FR3096724B1 - TURBINE MODULE FOR AN AIRCRAFT TURBOMACHINE - Google Patents

TURBINE MODULE FOR AN AIRCRAFT TURBOMACHINE Download PDF

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Publication number
FR3096724B1
FR3096724B1 FR1905762A FR1905762A FR3096724B1 FR 3096724 B1 FR3096724 B1 FR 3096724B1 FR 1905762 A FR1905762 A FR 1905762A FR 1905762 A FR1905762 A FR 1905762A FR 3096724 B1 FR3096724 B1 FR 3096724B1
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FR
France
Prior art keywords
plane
downstream
arms
module
situated
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
FR1905762A
Other languages
French (fr)
Other versions
FR3096724A1 (en
Inventor
Charlie Michaël Koupper
Bayon Yves-Marie Pierre Le
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 Helicopter Engines SAS
Original Assignee
Safran Helicopter 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 Helicopter Engines SAS filed Critical Safran Helicopter Engines SAS
Priority to FR1905762A priority Critical patent/FR3096724B1/en
Priority to PCT/FR2020/050894 priority patent/WO2020240136A1/en
Publication of FR3096724A1 publication Critical patent/FR3096724A1/en
Application granted granted Critical
Publication of FR3096724B1 publication Critical patent/FR3096724B1/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
    • 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
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/128—Nozzles
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Module de turbine (50) pour une turbomachine (10) d’aéronef, ce module comportant : - des bras (52) de liaison de parois annulaires (50a, 50b), ces bras comportant en amont des bords d’attaque (52a) qui sont situés dans un plan P1 perpendiculaire audit axe, un distributeur (54) situé en aval desdits bras et comportant des aubes de stator (54a) qui comportent en amont des bords d’attaque (54b) situés dans un plan P2 perpendiculaire audit axe et situé en aval du plan P1, et en aval des bords de fuite (54c) situés dans un plan P3 perpendiculaire audit axe et situé en aval dudit plan P2, caractérisé en ce que ce le module est formé d’une seule pièce, les aubes s’étendant sensiblement radialement entre les parois, et les bras se prolongeant vers l’aval et étant chacun intimement liés avec une des aubes. Figure pour l'abrégé : Figure 4Turbine module (50) for an aircraft turbomachine (10), this module comprising: - arms (52) connecting annular walls (50a, 50b), these arms comprising leading edges (52a) upstream which are situated in a plane P1 perpendicular to said axis, a distributor (54) situated downstream of said arms and comprising stator vanes (54a) which comprise upstream leading edges (54b) situated in a plane P2 perpendicular to said axis and located downstream of plane P1, and downstream of the trailing edges (54c) located in a plane P3 perpendicular to said axis and located downstream of said plane P2, characterized in that the module is formed in one piece, the vanes extending substantially radially between the walls, and the arms extending downstream and each being intimately connected with one of the vanes. Figure for abstract: Figure 4

FR1905762A 2019-05-29 2019-05-29 TURBINE MODULE FOR AN AIRCRAFT TURBOMACHINE Active FR3096724B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR1905762A FR3096724B1 (en) 2019-05-29 2019-05-29 TURBINE MODULE FOR AN AIRCRAFT TURBOMACHINE
PCT/FR2020/050894 WO2020240136A1 (en) 2019-05-29 2020-05-27 Turbine module for an aircraft turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1905762 2019-05-29
FR1905762A FR3096724B1 (en) 2019-05-29 2019-05-29 TURBINE MODULE FOR AN AIRCRAFT TURBOMACHINE

Publications (2)

Publication Number Publication Date
FR3096724A1 FR3096724A1 (en) 2020-12-04
FR3096724B1 true FR3096724B1 (en) 2022-12-23

Family

ID=69375374

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1905762A Active FR3096724B1 (en) 2019-05-29 2019-05-29 TURBINE MODULE FOR AN AIRCRAFT TURBOMACHINE

Country Status (2)

Country Link
FR (1) FR3096724B1 (en)
WO (1) WO2020240136A1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8182204B2 (en) * 2009-04-24 2012-05-22 Pratt & Whitney Canada Corp. Deflector for a gas turbine strut and vane assembly
US8668442B2 (en) * 2010-06-30 2014-03-11 Honeywell International Inc. Turbine nozzles and methods of manufacturing the same
US10221707B2 (en) * 2013-03-07 2019-03-05 Pratt & Whitney Canada Corp. Integrated strut-vane
US9909434B2 (en) * 2015-07-24 2018-03-06 Pratt & Whitney Canada Corp. Integrated strut-vane nozzle (ISV) with uneven vane axial chords

Also Published As

Publication number Publication date
FR3096724A1 (en) 2020-12-04
WO2020240136A1 (en) 2020-12-03

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