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EP2948640B1 - Aubage fixe de distribution de flux dans une turbomachine, comprenant une plate-forme interne a renforts intégrés, turbomachine et procédé de fabrication associés - Google Patents

Aubage fixe de distribution de flux dans une turbomachine, comprenant une plate-forme interne a renforts intégrés, turbomachine et procédé de fabrication associés Download PDF

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Publication number
EP2948640B1
EP2948640B1 EP14704842.5A EP14704842A EP2948640B1 EP 2948640 B1 EP2948640 B1 EP 2948640B1 EP 14704842 A EP14704842 A EP 14704842A EP 2948640 B1 EP2948640 B1 EP 2948640B1
Authority
EP
European Patent Office
Prior art keywords
ring
vane assembly
partition
radial
tongue
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
EP14704842.5A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2948640A1 (fr
Inventor
Sébastien CONGRATEL
Marion CHAMBRE
Bruno Richard
Romain ROULLET
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.)
Filing date
Publication date
Application filed by SNECMA Services SA, SNECMA SAS filed Critical SNECMA Services SA
Publication of EP2948640A1 publication Critical patent/EP2948640A1/fr
Application granted granted Critical
Publication of EP2948640B1 publication Critical patent/EP2948640B1/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing
    • 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

Definitions

  • the field of the invention is that of fixed vanes for distribution of the air flow in a turbomachine.
  • a turbomachine generally comprises, from upstream to downstream in the direction of the gas flow, a blower, one or more stages of compressors, for example a low pressure compressor and a high pressure compressor, a combustion chamber, one or more turbine stages, for example a high pressure turbine and a low pressure turbine, and a gas exhaust nozzle.
  • These turbines comprise a distributor of the air flow in the turbomachine, composed of a plurality of fixed blade stages each comprising a plurality of blades extending generally radially with respect to an axis of the turbomachine, and disposed between an inner annular platform and an outer annular platform by which said vanes are attached to the turbomachine.
  • the blades are conventionally produced by a technique known as the foundry lost wax. Nuclei are inserted in the mold before injection of the wax, these cores being held in position by sockets, the association between the cores and the sockets being carried out manually.
  • the invention aims to remedy this problem by proposing a fixed blade of flow distribution in a turbomachine, comprising an inner annular platform and a plurality of fixed vanes mounted on it, the inner platform comprising a support plate forming the base of said blades, a radial annular partition extending from the support plate towards an axis of the blade, and an inner ring attached to the radial annular partition, and having an inner surface on which is disposed a material abradable, the blade being characterized in that the inner ring comprises at least one cutout defining a tongue, the tongue being folded to bear against the radial annular partition.
  • the invention also proposes a turbomachine comprising at least one such blade.
  • the distribution vane according to the invention is lighter but as robust as before since the reinforcement function in support against the partition radial is made by the inner crown of the vane itself, without adding material.
  • FIG. 1 there is shown a partial view of a fixed blade 10 distribution of the flow of air flowing in a turbomachine, the direction of flow of the air flow being represented by an arrow F, the blade forming a stage of a distributor of a turbomachine turbine, for example a low-pressure turbine.
  • Blading 10 comprises a plurality of fixed blades 11 arranged radially with respect to an axis of the turbomachine (not shown), which is also the axis of the blade, said blades being mounted on an inner annular platform 12 .
  • the platform 12 comprises an annular partition 120 extending radially with respect to the axis of the turbomachine, as well as an annular plate 121 for supporting the blades 11, extending on either side of the annular partition. at a radially outer end thereof.
  • the platform 12 also comprises an inner ring 122 extending on either side of the radial annular partition 120, at its radially inner end, and on which a layer of abradable material 123 is attached.
  • the inner ring 122 has a median annular section 1220 extending substantially axially with respect to the axis of the blading, and two end annular tabs 1221, 1222 extending respectively upstream and downstream.
  • the blading relative to the airflow being radially offset from the center section 1220, said sections being inclined relative to the axis of the blading.
  • These sections are shaped to cooperate with rotor blade spoilers placed upstream and downstream with respect to the blade 10, in order to form labyrinth type seals, to avoid recirculation of air in one direction. radial between the vein of the blade 10 (that is to say between the blades 11) and the gap between the platform of the fixed blade and the adjacent rotor.
  • the inner ring 122 comprises, on its median section 1220, at least one, and preferably a plurality of U-shaped cutouts 1223, each cutout thus comprising two preferably but non-limitatively parallel portions 1224 (forming the branches of the "U"") Joined at one end by a transverse portion 1225 (forming the base of the" U ").
  • the portions 1224 are oriented substantially parallel to the axis of the blade and the transverse portion 1225 and disposed on the downstream side of the blank with respect to the air flow.
  • Each cutout 1223 thus delimits a tongue 1226 detached from the rest of the median section by the three portions of the cutout. Because of the shape of the cutouts, each tab extends over a ring sector.
  • At least one end portion 1227 of each cutout is bent at right angles to the middle section of the ring 122 so as to extend substantially radially.
  • each tongue can also be bent at right angles to the crown.
  • Each tongue thus folded releases an opening 1228 in ring sector in the ring 122.
  • the cuts 1123, and therefore the tabs 1226 and the openings 1228 are distributed regularly, that is to say at constant angular interval relative to the axis of the blade, along the circumference of the crown.
  • the ring 122 has, on an annular zone of its median section of the width of the openings, an alternation of solid areas and openings 1228.
  • the ring 122 is attached to the radial partition 120 at the annular zone comprising the alternation of openings and solid areas, the end 1227 of the tabs at right angles to the ring bearing against the wall radial.
  • the tongues cut in the crown constitute the surface to be soldered on the radial partition, thus making it possible to assemble the crown to the radial partition without adding additional elements (for example sheets, tabs on a radial partition ).
  • the blading is thus lightened.
  • the layer of abradable material 123 attached to the ring can also be reported on the radial wall through each opening 1228 of said ring.
  • the layer of abradable material 123 is brazed firstly on the radial wall through each opening, and secondly on the radially inner surface of the middle section 1220 of the inner ring.
  • the ring 122 may comprise only a cutout 1223 U, it thus occupies a smaller space. Other types of attachment can nevertheless be integrated in the crown in addition to this single cut.
  • a plurality of U-shaped cutouts 1223 are produced on the circumference of an annular ring 122, in accordance with the cuts described above, the cuts being preferably evenly distributed over said circumference.
  • each cutout 1223 is folded at right angles outwardly of the ring, so that the end 1227 of each tongue is oriented substantially radially with respect to the axis of the crown.
  • the crown 122 is reported on the radial partition 120 of an internal platform with a fixed blade, the blades 11 and the outer platform of the blade may also be already mounted on the internal platform.
  • the crown is attached so that the folded ends of each tongue bear against the radial partition, and the radial annular partition is disposed at the openings 1228 made in the ring.
  • the ends of the tongues 1226 bearing against the radial partition, as well as the zones of the ring between two consecutive openings are brazed to the radial wall.
  • a layer of abradable material 123 on the assembly obtained in the previous step preferably by brazing the layer on the radially inner surface of the median portion 1220 of the ring, and at the openings 1228, brazing the layer 123 to the radial wall (also on its radially inner surface).
  • brazing operations 300 and 400 can be performed simultaneously, which makes the process faster to implement.

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)
EP14704842.5A 2013-01-23 2014-01-22 Aubage fixe de distribution de flux dans une turbomachine, comprenant une plate-forme interne a renforts intégrés, turbomachine et procédé de fabrication associés Active EP2948640B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1350582A FR3001252B1 (fr) 2013-01-23 2013-01-23 Aubage fixe de distribution de flux comprenant une plate-forme interne a renforts integres
PCT/FR2014/050113 WO2014114873A1 (fr) 2013-01-23 2014-01-22 Aubage fixe de distribution de flux dans une turbomachine, comprenant une plate-forme interne a renforts intégrés, turbomachine et procédé de fabrication associés

Publications (2)

Publication Number Publication Date
EP2948640A1 EP2948640A1 (fr) 2015-12-02
EP2948640B1 true EP2948640B1 (fr) 2017-04-19

Family

ID=48521143

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14704842.5A Active EP2948640B1 (fr) 2013-01-23 2014-01-22 Aubage fixe de distribution de flux dans une turbomachine, comprenant une plate-forme interne a renforts intégrés, turbomachine et procédé de fabrication associés

Country Status (8)

Country Link
US (1) US10024179B2 (zh)
EP (1) EP2948640B1 (zh)
CN (1) CN104937216B (zh)
BR (1) BR112015017351B1 (zh)
CA (1) CA2898864C (zh)
FR (1) FR3001252B1 (zh)
RU (1) RU2651919C2 (zh)
WO (1) WO2014114873A1 (zh)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3082233B1 (fr) * 2018-06-12 2020-07-17 Safran Aircraft Engines Ensemble de turbine
FR3100838B1 (fr) * 2019-09-13 2021-10-01 Safran Aircraft Engines Anneau d’etancheite de turbomachine
FR3103012B1 (fr) * 2019-11-12 2021-11-19 Safran Aircraft Engines Rangée annulaire sectorisée d’aubes fixes
DE102020200073A1 (de) 2020-01-07 2021-07-08 Siemens Aktiengesellschaft Leitschaufelkranz
FR3113298B1 (fr) * 2020-08-10 2023-09-01 Safran Aircraft Engines Porte-abradable d’un distributeur basse pression comprenant une unique tôle
FR3146931A1 (fr) * 2023-03-23 2024-09-27 Safran Aircraft Engines Ensemble statorique pour une turbomachine d’aéronef

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB807231A (en) * 1955-05-20 1959-01-14 Gen Electric Securing means for blading of compressors or turbines
US3018085A (en) * 1957-03-25 1962-01-23 Gen Motors Corp Floating labyrinth seal
DE3003469C2 (de) * 1980-01-31 1987-03-19 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Einrichtung zur Verbindung einander rotationssymmetrisch zugeordneter, unterschiedlichen thermischen Einflüssen ausgesetzter Bauteile für Strömungsmaschinen, insbesondere Gasturbinentriebwerke
US4767267A (en) * 1986-12-03 1988-08-30 General Electric Company Seal assembly
RU2171380C2 (ru) * 1999-04-27 2001-07-27 Открытое акционерное общество "Авиадвигатель" Сопловой аппарат турбомашины
FR2928961B1 (fr) * 2008-03-19 2015-11-13 Snecma Distributeur sectorise pour une turbomachine.
FR2930592B1 (fr) * 2008-04-24 2010-04-30 Snecma Distributeur de turbine pour une turbomachine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
RU2651919C2 (ru) 2018-04-24
RU2015135580A (ru) 2017-03-02
FR3001252B1 (fr) 2015-02-13
CN104937216B (zh) 2016-08-10
CA2898864C (fr) 2020-08-25
BR112015017351B1 (pt) 2021-12-14
US10024179B2 (en) 2018-07-17
EP2948640A1 (fr) 2015-12-02
BR112015017351A2 (pt) 2017-07-11
CA2898864A1 (fr) 2014-07-31
WO2014114873A1 (fr) 2014-07-31
FR3001252A1 (fr) 2014-07-25
CN104937216A (zh) 2015-09-23
US20150377044A1 (en) 2015-12-31

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