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 layerInfo
- 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
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.
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)
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)
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 |
-
1978
- 1978-07-31 FR FR7822614A patent/FR2432608A1/en active Granted
Patent Citations (4)
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)
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
Date | Code | Title | Description |
---|---|---|---|
ST | Notification of lapse |