FR3100560B1 - Set for a turbomachine turbine - Google Patents

Set for a turbomachine turbine Download PDF

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Publication number
FR3100560B1
FR3100560B1 FR1909847A FR1909847A FR3100560B1 FR 3100560 B1 FR3100560 B1 FR 3100560B1 FR 1909847 A FR1909847 A FR 1909847A FR 1909847 A FR1909847 A FR 1909847A FR 3100560 B1 FR3100560 B1 FR 3100560B1
Authority
FR
France
Prior art keywords
sector
turbine
slot
ring
circumferential end
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
FR1909847A
Other languages
French (fr)
Other versions
FR3100560A1 (en
Inventor
Etienne Gérard Joseph Canelle
Jacques Marcel Arthur Bunel
Emeric Christian Amaury D'herbigny
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
Safran Aircraft Engines 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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1909847A priority Critical patent/FR3100560B1/en
Publication of FR3100560A1 publication Critical patent/FR3100560A1/en
Application granted granted Critical
Publication of FR3100560B1 publication Critical patent/FR3100560B1/en
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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/02—Sealings between relatively-stationary surfaces
    • F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
    • F16J15/08—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with exclusively metal packing
    • F16J15/0887—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with exclusively metal packing the sealing effect being obtained by elastic deformation of the packing
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L’invention concerne un ensemble comportant au moins un premier secteur (21) d’anneau (17) de turbine (7) et un second secteur (21) d’anneau (17) de turbine (7), les deux secteurs (21) étant disposés de façon adjacente l’un par rapport à l’autre, chaque secteur (21) s’étendant sur une portion angulaire autour d’un axe X, chaque secteur (21) comportant une partie radialement externe (22) comprenant des moyens de fixation aptes à permettre la fixation du secteur (21) à un carter de turbine et une partie radialement interne (23) comportant un matériau abradable destiné à coopérer avec des léchettes ou des sommets d’aubes mobiles de la turbine (7), la partie radialement externe (22) comportant une première extrémité circonférentielle comportant une première fente (25a) et une seconde extrémité circonférentielle comportant une seconde fente (25b).The invention relates to an assembly comprising at least a first sector (21) of the ring (17) of the turbine (7) and a second sector (21) of the ring (17) of the turbine (7), the two sectors (21 ) being arranged adjacent to each other, each sector (21) extending over an angular portion around an axis X, each sector (21) comprising a radially outer part (22) comprising fixing means capable of allowing the fixing of the sector (21) to a turbine casing and a radially internal part (23) comprising an abradable material intended to cooperate with the wipers or the tips of the moving blades of the turbine (7), the radially outer portion (22) having a first circumferential end having a first slot (25a) and a second circumferential end having a second slot (25b).

FR1909847A 2019-09-06 2019-09-06 Set for a turbomachine turbine Active FR3100560B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1909847A FR3100560B1 (en) 2019-09-06 2019-09-06 Set for a turbomachine turbine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1909847 2019-09-06
FR1909847A FR3100560B1 (en) 2019-09-06 2019-09-06 Set for a turbomachine turbine

Publications (2)

Publication Number Publication Date
FR3100560A1 FR3100560A1 (en) 2021-03-12
FR3100560B1 true FR3100560B1 (en) 2022-04-29

Family

ID=69157999

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1909847A Active FR3100560B1 (en) 2019-09-06 2019-09-06 Set for a turbomachine turbine

Country Status (1)

Country Link
FR (1) FR3100560B1 (en)

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0228748D0 (en) * 2002-12-10 2003-01-15 Alstom Switzerland Ltd Sealing arrangement
US8016549B2 (en) * 2006-07-13 2011-09-13 United Technologies Corporation Turbine engine alloys and crystalline orientations
US9353635B2 (en) * 2011-08-16 2016-05-31 General Electric Company Seal end attachment
US9757920B2 (en) * 2013-03-15 2017-09-12 Rolls-Royce Corporation Flexible ceramic matrix composite seal
FR3030323B1 (en) 2014-12-23 2019-08-09 Safran Aircraft Engines MANUFACTURING PLATE FOR THE MANUFACTURE OF PARTS BY SELECTIVE FUSION OR SELECTIVE POWDER BED STITCHING, TOOLING AND MANUFACTURING PROCESS USING SUCH A PLATE
EP3073056B1 (en) * 2015-03-25 2018-01-03 Ansaldo Energia IP UK Limited Wire seal
US10161257B2 (en) * 2015-10-20 2018-12-25 General Electric Company Turbine slotted arcuate leaf seal

Also Published As

Publication number Publication date
FR3100560A1 (en) 2021-03-12

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