FR2432608A1 - Prevention of turbulence blades - is achieved by fitting ailerons near blade root and tip to deter breaking away of boundary layer - Google Patents

Prevention of turbulence blades - is achieved by fitting ailerons near blade root and tip to deter breaking away of boundary layer

Info

Publication number
FR2432608A1
FR2432608A1 FR7822614A FR7822614A FR2432608A1 FR 2432608 A1 FR2432608 A1 FR 2432608A1 FR 7822614 A FR7822614 A FR 7822614A FR 7822614 A FR7822614 A FR 7822614A FR 2432608 A1 FR2432608 A1 FR 2432608A1
Authority
FR
France
Prior art keywords
ailerons
tip
fitting
boundary layer
breaking away
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.)
Granted
Application number
FR7822614A
Other languages
French (fr)
Other versions
FR2432608B1 (en
Inventor
Gilbert Riollet
Raymond Bessay
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.)
Alsthom Atlantique SA
Original Assignee
Alsthom Atlantique 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 Alsthom Atlantique SA filed Critical Alsthom Atlantique SA
Priority to FR7822614A priority Critical patent/FR2432608A1/en
Publication of FR2432608A1 publication Critical patent/FR2432608A1/en
Application granted granted Critical
Publication of FR2432608B1 publication Critical patent/FR2432608B1/fr
Granted legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations

Landscapes

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

Abstract

When air flows between adjacent blades of a turbine or compressor there is a tendency for the boundary layer to break away near the trailing edge of the convex side of the trailing edge in the region of the tip and the root of the blade. This effect and the consequent loss of efficiency. It can be reduced by fitting small ailerons (4, 5), to the convex side of the blade. The ailerons consist of small strips inclined to the convex surface so that the air flow is prevented from breaking away from the blade surface.
FR7822614A 1978-07-31 1978-07-31 Prevention of turbulence blades - is achieved by fitting ailerons near blade root and tip to deter breaking away of boundary layer Granted FR2432608A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR7822614A FR2432608A1 (en) 1978-07-31 1978-07-31 Prevention of turbulence blades - is achieved by fitting ailerons near blade root and tip to deter breaking away of boundary layer

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7822614A FR2432608A1 (en) 1978-07-31 1978-07-31 Prevention of turbulence blades - is achieved by fitting ailerons near blade root and tip to deter breaking away of boundary layer

Publications (2)

Publication Number Publication Date
FR2432608A1 true FR2432608A1 (en) 1980-02-29
FR2432608B1 FR2432608B1 (en) 1981-10-23

Family

ID=9211408

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7822614A Granted FR2432608A1 (en) 1978-07-31 1978-07-31 Prevention of turbulence blades - is achieved by fitting ailerons near blade root and tip to deter breaking away of boundary layer

Country Status (1)

Country Link
FR (1) FR2432608A1 (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2485620A1 (en) * 1980-06-24 1981-12-31 Mtu Muenchen Gmbh DEVICE FOR REDUCING SECONDARY LOSSES IN A TURBOMACHINE FLOW CONDUIT WITH AUBAGES
EP0978632A1 (en) * 1998-08-07 2000-02-09 Asea Brown Boveri AG Turbomachine with intermediate blades as flow dividers
US20080095614A1 (en) * 2006-10-20 2008-04-24 Snecma Fan platform fin
FR2938871A1 (en) * 2008-11-25 2010-05-28 Snecma Blade grid for use as e.g. mobile wheel of compressor of aeronautical turbomachine, has rings with discharge guides placed circumferentially between blades, where rings are extended along directions parallel to skeleton lines of blades
FR2939852A1 (en) * 2008-12-15 2010-06-18 Snecma Stator blade stage for compressor of turboshaft engine e.g. turbopropeller engine, has intermediate blades with axial length or radial height less than that of rectifier blades and extend radially between rectifier blades
WO2021069817A1 (en) * 2019-10-10 2021-04-15 Safran Aircraft Engines Variable-pitch stator vane comprising aerodynamic fins

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3039736A (en) * 1954-08-30 1962-06-19 Pon Lemuel Secondary flow control in fluid deflecting passages
FR1373327A (en) * 1962-10-29 1964-09-25 Gen Electric Special blade structure for compressor or turbine
FR2054402A5 (en) * 1969-07-23 1971-04-16 Dettmering Wilhelm
DE2135286A1 (en) * 1971-07-15 1973-01-25 Wilhelm Prof Dr Ing Dettmering RUNNER AND GUIDE WHEEL GRILLE FOR TURBO MACHINERY

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3039736A (en) * 1954-08-30 1962-06-19 Pon Lemuel Secondary flow control in fluid deflecting passages
FR1373327A (en) * 1962-10-29 1964-09-25 Gen Electric Special blade structure for compressor or turbine
FR2054402A5 (en) * 1969-07-23 1971-04-16 Dettmering Wilhelm
DE2135286A1 (en) * 1971-07-15 1973-01-25 Wilhelm Prof Dr Ing Dettmering RUNNER AND GUIDE WHEEL GRILLE FOR TURBO MACHINERY

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2485620A1 (en) * 1980-06-24 1981-12-31 Mtu Muenchen Gmbh DEVICE FOR REDUCING SECONDARY LOSSES IN A TURBOMACHINE FLOW CONDUIT WITH AUBAGES
US4420288A (en) * 1980-06-24 1983-12-13 Mtu Motoren- Und Turbinen-Union Gmbh Device for the reduction of secondary losses in a bladed flow duct
EP0978632A1 (en) * 1998-08-07 2000-02-09 Asea Brown Boveri AG Turbomachine with intermediate blades as flow dividers
US20080095614A1 (en) * 2006-10-20 2008-04-24 Snecma Fan platform fin
FR2907519A1 (en) * 2006-10-20 2008-04-25 Snecma Sa FLOOR PLATFORM FLOOR
EP1916385A1 (en) * 2006-10-20 2008-04-30 Snecma Sponson of fan platform
US8303258B2 (en) 2006-10-20 2012-11-06 Snecma Fan platform fin
FR2938871A1 (en) * 2008-11-25 2010-05-28 Snecma Blade grid for use as e.g. mobile wheel of compressor of aeronautical turbomachine, has rings with discharge guides placed circumferentially between blades, where rings are extended along directions parallel to skeleton lines of blades
FR2939852A1 (en) * 2008-12-15 2010-06-18 Snecma Stator blade stage for compressor of turboshaft engine e.g. turbopropeller engine, has intermediate blades with axial length or radial height less than that of rectifier blades and extend radially between rectifier blades
WO2021069817A1 (en) * 2019-10-10 2021-04-15 Safran Aircraft Engines Variable-pitch stator vane comprising aerodynamic fins
FR3101914A1 (en) * 2019-10-10 2021-04-16 Safran Aircraft Engines Variable-pitch stator vane with aerodynamic fins
US11859502B2 (en) 2019-10-10 2024-01-02 Safran Aircraft Engines Variable-pitch stator vane comprising aerodynamic fins

Also Published As

Publication number Publication date
FR2432608B1 (en) 1981-10-23

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Legal Events

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