinity of the leading edge 52c of the blade 50.
  • the directions B and B 'respectively substantially parallel to the lips 14 and 14' respectively indicate the direction of the width of the lips 14 and 14 '.
  • the "distal" character of the distal end portion is considered in these directions B and B ', the distal end portion of a lip being opposite the base in the direction of the width of the lip.
  • the figure 7 represents a section of the whole dawn and platforms of the figure 4 in a zone distinct from the vicinity of the leading edge 52c and the trailing edge 52d of the blade 50.
  • the seals 10 and 10 'do not have no linear groove.
  • the cross section of the seals 10 and 10 ', and more particularly of the base 12 and the lip 14 of the seal 10 and the base 12' and the lip 14 'of the seal 10', is progressive along the longitudinal direction L and L ', as can be seen from the Figures 5 to 9 .
  • the figure 10 is a seal segment 10, comprising stiffeners 18.
  • each stiffener 18 has a rib shape formed integrally with the seal 10.
  • a stiffener is formed by a frame disposed in the thickness of the lip, or by a sheath arranged around the lip. Such stiffeners may also be provided for the seal 10 '.
  • the seals 10 and 10 ' respectively have a shoulder 20 and 20' formed in the thickness of the base 12 and 12 '.
  • the base 12 and 12 'each have a protective portion 12a and 12'a covering respectively the edge 42a and 42b of the platform 40.
  • the protective portions 12a and 12'a are thicker in the segments 10a, 10'a, 10c and 10'c (either upstream of the leading edge and downstream of the trailing edge) than in the segments 10b and 10'b. These greater thicknesses in these areas make it possible in particular to stiffen the seals 10 and 10 'in these areas and prevent the lips from turning over (ie pass on the side of the aerodynamic profile 52 of the blade).
  • the seal 10 and 10 ' are preferably elastomeric plastic and manufactured by molding.

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)
  • Gasket Seals (AREA)
EP13710460.0A 2012-02-22 2013-02-15 Joint linéaire de plateforme inter- aubes, plateforme inter- aubes, rotor et turboréacteur associés Active EP2817491B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1251611A FR2987086B1 (fr) 2012-02-22 2012-02-22 Joint lineaire de plateforme inter-aubes
PCT/FR2013/050310 WO2013124570A1 (fr) 2012-02-22 2013-02-15 Joint linéaire de plateforme inter- aubes, plateforme inter- aubes, rotor et turboréacteur associés

Publications (2)

Publication Number Publication Date
EP2817491A1 EP2817491A1 (fr) 2014-12-31
EP2817491B1 true EP2817491B1 (fr) 2016-07-20

Family

ID=47901174

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13710460.0A Active EP2817491B1 (fr) 2012-02-22 2013-02-15 Joint linéaire de plateforme inter- aubes, plateforme inter- aubes, rotor et turboréacteur associés

Country Status (10)

Country Link
US (1) US9869323B2 (enrdf_load_stackoverflow)
EP (1) EP2817491B1 (enrdf_load_stackoverflow)
JP (1) JP6199319B2 (enrdf_load_stackoverflow)
CN (1) CN104145087B (enrdf_load_stackoverflow)
BR (1) BR112014020359B1 (enrdf_load_stackoverflow)
CA (1) CA2864536C (enrdf_load_stackoverflow)
FR (1) FR2987086B1 (enrdf_load_stackoverflow)
IN (1) IN2014DN06758A (enrdf_load_stackoverflow)
RU (1) RU2617635C2 (enrdf_load_stackoverflow)
WO (1) WO2013124570A1 (enrdf_load_stackoverflow)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015088593A1 (en) * 2013-12-13 2015-06-18 United Technologies Corporation Fan platform edge seal
US9988920B2 (en) 2015-04-08 2018-06-05 United Technologies Corporation Fan blade platform seal with leading edge winglet
FR3035676B1 (fr) * 2015-04-29 2017-05-12 Snecma Aube munie de plateformes possedant un raidisseur
FR3048997B1 (fr) * 2016-03-21 2020-03-27 Safran Aircraft Engines Plateforme d'aube et disque de soufflante de turbomachine aeronautique
FR3053083B1 (fr) 2016-06-22 2019-11-01 Safran Aircraft Engines Anneau de carenage de roue a aubes
TWI669954B (zh) * 2017-04-21 2019-08-21 美商時美媒體公司 用於編碼器導引自適應性品質演現的系統及方法
EP3438410B1 (en) 2017-08-01 2021-09-29 General Electric Company Sealing system for a rotary machine
US10738630B2 (en) * 2018-02-19 2020-08-11 General Electric Company Platform apparatus for propulsion rotor
US11028714B2 (en) * 2018-07-16 2021-06-08 Raytheon Technologies Corporation Fan platform wedge seal
FR3091563B1 (fr) 2019-01-04 2023-01-20 Safran Aircraft Engines Joint d’étanchéité amélioré de plateforme inter-aubes
FR3097904B1 (fr) * 2019-06-26 2021-06-11 Safran Aircraft Engines Plateforme inter-aube avec caisson sacrificiel
FR3099201B1 (fr) * 2019-07-25 2021-08-20 Safran Aircraft Engines Rotor de soufflante comportant des moyens d'etancheite ameliores
FR3159627A1 (fr) * 2024-02-27 2025-08-29 Safran Aircraft Engines Plateforme inter-aubes pour une helice de turbomachine d’aeronef

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU881354A2 (ru) * 1980-01-04 1981-11-15 Предприятие П/Я В-2285 Устройство дл уплотнени рабочих лопаток турбины
DE19501724C1 (de) * 1995-01-20 1996-10-10 Bruss Dichtungstechnik Wellendichtring sowie Verfahren und Vorrichtung zu seiner Herstellung
JP3684620B2 (ja) * 1995-06-19 2005-08-17 石川島播磨重工業株式会社 翼間スペーサのシール構造
GB9602129D0 (en) 1996-02-02 1996-04-03 Rolls Royce Plc Rotors for gas turbine engines
GB9915637D0 (en) * 1999-07-06 1999-09-01 Rolls Royce Plc A rotor seal
EP1124038A1 (de) * 2000-02-09 2001-08-16 Siemens Aktiengesellschaft Turbinenschaufelanordnung
US6447250B1 (en) * 2000-11-27 2002-09-10 General Electric Company Non-integral fan platform
US6705617B2 (en) * 2001-11-28 2004-03-16 Federal-Mogul World Wide, Inc. Hydrodynamic seal and method of making the same
FR2858351B1 (fr) * 2003-07-31 2006-01-13 Snecma Moteurs Plate-forme inter-aubes a flechissement lateral, pour un support d'aubes de turboreacteur
GB2420162A (en) * 2004-11-16 2006-05-17 Cross Mfg Company A seal arrangement for sealing between turbine blades
GB0611031D0 (en) * 2006-06-06 2006-07-12 Rolls Royce Plc An aerofoil stage and a seal for use therein
US7891670B2 (en) * 2008-02-01 2011-02-22 Freudenberg-Nok General Partnership Multi-directional shaft seal
FR2939835B1 (fr) * 2008-12-12 2017-06-09 Snecma Joint d'etancheite de plateforme dans un rotor de turbomachine, methode pour ameliorer l'etancheite entre une plateforme et une aube de turbomachine.
GB0910752D0 (en) * 2009-06-23 2009-08-05 Rolls Royce Plc An annulus filler for a gas turbine engine
US8066479B2 (en) * 2010-04-05 2011-11-29 Pratt & Whitney Rocketdyne, Inc. Non-integral platform and damper for an airfoil

Also Published As

Publication number Publication date
JP6199319B2 (ja) 2017-09-20
EP2817491A1 (fr) 2014-12-31
RU2617635C2 (ru) 2017-04-25
CN104145087B (zh) 2016-03-02
IN2014DN06758A (enrdf_load_stackoverflow) 2015-05-22
US20150016960A1 (en) 2015-01-15
US9869323B2 (en) 2018-01-16
BR112014020359B1 (pt) 2021-10-19
WO2013124570A1 (fr) 2013-08-29
FR2987086B1 (fr) 2014-03-21
BR112014020359A2 (enrdf_load_stackoverflow) 2017-06-20
CN104145087A (zh) 2014-11-12
RU2014138113A (ru) 2016-04-10
CA2864536A1 (fr) 2013-08-29
JP2015510077A (ja) 2015-04-02
FR2987086A1 (fr) 2013-08-23
CA2864536C (fr) 2019-06-11

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