FR3107082B1 - Turbomachine wheel - Google Patents

Turbomachine wheel Download PDF

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Publication number
FR3107082B1
FR3107082B1 FR2001160A FR2001160A FR3107082B1 FR 3107082 B1 FR3107082 B1 FR 3107082B1 FR 2001160 A FR2001160 A FR 2001160A FR 2001160 A FR2001160 A FR 2001160A FR 3107082 B1 FR3107082 B1 FR 3107082B1
Authority
FR
France
Prior art keywords
axially
sealing
stilts
cells
flow
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
FR2001160A
Other languages
French (fr)
Other versions
FR3107082A1 (en
Inventor
Edouard Garreau
Josserand Jacques André Bassery
Elsa Maxime
Ba-Phuc Tang
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 FR2001160A priority Critical patent/FR3107082B1/en
Publication of FR3107082A1 publication Critical patent/FR3107082A1/en
Application granted granted Critical
Publication of FR3107082B1 publication Critical patent/FR3107082B1/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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
    • 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
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L’invention concerne une roue (2) de turbomachine s’étendant longitudinalement selon un axe X comprenant un disque (4) présentant à sa périphérie des alvéoles sensiblement axiales, des aubes (5) dont les pieds (9) sont engagés axialement et retenus radialement dans lesdites alvéoles et présentent des échasses (8) de liaison des pieds (9) à des plates-formes (7) destinées à délimiter radialement vers l’extérieur une veine annulaire d’écoulement d’un flux de gaz, des dispositifs d’étanchéité (20) montés dans des cavités inter-échasses (19) délimitées circonférentiellement entre deux échasses (8) de deux aubes (5) adjacentes et axialement par des parois transverses (16, 17) reliées à leurs périphéries radialement externes aux plates-formes (7), caractérisée en ce qu’au moins un des dispositifs d’étanchéité (20) comprend une languette de maintien axial (23) prenant appui axialement sur au moins une paroi transverse d’étanchéité (17) de façon à maintenir axialement en position le dispositif d’étanchéité (20) par rapport au pied (9) de l’aube correspondante (5). Figure à publier avec l’abrégé : Figure 9The invention relates to a turbine engine wheel (2) extending longitudinally along an axis X comprising a disk (4) having at its periphery substantially axial cells, blades (5) whose roots (9) are axially engaged and retained radially in said cells and have stilts (8) for connecting the feet (9) to platforms (7) intended to delimit radially outwards an annular vein for the flow of a flow of gas, devices for sealing (20) mounted in inter-stilt cavities (19) delimited circumferentially between two stilts (8) of two adjacent blades (5) and axially by transverse walls (16, 17) connected at their radially outer peripheries to the plates shapes (7), characterized in that at least one of the sealing devices (20) comprises an axial holding tab (23) bearing axially on at least one transverse sealing wall (17) so as to hold axially in position the device seal (20) relative to the root (9) of the corresponding blade (5). Figure to be published with abstract: Figure 9

FR2001160A 2020-02-06 2020-02-06 Turbomachine wheel Active FR3107082B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2001160A FR3107082B1 (en) 2020-02-06 2020-02-06 Turbomachine wheel

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2001160 2020-02-06
FR2001160A FR3107082B1 (en) 2020-02-06 2020-02-06 Turbomachine wheel

Publications (2)

Publication Number Publication Date
FR3107082A1 FR3107082A1 (en) 2021-08-13
FR3107082B1 true FR3107082B1 (en) 2022-08-05

Family

ID=71094458

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2001160A Active FR3107082B1 (en) 2020-02-06 2020-02-06 Turbomachine wheel

Country Status (1)

Country Link
FR (1) FR3107082B1 (en)

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5228835A (en) * 1992-11-24 1993-07-20 United Technologies Corporation Gas turbine blade seal
FR2971004B1 (en) 2011-02-01 2013-02-15 Snecma METHOD FOR ASSEMBLING A LOW-BODY TURBOREACTOR LOW-PRESSURE TURBINE
US9366142B2 (en) * 2011-10-28 2016-06-14 General Electric Company Thermal plug for turbine bucket shank cavity and related method
US10113434B2 (en) * 2012-01-31 2018-10-30 United Technologies Corporation Turbine blade damper seal
WO2014051688A1 (en) * 2012-09-28 2014-04-03 United Technologies Corporation Seal damper with improved retention
FR3027949B1 (en) * 2014-11-04 2019-07-26 Safran Aircraft Engines TURBINE WHEEL FOR A TURBOMACHINE
US9863257B2 (en) * 2015-02-04 2018-01-09 United Technologies Corporation Additive manufactured inseparable platform damper and seal assembly for a gas turbine engine
US9845690B1 (en) * 2016-06-03 2017-12-19 General Electric Company System and method for sealing flow path components with front-loaded seal
FR3072122B1 (en) 2017-10-11 2019-09-27 Safran Aircraft Engines TURBOMACHINE WHEEL

Also Published As

Publication number Publication date
FR3107082A1 (en) 2021-08-13

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