FR3053999B1 - IMPROVED PRODUCTION OF VANE COOLING HOLES - Google Patents

IMPROVED PRODUCTION OF VANE COOLING HOLES Download PDF

Info

Publication number
FR3053999B1
FR3053999B1 FR1656722A FR1656722A FR3053999B1 FR 3053999 B1 FR3053999 B1 FR 3053999B1 FR 1656722 A FR1656722 A FR 1656722A FR 1656722 A FR1656722 A FR 1656722A FR 3053999 B1 FR3053999 B1 FR 3053999B1
Authority
FR
France
Prior art keywords
duct
cooling holes
improved production
internal cavity
vane 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
FR1656722A
Other languages
French (fr)
Other versions
FR3053999A1 (en
Inventor
Jean Luc Vollebregt Matthieu
Davy Boisnault Franck
Marc Herb Vincent
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 FR1656722A priority Critical patent/FR3053999B1/en
Publication of FR3053999A1 publication Critical patent/FR3053999A1/en
Application granted granted Critical
Publication of FR3053999B1 publication Critical patent/FR3053999B1/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
    • F01D5/186—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
    • 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

L'invention concerne un procédé de réalisation d'une aube (10) de turbomachine comportant une paroi d'intrados (12), une paroi d'extrados, une cavité interne et au moins un trou de refroidissement (18) réalisé dans l'une de la paroi d'intrados et/ou d'extrados, comportant un conduit (20) qui relie la cavité interne à l'extérieur, une extrémité du conduit débouchant dans la cavité interne, l'autre extrémité dudit conduit (20) débouchant dans ladite paroi d'intrados et/ou d'extrados par une embouchure (22), le procédé comportant une étape de moulage pour la production de l'aube (10) et une étape de perçage du conduit (20), caractérisé en ce que l'embouchure (22) est réalisée lors de l'étape de moulage et l'étape de perçage consiste à percer uniquement ledit au moins un conduit (20).The invention relates to a method for producing a turbine engine blade (10) comprising a lower surface wall (12), an upper surface wall, an internal cavity and at least one cooling hole (18) produced in the one of the lower and / or upper surface wall, comprising a duct (20) which connects the internal cavity to the outside, one end of the duct opening into the internal cavity, the other end of said duct (20) opening in said bottom and / or top wall by a mouth (22), the method comprising a molding step for the production of the blade (10) and a step of drilling the duct (20), characterized in that that the mouth (22) is produced during the molding step and the drilling step consists in piercing only said at least one conduit (20).

FR1656722A 2016-07-13 2016-07-13 IMPROVED PRODUCTION OF VANE COOLING HOLES Active FR3053999B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1656722A FR3053999B1 (en) 2016-07-13 2016-07-13 IMPROVED PRODUCTION OF VANE COOLING HOLES

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1656722 2016-07-13
FR1656722A FR3053999B1 (en) 2016-07-13 2016-07-13 IMPROVED PRODUCTION OF VANE COOLING HOLES

Publications (2)

Publication Number Publication Date
FR3053999A1 FR3053999A1 (en) 2018-01-19
FR3053999B1 true FR3053999B1 (en) 2020-06-26

Family

ID=57906677

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1656722A Active FR3053999B1 (en) 2016-07-13 2016-07-13 IMPROVED PRODUCTION OF VANE COOLING HOLES

Country Status (1)

Country Link
FR (1) FR3053999B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5419681A (en) * 1993-01-25 1995-05-30 General Electric Company Film cooled wall
US6547524B2 (en) * 2001-05-21 2003-04-15 United Technologies Corporation Film cooled article with improved temperature tolerance
FR2896710B1 (en) * 2006-01-27 2009-10-30 Snecma Sa PROCESS FOR MANUFACTURING TURBOMACHINE COMPONENT WITH COOLING AIR EXHAUST ORIFICES
US9316104B2 (en) * 2012-10-25 2016-04-19 United Technologies Corporation Film cooling channel array having anti-vortex properties

Also Published As

Publication number Publication date
FR3053999A1 (en) 2018-01-19

Similar Documents

Publication Publication Date Title
FR3027951B1 (en) BATH OF SUMMIT OF DAWN OF A TURBINE OF TURBOMACHINE
BR112018070426A2 (en) subsea collector and method for installing a subsea collector
EP2787174A3 (en) Gas turbine engines with turbine airfoil cooling
FR3034129B1 (en) MOBILE TURBINE AUB WITH IMPROVED DESIGN FOR AN AIRCRAFT TURBOMACHINE
WO2015160403A3 (en) Additive manufactured non-round, septum tied, conformal high pressure tubing
FR3059353B1 (en) AIRBOARD TURBOMACHINE EXIT OUTPUT AUDE COMPRISING A LUBRICANT-BENDED ZONE HAVING AN IMPROVED DESIGN
FR3069291B1 (en) SUPPLY DUCT FOR A COMPRESSOR OF A TURBOMACHINE
FR3039199B1 (en) BLADE OF HIGH PRESSURE DISTRIBUTOR WITH A VARIABLE GEOMETRY INSERT
FR3014142B1 (en) PROPULSIVE ASSEMBLY COMPRISING A DRAIN FLUID RETENTION BOX
FR3053999B1 (en) IMPROVED PRODUCTION OF VANE COOLING HOLES
FR3021698B1 (en) TURBINE BLADE, INCLUDING A CENTRAL COOLING DUCT THERMALLY INSULATED FROM THE BLADE WALLS BY TWO JOINT SIDE CAVITIES DOWNSTREAM FROM THE CENTRAL DUCT
FR3099801B1 (en) Set for a turbomachine turbine
FR3026135B1 (en) TURBOMACHINE BEARING LUBRICATION DEVICE
FR3060056B1 (en) CAP FOR TURBOMACHINE ROTATING INPUT HOOD, COMPRISING AERODYNAMIC EXTERNAL WALL BEYOND A CONE ATTACHMENT
FR3036144B1 (en) TURBOMACHINE PROPELLER
ES2609983T3 (en) Submerged refractory inlet nozzle
EP3561230A3 (en) Spiral cooling flow cavities for gas turbine engine components
FR3070714B1 (en) TURBOMACHINE VANE WITH IMPROVED COOLING HOLES
RU2015112104A (en) GAS TURBINE SHOULDER COOLING TUBE WITH DIVIDING WALL
FR3079551B1 (en) TURBINE DISTRIBUTOR BLADE HAVING AN INTERNAL COOLING WALL ARISING FROM ADDITIVE MANUFACTURING
FR3064466B1 (en) METHOD OF MANUFACTURING A MENSTRUAL CUP.
WO2017191075A3 (en) A turbomachine blade or vane having a vortex generating element
CY1123547T1 (en) APPARATUS AND METHOD OF CREATING CONNECTING ARMS FOR IRRIGATION LINES ALONG A LENGTH OF A PREFABRICATED FLADENED PIPE
FR3097028B1 (en) Method of manufacturing a flame tube for a turbomachine
RU163006U1 (en) DEVICE FOR RELEASING EXHAUST GASES OF A GAS TURBINE ENGINE

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20180119

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4

PLFP Fee payment

Year of fee payment: 5

PLFP Fee payment

Year of fee payment: 6

PLFP Fee payment

Year of fee payment: 7

PLFP Fee payment

Year of fee payment: 8