FR3106157B1 - Composant de turbomachine comportant des orifices de refroidissement ameliores - Google Patents

Composant de turbomachine comportant des orifices de refroidissement ameliores Download PDF

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Publication number
FR3106157B1
FR3106157B1 FR2000198A FR2000198A FR3106157B1 FR 3106157 B1 FR3106157 B1 FR 3106157B1 FR 2000198 A FR2000198 A FR 2000198A FR 2000198 A FR2000198 A FR 2000198A FR 3106157 B1 FR3106157 B1 FR 3106157B1
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FR
France
Prior art keywords
face
wall
mouth
turbomachine component
cooling holes
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
FR2000198A
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English (en)
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FR3106157A1 (fr
Inventor
Michel Slusarz
Léandre Ostino
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 FR2000198A priority Critical patent/FR3106157B1/fr
Publication of FR3106157A1 publication Critical patent/FR3106157A1/fr
Application granted granted Critical
Publication of FR3106157B1 publication Critical patent/FR3106157B1/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

L'invention concerne un composant (10) de turbomachine comportant une paroi (14) délimitée par une face interne (18) et une face externe (16) opposées, la paroi (14) comprenant au moins un orifice de refroidissement (12) pour permettre à un flux de gaz de traverser la paroi (14) en reliant fluidiquement la face interne (18) et la face externe (16), l’orifice de refroidissement (12) comportant un perçage (20) débouchant sur la face interne (18) et une embouchure (26) évasée qui débouche sur la face externe (16), l’embouchure (26) présentant une section progressivement croissante vers la face externe (16), l'embouchure (26) comportant en outre une face de fond (28) qui est inclinée par rapport à la face externe (16), caractérisé en ce que la face interne (18) de la paroi (14) comporte une surépaisseur (42) qui s’étend au droit de l'embouchure (26) de l’orifice de refroidissement (12). Figure pour l’abrégé : figure 2.
FR2000198A 2020-01-10 2020-01-10 Composant de turbomachine comportant des orifices de refroidissement ameliores Active FR3106157B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2000198A FR3106157B1 (fr) 2020-01-10 2020-01-10 Composant de turbomachine comportant des orifices de refroidissement ameliores

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2000198A FR3106157B1 (fr) 2020-01-10 2020-01-10 Composant de turbomachine comportant des orifices de refroidissement ameliores
FR2000198 2020-01-10

Publications (2)

Publication Number Publication Date
FR3106157A1 FR3106157A1 (fr) 2021-07-16
FR3106157B1 true FR3106157B1 (fr) 2023-04-28

Family

ID=70918530

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2000198A Active FR3106157B1 (fr) 2020-01-10 2020-01-10 Composant de turbomachine comportant des orifices de refroidissement ameliores

Country Status (1)

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FR (1) FR3106157B1 (fr)

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8683814B2 (en) * 2012-02-15 2014-04-01 United Technologies Corporation Gas turbine engine component with impingement and lobed cooling hole
US10982552B2 (en) * 2014-09-08 2021-04-20 Raytheon Technologies Corporation Gas turbine engine component with film cooling hole
US20170306764A1 (en) * 2016-04-26 2017-10-26 General Electric Company Airfoil for a turbine engine

Also Published As

Publication number Publication date
FR3106157A1 (fr) 2021-07-16

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