FR3121472B1 - Procede de fabrication d’une piece de turbomachine comprenant des portions arrondies optimisees et piece de turbomachine correspondante - Google Patents

Procede de fabrication d’une piece de turbomachine comprenant des portions arrondies optimisees et piece de turbomachine correspondante Download PDF

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Publication number
FR3121472B1
FR3121472B1 FR2103406A FR2103406A FR3121472B1 FR 3121472 B1 FR3121472 B1 FR 3121472B1 FR 2103406 A FR2103406 A FR 2103406A FR 2103406 A FR2103406 A FR 2103406A FR 3121472 B1 FR3121472 B1 FR 3121472B1
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France
Prior art keywords
turbomachine part
theoretical
rounded portions
manufacturing
portions
Prior art date
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Active
Application number
FR2103406A
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English (en)
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FR3121472A1 (fr
Inventor
Cyrille Telman
Estelle Jaudoin
Jean Michel Anthime Papail
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR2103406A priority Critical patent/FR3121472B1/fr
Publication of FR3121472A1 publication Critical patent/FR3121472A1/fr
Application granted granted Critical
Publication of FR3121472B1 publication Critical patent/FR3121472B1/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • 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
    • F05D2260/81—Modelling or simulation
    • 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
    • F05D2260/82—Forecasts
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

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

Abstract

L’invention concerne un procédé de fabrication d’une pièce de turbomachine comprenant une bride festonnée, la bride festonnée comprenant une alternance de parties pleines et de parties creuses délimitées par une portion de périphérie (12), deux portions latérales et deux portions arrondies reliant la portion de périphérie aux deux portions latérales, le procédé comprenant une étape d’optimisation des portions arrondies théoriques, dans un modèle numérique, de sorte à présenter un rayon variable, les portions arrondies théoriques étant configurées chacune de manière à être reliée, au niveau d’un premier point de liaison (14), à un premier segment (15) d’une première droite qui est tangente à une portion latérale théorique et, au niveau d’un deuxième point de liaison (16) à un deuxième segment (17) d’une deuxième droite qui est tangente à la portion de périphérie théorique, les premier et deuxième segments étant sécants en un point d’intersection (18, 18’) et présentant respectivement une première et une deuxième longueurs déterminées. Figure  d’abrégé : Figure  5
FR2103406A 2021-04-01 2021-04-01 Procede de fabrication d’une piece de turbomachine comprenant des portions arrondies optimisees et piece de turbomachine correspondante Active FR3121472B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2103406A FR3121472B1 (fr) 2021-04-01 2021-04-01 Procede de fabrication d’une piece de turbomachine comprenant des portions arrondies optimisees et piece de turbomachine correspondante

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2103406 2021-04-01
FR2103406A FR3121472B1 (fr) 2021-04-01 2021-04-01 Procede de fabrication d’une piece de turbomachine comprenant des portions arrondies optimisees et piece de turbomachine correspondante

Publications (2)

Publication Number Publication Date
FR3121472A1 FR3121472A1 (fr) 2022-10-07
FR3121472B1 true FR3121472B1 (fr) 2023-07-14

Family

ID=76283916

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2103406A Active FR3121472B1 (fr) 2021-04-01 2021-04-01 Procede de fabrication d’une piece de turbomachine comprenant des portions arrondies optimisees et piece de turbomachine correspondante

Country Status (1)

Country Link
FR (1) FR3121472B1 (fr)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19941134C1 (de) * 1999-08-30 2000-12-28 Mtu Muenchen Gmbh Schaufelkranz für eine Gasturbine
FR2938292B1 (fr) * 2008-11-07 2010-12-24 Snecma Bride annulaire de fixation d'un element de rotor ou de stator dans une turbomachine
FR2946083B1 (fr) * 2009-05-28 2011-06-17 Snecma Turbine basse-pression
US9598981B2 (en) * 2013-11-22 2017-03-21 Siemens Energy, Inc. Industrial gas turbine exhaust system diffuser inlet lip
FR3051831B1 (fr) 2016-05-26 2018-05-18 Safran Aircraft Engines Carter d'echappement de turbomachine et son procede de fabrication

Also Published As

Publication number Publication date
FR3121472A1 (fr) 2022-10-07

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