FR3115559B1 - Turbine blade with improved cooling circuits - Google Patents

Turbine blade with improved cooling circuits Download PDF

Info

Publication number
FR3115559B1
FR3115559B1 FR2011027A FR2011027A FR3115559B1 FR 3115559 B1 FR3115559 B1 FR 3115559B1 FR 2011027 A FR2011027 A FR 2011027A FR 2011027 A FR2011027 A FR 2011027A FR 3115559 B1 FR3115559 B1 FR 3115559B1
Authority
FR
France
Prior art keywords
blade
cooling circuit
internal
turbine blade
primary cooling
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
FR2011027A
Other languages
French (fr)
Other versions
FR3115559A1 (en
Inventor
Sylvain Paquin
Romain Pierre Cariou
Adrien Bernard Vincent Rollinger
Léandre Ostino
Filippo Pagnoni
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 SA
Original Assignee
Safran SA
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 SA filed Critical Safran SA
Priority to FR2011027A priority Critical patent/FR3115559B1/en
Publication of FR3115559A1 publication Critical patent/FR3115559A1/en
Application granted granted Critical
Publication of FR3115559B1 publication Critical patent/FR3115559B1/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
    • F01D5/187—Convection cooling
    • 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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F05D2250/15—Two-dimensional spiral
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/25—Three-dimensional helical
    • 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)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Aube de turbine avec circuits de refroidissement améliorés Aube (114) de turbine, comprenant un corps d’aube (18) s’étendant selon une direction principale, une paroi intrados (24), une paroi extrados (26), un bord d’attaque (20) et un bord de fuite (22), l’aube (114) comprenant une pluralité de cavités internes (31) définissant un circuit de refroidissement primaire (131) de l’aube (114), un circuit de refroidissement secondaire (132), comprenant une pluralité de conduits internes (140), chacun desdits conduits internes (140) s’étendant au moins partiellement entre une cavité interne (31) du circuit de refroidissement primaire (131) et la paroi intrados (24), et entre la cavité interne (31) du circuit de refroidissement primaire (131) et la paroi extrados (26), de manière à au moins partiellement entourer une cavité interne (31) du circuit de refroidissement primaire (131), chacun desdits conduits internes (140) présentant une section inférieure ou égale à 2 mm. Turbomachine comprenant une telle aube (114). Figure pour l’abrégé : Fig. 3Turbine blade with improved cooling circuits Turbine blade (114), comprising a blade body (18) extending in a main direction, an intrados wall (24), an extrados wall (26), an edge of attack (20) and a trailing edge (22), the blade (114) comprising a plurality of internal cavities (31) defining a primary cooling circuit (131) of the blade (114), a secondary cooling circuit (132), comprising a plurality of internal conduits (140), each of said internal conduits (140) extending at least partially between an internal cavity (31) of the primary cooling circuit (131) and the intrados wall (24), and between the internal cavity (31) of the primary cooling circuit (131) and the extrados wall (26), so as to at least partially surround an internal cavity (31) of the primary cooling circuit (131), each of said internal conduits (140) having a section less than or equal to 2 mm. Turbomachine comprising such a blade (114). Figure for abstract: Fig. 3

FR2011027A 2020-10-28 2020-10-28 Turbine blade with improved cooling circuits Active FR3115559B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2011027A FR3115559B1 (en) 2020-10-28 2020-10-28 Turbine blade with improved cooling circuits

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2011027A FR3115559B1 (en) 2020-10-28 2020-10-28 Turbine blade with improved cooling circuits
FR2011027 2020-10-28

Publications (2)

Publication Number Publication Date
FR3115559A1 FR3115559A1 (en) 2022-04-29
FR3115559B1 true FR3115559B1 (en) 2024-05-03

Family

ID=74758906

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2011027A Active FR3115559B1 (en) 2020-10-28 2020-10-28 Turbine blade with improved cooling circuits

Country Status (1)

Country Link
FR (1) FR3115559B1 (en)

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2163219B (en) * 1981-10-31 1986-08-13 Rolls Royce Cooled turbine blade
US7306026B2 (en) * 2005-09-01 2007-12-11 United Technologies Corporation Cooled turbine airfoils and methods of manufacture
US7568887B1 (en) * 2006-11-16 2009-08-04 Florida Turbine Technologies, Inc. Turbine blade with near wall spiral flow serpentine cooling circuit
US20160222793A1 (en) * 2013-09-09 2016-08-04 United Technologies Corporation Cooling configuration for engine component
US9476306B2 (en) * 2013-11-26 2016-10-25 General Electric Company Components with multi-layered cooling features and methods of manufacture
US10760430B2 (en) * 2017-05-31 2020-09-01 General Electric Company Adaptively opening backup cooling pathway
US20190003316A1 (en) * 2017-06-29 2019-01-03 United Technologies Corporation Helical skin cooling passages for turbine airfoils

Also Published As

Publication number Publication date
FR3115559A1 (en) 2022-04-29

Similar Documents

Publication Publication Date Title
US7887295B2 (en) Z-Notch shape for a turbine blade
US20020159889A1 (en) Turbine blade having a cooled tip shroud
EP1559871A2 (en) Rotor blade for a turbomachine
US6890150B2 (en) Center-located cutter teeth on shrouded turbine blades
JP2005214206A (en) Rotor blade for rotary machine
EP0997612A3 (en) Bladed ducting for turbomachinery
JP2007064215A (en) Method of forming component used for gas turbine engine, structure used for gas turbine engine, structure used for forming train of turbine engine components, and train of turbine engine components
EP3543463A3 (en) Strut for a gas turbine engine
US10577936B2 (en) Mateface surfaces having a geometry on turbomachinery hardware
US11795823B2 (en) Method for designing vane of fan, compressor and turbine of axial flow type, and vane obtained by the designing
US7708528B2 (en) Platform mate face contours for turbine airfoils
US20130101409A1 (en) Turbine component including airfoil with contour
US9581027B2 (en) Airfoil for gas turbine, blade and vane
FR3062675B1 (en) HELICOPTER TURBINE HIGH PRESSURE VENTILATED VANE INCLUDING UPSTREAM DUCT AND CENTRAL COOLING CAVITY
US10513934B2 (en) Z-notch shape for a turbine blade tip shroud
FR3115559B1 (en) Turbine blade with improved cooling circuits
CN107435562B (en) Blade with stress reducing bulbous protrusion at turn opening of coolant channel
CN104763477B (en) A kind of turbomachine movable vane tip segment shroud structure
US10539030B2 (en) Gas turbine engine stator vane platform reinforcement
FR3091724B1 (en) Blade or blade of composite propeller for aircraft incorporating a conformation foam
JP2005214205A (en) Rotor blade for rotary machine
US8721289B2 (en) Flow balancing slot
RU2483217C2 (en) Cooling channel made in wall
US10731489B2 (en) Guide vane segment with curved relief gap
JP2006524301A (en) Turbine bucket with curved rear shank wall for stress reduction

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20220429

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4