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FR3128245B1 - METHOD FOR MANUFACTURING A TURBOMACHINE ROTOR PART COMPRISING OPTIMIZED ROUNDED PORTIONS AND CORRESPONDING TURBOMACHINE PART - Google Patents

METHOD FOR MANUFACTURING A TURBOMACHINE ROTOR PART COMPRISING OPTIMIZED ROUNDED PORTIONS AND CORRESPONDING TURBOMACHINE PART Download PDF

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Publication number
FR3128245B1
FR3128245B1 FR2111092A FR2111092A FR3128245B1 FR 3128245 B1 FR3128245 B1 FR 3128245B1 FR 2111092 A FR2111092 A FR 2111092A FR 2111092 A FR2111092 A FR 2111092A FR 3128245 B1 FR3128245 B1 FR 3128245B1
Authority
FR
France
Prior art keywords
theoretical
turbomachine
manufacturing
rounded portions
cell
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
FR2111092A
Other languages
French (fr)
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FR3128245A1 (en
Inventor
Maxime Jouniaux
Florian Carry
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 FR2111092A priority Critical patent/FR3128245B1/en
Publication of FR3128245A1 publication Critical patent/FR3128245A1/en
Application granted granted Critical
Publication of FR3128245B1 publication Critical patent/FR3128245B1/en
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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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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

Landscapes

  • 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 (100) de fabrication d’une pièce de rotor de turbomachine comprenant au moins une alvéole (22) pour recevoir un pied (23) d’une aube, l’alvéole (22) comprenant deux parois de rétention latérales (30a, 30b) opposées et une paroi de fond (31) reliée aux parois de rétention par des portions arrondies (32a, 32b). Selon l’invention, chaque portion arrondie présente un rayon variable et en ce que le procédé comprend une étape d’optimisation desdites parois de l’alvéole, au moyen d’un modèle numérique de la pièce, des portions arrondies théoriques étant configurées chacune de manière à être reliée, à un premier segment (34, 34’), tangent à une paroi de rétention latérale théorique, délimitant la profondeur de chaque portion arrondie théorique et à un deuxième segment (36, 36’), tangent à la paroi de fond théorique, délimitant une demi largeur circonférentielle de chaque portion arrondie théorique, les premier et deuxième segments étant sécants en un point d’intersection et présentant respectivement des première et deuxième longueurs (l1, l2) déterminées. Figure d’abrégé : Fig.5The invention relates to a method (100) for manufacturing a turbomachine rotor part comprising at least one cell (22) for receiving a root (23) of a blade, the cell (22) comprising two retention walls opposite side walls (30a, 30b) and a bottom wall (31) connected to the retention walls by rounded portions (32a, 32b). According to the invention, each rounded portion has a variable radius and in that the method comprises a step of optimizing said walls of the cell, by means of a digital model of the part, theoretical rounded portions each being configured in so as to be connected, to a first segment (34, 34'), tangent to a theoretical lateral retention wall, delimiting the depth of each theoretical rounded portion and to a second segment (36, 36'), tangent to the wall of theoretical bottom, delimiting a half circumferential width of each theoretical rounded portion, the first and second segments being intersecting at an intersection point and having respectively determined first and second lengths (l1, l2). Abstract Figure: Fig.5

FR2111092A 2021-10-19 2021-10-19 METHOD FOR MANUFACTURING A TURBOMACHINE ROTOR PART COMPRISING OPTIMIZED ROUNDED PORTIONS AND CORRESPONDING TURBOMACHINE PART Active FR3128245B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2111092A FR3128245B1 (en) 2021-10-19 2021-10-19 METHOD FOR MANUFACTURING A TURBOMACHINE ROTOR PART COMPRISING OPTIMIZED ROUNDED PORTIONS AND CORRESPONDING TURBOMACHINE PART

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2111092 2021-10-19
FR2111092A FR3128245B1 (en) 2021-10-19 2021-10-19 METHOD FOR MANUFACTURING A TURBOMACHINE ROTOR PART COMPRISING OPTIMIZED ROUNDED PORTIONS AND CORRESPONDING TURBOMACHINE PART

Publications (2)

Publication Number Publication Date
FR3128245A1 FR3128245A1 (en) 2023-04-21
FR3128245B1 true FR3128245B1 (en) 2024-07-05

Family

ID=80122663

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2111092A Active FR3128245B1 (en) 2021-10-19 2021-10-19 METHOD FOR MANUFACTURING A TURBOMACHINE ROTOR PART COMPRISING OPTIMIZED ROUNDED PORTIONS AND CORRESPONDING TURBOMACHINE PART

Country Status (1)

Country Link
FR (1) FR3128245B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8608447B2 (en) * 2009-02-19 2013-12-17 Rolls-Royce Corporation Disk for turbine engine
ES2620424T3 (en) * 2010-11-15 2017-06-28 Mtu Aero Engines Gmbh Turbomachine with clamping means for axial clamping of a blade root
EP2546465A1 (en) * 2011-07-14 2013-01-16 Siemens Aktiengesellschaft Blade root, corresponding blade, rotor disc, and turbomachine assembly
DE102012023611A1 (en) * 2012-12-04 2014-06-05 Mann+Hummel Gmbh Compressor stator for supercharger i.e. exhaust gas turbo supercharger, of combustion engine of motor car, has adapter element introduced into stator over which bearing support of compressor wheel is connected with stator

Also Published As

Publication number Publication date
FR3128245A1 (en) 2023-04-21

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