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FR3107721B1 - Turbomachine stator blade, stator sector and method of manufacture - Google Patents

Turbomachine stator blade, stator sector and method of manufacture Download PDF

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Publication number
FR3107721B1
FR3107721B1 FR2001961A FR2001961A FR3107721B1 FR 3107721 B1 FR3107721 B1 FR 3107721B1 FR 2001961 A FR2001961 A FR 2001961A FR 2001961 A FR2001961 A FR 2001961A FR 3107721 B1 FR3107721 B1 FR 3107721B1
Authority
FR
France
Prior art keywords
blade
stator
manufacture
recess
turbomachine
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
FR2001961A
Other languages
French (fr)
Other versions
FR3107721A1 (en
Inventor
Romain Mikel Erwan Gouspy
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 FR2001961A priority Critical patent/FR3107721B1/en
Publication of FR3107721A1 publication Critical patent/FR3107721A1/en
Application granted granted Critical
Publication of FR3107721B1 publication Critical patent/FR3107721B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F05D2260/961—Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
    • 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
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P10/00—Technologies related to metal processing
    • Y02P10/25—Process efficiency

Landscapes

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

Abstract

La présente invention concerne notamment de redresseur de turbomachine, de hauteur H s'étendant entre un pied de pale (40) et une tête de pale (41), caractérisée par le fait qu'elle présente un évidement interne (42) qui est délimité par deux parois (43, 44) lesquelles se rejoignent respectivement au bord d'attaque et au bord de fuite de ladite pale (4) pour y former des régions pleines opposées et en regard l'une de l'autre (45, 46), et que l'épaisseur desdites régions pleines (45, 46), mesurée parallèlement audit pied de pale (40), entre ledit évidement (42) et le bord d'attaque, respectivement le bord de fuite, est variable entre lesdits pied (40) et tête de pale (41), cette variation d'épaisseur se faisant uniquement du côté de l'évidement (la revendication 1 sera recopiée ici). Figure pour l’abrégé : Fig. 3The present invention relates in particular to a turbomachine stator, of height H extending between a blade root (40) and a blade head (41), characterized in that it has an internal recess (42) which is delimited by two walls (43, 44) which meet respectively at the leading edge and at the trailing edge of said blade (4) to form opposite solid regions facing each other (45, 46) , and that the thickness of said solid regions (45, 46), measured parallel to said blade root (40), between said recess (42) and the leading edge, respectively the trailing edge, is variable between said root ( 40) and blade head (41), this variation in thickness taking place only on the side of the recess (claim 1 will be copied here). Figure for the abstract: Fig. 3

FR2001961A 2020-02-27 2020-02-27 Turbomachine stator blade, stator sector and method of manufacture Active FR3107721B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2001961A FR3107721B1 (en) 2020-02-27 2020-02-27 Turbomachine stator blade, stator sector and method of manufacture

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2001961A FR3107721B1 (en) 2020-02-27 2020-02-27 Turbomachine stator blade, stator sector and method of manufacture
FR2001961 2020-02-27

Publications (2)

Publication Number Publication Date
FR3107721A1 FR3107721A1 (en) 2021-09-03
FR3107721B1 true FR3107721B1 (en) 2022-07-08

Family

ID=71575438

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2001961A Active FR3107721B1 (en) 2020-02-27 2020-02-27 Turbomachine stator blade, stator sector and method of manufacture

Country Status (1)

Country Link
FR (1) FR3107721B1 (en)

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11168566B2 (en) * 2016-12-05 2021-11-09 MTU Aero Engines AG Turbine blade comprising a cavity with wall surface discontinuities and process for the production thereof
US10837287B2 (en) * 2017-01-20 2020-11-17 Pratt & Whitney Canada Corp. Mistuned bladed rotor and associated manufacturing method
DE102018211158A1 (en) * 2018-07-06 2020-01-09 MTU Aero Engines AG Blade arrangement for a gas turbine and method for producing the blade arrangement

Also Published As

Publication number Publication date
FR3107721A1 (en) 2021-09-03

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