FR3089549B1 - Turbomachine hollow blade fitted with primary disruptors and secondary disruptors - Google Patents

Turbomachine hollow blade fitted with primary disruptors and secondary disruptors Download PDF

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Publication number
FR3089549B1
FR3089549B1 FR1872505A FR1872505A FR3089549B1 FR 3089549 B1 FR3089549 B1 FR 3089549B1 FR 1872505 A FR1872505 A FR 1872505A FR 1872505 A FR1872505 A FR 1872505A FR 3089549 B1 FR3089549 B1 FR 3089549B1
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FR
France
Prior art keywords
disruptors
primary
hollow blade
blade fitted
disruptor
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
FR1872505A
Other languages
French (fr)
Other versions
FR3089549A1 (en
Inventor
Paul Olivier Danre
Jean-Luc Bacha
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 FR1872505A priority Critical patent/FR3089549B1/en
Publication of FR3089549A1 publication Critical patent/FR3089549A1/en
Application granted granted Critical
Publication of FR3089549B1 publication Critical patent/FR3089549B1/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
    • 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
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
    • 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

Aube creuse (10) de turbomachine (100), ladite aube comprenant un circuit de refroidissement (12), une paroi (13) du circuit interne (12) présentant au moins une nervure formant un perturbateur primaire (14) configuré pour perturber un flux de refroidissement circulant au sein du circuit de refroidissement (12), le perturbateur primaire présentant une section transverse en forme de premier quadrilatère, le perturbateur primaire (14) étant pourvu d’au moins une nervure et/ou d’au moins une rainure formant un perturbateur secondaire (16) configuré pour perturber le flux de refroidissement au sein du circuit de refroidissement (12), le perturbateur secondaire (16) présentant une section transverse en forme de deuxième quadrilatère. Figure pour l’abrégé : Fig. 2.Hollow blade (10) of a turbomachine (100), said blade comprising a cooling circuit (12), a wall (13) of the internal circuit (12) having at least one rib forming a primary disruptor (14) configured to disturb a flow cooling circulating within the cooling circuit (12), the primary disturber having a cross section in the form of a first quadrilateral, the primary disturber (14) being provided with at least one rib and / or at least one groove forming a secondary disruptor (16) configured to disrupt the cooling flow within the cooling circuit (12), the secondary disruptor (16) having a cross section in the form of a second quadrilateral. Figure for the abstract: Fig. 2.

FR1872505A 2018-12-07 2018-12-07 Turbomachine hollow blade fitted with primary disruptors and secondary disruptors Active FR3089549B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1872505A FR3089549B1 (en) 2018-12-07 2018-12-07 Turbomachine hollow blade fitted with primary disruptors and secondary disruptors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1872505A FR3089549B1 (en) 2018-12-07 2018-12-07 Turbomachine hollow blade fitted with primary disruptors and secondary disruptors

Publications (2)

Publication Number Publication Date
FR3089549A1 FR3089549A1 (en) 2020-06-12
FR3089549B1 true FR3089549B1 (en) 2021-01-29

Family

ID=66530168

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1872505A Active FR3089549B1 (en) 2018-12-07 2018-12-07 Turbomachine hollow blade fitted with primary disruptors and secondary disruptors

Country Status (1)

Country Link
FR (1) FR3089549B1 (en)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH05179902A (en) * 1992-01-07 1993-07-20 Mitsubishi Heavy Ind Ltd Gas turbine air-cooled cascade blade
JPH07190663A (en) * 1993-11-16 1995-07-28 Mitsubishi Heavy Ind Ltd Heating tube
DE19963374B4 (en) * 1999-12-28 2007-09-13 Alstom Device for cooling a flow channel wall surrounding a flow channel with at least one rib element
KR102138327B1 (en) * 2013-11-15 2020-07-27 한화에어로스페이스 주식회사 Turbine
KR101797370B1 (en) * 2016-07-04 2017-12-12 두산중공업 주식회사 Gas Turbine Blade

Also Published As

Publication number Publication date
FR3089549A1 (en) 2020-06-12

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