WO2010043798A1 - Aube de turbine a performances aerodynamiques ameliorees - Google Patents
Aube de turbine a performances aerodynamiques ameliorees Download PDFInfo
- Publication number
- WO2010043798A1 WO2010043798A1 PCT/FR2009/051897 FR2009051897W WO2010043798A1 WO 2010043798 A1 WO2010043798 A1 WO 2010043798A1 FR 2009051897 W FR2009051897 W FR 2009051897W WO 2010043798 A1 WO2010043798 A1 WO 2010043798A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- protuberance
- trailing edge
- rotor blade
- turbine rotor
- blade according
- Prior art date
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
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- 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
-
- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/301—Cross-sectional characteristics
-
- 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
Definitions
- the invention relates to a turbine blade, in particular a blade of a low-pressure turbine wheel of an airplane turbojet, whose aerodynamic behavior is improved to avoid "delamination" of the boundary layer of the air flow. relative to the surface of the dawn, mainly at the back of the extrados area.
- the invention relates to a turbine blade, characterized in that it comprises at least one protuberance in the vicinity of its trailing edge, extrados side.
- protuberances may advantageously be placed in the vicinity of the radially inner end of said trailing edge and / or in the vicinity of the outer radial end of said trailing edge.
- the calculations result in placing several aforementioned protuberances distributed along the outer radial third of said trailing edge.
- the shape of such a protuberance is preferably generally that of a rounded stud projecting from the surface of the extrados with smooth connection thereto.
- a median section of the protrusion, perpendicular to the trailing edge will have the shape of a half-wave with smooth connection to the extrados surface.
- another section of said protuberance perpendicular to said median section will have the form of a corrugation having a central end and sidewaves muffled.
- said protrusion is similar to the waveform caused to the flat surface of a liquid by the drop of a drop of liquid, this waveform is not, however, isomorphic circumferentially around from the central point.
- FIG. 1 is a partial perspective view of a turbine rotor wheel provided with blades according to the invention
- - Figure 2 is a partial section of the blade, illustrating the profile of a protuberance according to the invention
- - Figure 3 is a partial section in another plane illustrating the profile of said protuberance
- FIG. 3 is a view similar to FIG. 3 illustrating a variant
- FIG. 4 is a schematic view illustrating a step of the method for determining the number and locations of the protuberances along the trailing edge.
- FIG. 1 shows a plurality of rotor blades 11, in this case moving blades oriented generally radially at the periphery of a rotary disc 13.
- each blade of a certain progressive thickness from front to back, is curved between a leading edge 15 and a trailing edge 17.
- the concave portion or intrados 19 is smooth.
- the convex or extrados portion 21 is smooth over most of its surface except, according to the invention, some protuberances 25 distributed in the vicinity and along the trailing edge 17.
- such a protuberance 25 preferably has the overall shape of a rounded stud projecting from the surface of the extrados 21 with smooth connection thereto.
- a median section of said protuberance 25 made perpendicular to the trailing edge 17 is in the form of a simple half-wave with a smooth connection to the upper surface 21. It should be noted that the slope of this half-wave is weaker towards the front than towards the rear. According to this section, the protuberance is connected with continuity to the trailing edge.
- FIG. 4 diagrammatically shows, from left to right, the various phases of the positioning of the protuberances on a blade 11 viewed along the extrados surface 21.
- the grayed portion represents the so-called “delamination” zone 30 on the extrados side and at the neighborhood of the trailing edge.
- this separation zone 30 extends over almost the entire height of the dawn from the edge of leak, with a maximum of width substantially halfway up.
- the analysis of this shape leads to placing a first protuberance 25a in the vicinity of the maximum disturbance zone, that is to say halfway up the blade, near the trailing edge.
- the result of this first simulation shows a decrease in the disturbance surface at mid-height but persistent disturbances at the radial ends, internal and external. This leads to placing another protuberance 25b in the vicinity of the radially inner end of the trailing edge and / or in the vicinity of the outer radial end 25c of the trailing edge.
- the arrangement of three protuberances results in reducing the width of the disturbance zone or detachment zone over practically the entire radial height of the dawn with however a zone of pronounced disturbance persistence between the central protrusion and the external protuberance.
Abstract
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA2740030A CA2740030C (fr) | 2008-10-13 | 2009-10-06 | Aube de turbine a performances aerodynamiques ameliorees |
EP09755969.4A EP2344720B2 (fr) | 2008-10-13 | 2009-10-06 | Aube de rotor de turbine avec protubérances côte extrados pour atténuer les phénomènes de décollement |
US13/123,922 US8794926B2 (en) | 2008-10-13 | 2009-10-06 | Turbine blade with improved aerodynamic performance |
CN200980140739.XA CN102187063B (zh) | 2008-10-13 | 2009-10-06 | 具有改善的空气动力学性能的涡轮机叶片 |
RU2011119021/06A RU2520273C2 (ru) | 2008-10-13 | 2009-10-06 | Лопатка турбины с улучшенной аэродинамической характеристикой и колесо турбины, содержащее такую лопатку |
JP2011530526A JP5710488B2 (ja) | 2008-10-13 | 2009-10-06 | 空気力学的性能が改善されたタービンブレード |
BRPI0920177A BRPI0920177A2 (pt) | 2008-10-13 | 2009-10-06 | pá de rotor de turbina e roda de turbina |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0856903A FR2937078B1 (fr) | 2008-10-13 | 2008-10-13 | Aube de turbine a performances aerodynamiques ameliorees. |
FR0856903 | 2008-10-13 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2010043798A1 true WO2010043798A1 (fr) | 2010-04-22 |
Family
ID=40668990
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2009/051897 WO2010043798A1 (fr) | 2008-10-13 | 2009-10-06 | Aube de turbine a performances aerodynamiques ameliorees |
Country Status (9)
Country | Link |
---|---|
US (1) | US8794926B2 (fr) |
EP (1) | EP2344720B2 (fr) |
JP (1) | JP5710488B2 (fr) |
CN (1) | CN102187063B (fr) |
BR (1) | BRPI0920177A2 (fr) |
CA (1) | CA2740030C (fr) |
FR (1) | FR2937078B1 (fr) |
RU (1) | RU2520273C2 (fr) |
WO (1) | WO2010043798A1 (fr) |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB201016455D0 (en) * | 2010-09-30 | 2010-11-17 | Imp Innovations Ltd | Fluid flow modification |
DE102012222953A1 (de) * | 2012-12-12 | 2014-06-26 | Honda Motor Co., Ltd. | Flügelprofil für einen Axialströmungskompressor |
GB2523026B (en) * | 2013-04-05 | 2016-08-31 | Bacon Andy | Improvements in the fuel efficiency of road vehicles |
FR3023635B1 (fr) * | 2014-07-10 | 2018-05-25 | Safran Aircraft Engines | Procede de modelisation d'une baignoire d'une aube |
FR3027623B1 (fr) * | 2014-10-23 | 2021-05-28 | Snecma | Aube mobile de rotor a reponse acoustique reduite |
US20160208626A1 (en) * | 2015-01-19 | 2016-07-21 | United Technologies Corporation | Integrally bladed rotor with pressure side thickness on blade trailing edge |
GB201512688D0 (en) * | 2015-07-20 | 2015-08-26 | Rolls Royce Plc | Aerofoil |
US10519976B2 (en) * | 2017-01-09 | 2019-12-31 | Rolls-Royce Corporation | Fluid diodes with ridges to control boundary layer in axial compressor stator vane |
CA3069372A1 (fr) * | 2017-09-29 | 2019-04-04 | Ihi Corporation | Ventilateur a flux axial, procede de modification d'une aube de compresseur et de turbine, et aube obtenue par modification |
US10995631B2 (en) | 2019-04-01 | 2021-05-04 | Pratt & Whitney Canada Corp. | Method of shedding ice and fan blade |
GB2592009B (en) * | 2020-02-11 | 2022-08-24 | Gkn Aerospace Sweden Ab | Compressor blade |
CN111622808B (zh) * | 2020-05-25 | 2021-05-04 | 武汉大学 | 一种基于汽轮机叶型改造的仿生叶片及设计方法 |
JP7417207B2 (ja) | 2020-12-03 | 2024-01-18 | 株式会社Ihi | 軸流型のファン、圧縮機及びタービンの翼の改造方法、及び当該改造により得られる翼 |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3578264A (en) * | 1968-07-09 | 1971-05-11 | Battelle Development Corp | Boundary layer control of flow separation and heat exchange |
US3588005A (en) * | 1969-01-10 | 1971-06-28 | Scott C Rethorst | Ridge surface system for maintaining laminar flow |
US4830315A (en) * | 1986-04-30 | 1989-05-16 | United Technologies Corporation | Airfoil-shaped body |
US20020079405A1 (en) * | 2000-07-24 | 2002-06-27 | Thombi Layukallo | Control of flow separation and related phenomena on aerodynamic surfaces |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2074201A (en) * | 1934-01-29 | 1937-03-16 | Avions Kellner Bechereau Soc | Airfoil used in aeronautics |
DE681479C (de) * | 1937-03-04 | 1939-09-23 | Escher Wyss Maschinenfabrik G | Leitschaufel fuer Dampf- oder Gasturbinen, insbesondere fuer den Niederdruckteil solcher Turbinen |
US2150299A (en) * | 1937-10-11 | 1939-03-14 | Telfer Edmund Victor | Propeller |
DE845900C (de) | 1943-08-07 | 1952-08-07 | Freiherr Re Koenig-Fachsenfeld | Einrichtung zur Beeinflussung der Grenzschicht an Koerpern aller Art |
US2800291A (en) * | 1950-10-24 | 1957-07-23 | Stephens Arthur Veryan | Solid boundary surface for contact with a relatively moving fluid medium |
US4720239A (en) * | 1982-10-22 | 1988-01-19 | Owczarek Jerzy A | Stator blades of turbomachines |
DE3325663C2 (de) * | 1983-07-15 | 1985-08-22 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Axial durchströmtes Schaufelgitter einer mit Gas oder Dampf betriebenen Turbine |
US4813633A (en) | 1986-12-29 | 1989-03-21 | United Technologies Corporation | Airfoil trailing edge |
US5088665A (en) * | 1989-10-31 | 1992-02-18 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Serrated trailing edges for improving lift and drag characteristics of lifting surfaces |
SU1765469A1 (ru) * | 1990-07-16 | 1992-09-30 | Военная академия им.Ф.Э.Дзержинского | Лопатка осевой турбомашины |
GB9920564D0 (en) * | 1999-08-31 | 1999-11-03 | Rolls Royce Plc | Axial flow turbines |
EP1580399B1 (fr) * | 2004-03-25 | 2006-11-15 | Rolls-Royce Deutschland Ltd & Co KG | Compresseur pour un moteur d'avion |
US8083487B2 (en) * | 2007-07-09 | 2011-12-27 | General Electric Company | Rotary airfoils and method for fabricating same |
-
2008
- 2008-10-13 FR FR0856903A patent/FR2937078B1/fr active Active
-
2009
- 2009-10-06 EP EP09755969.4A patent/EP2344720B2/fr active Active
- 2009-10-06 BR BRPI0920177A patent/BRPI0920177A2/pt not_active Application Discontinuation
- 2009-10-06 US US13/123,922 patent/US8794926B2/en active Active
- 2009-10-06 RU RU2011119021/06A patent/RU2520273C2/ru active
- 2009-10-06 WO PCT/FR2009/051897 patent/WO2010043798A1/fr active Application Filing
- 2009-10-06 CN CN200980140739.XA patent/CN102187063B/zh active Active
- 2009-10-06 CA CA2740030A patent/CA2740030C/fr active Active
- 2009-10-06 JP JP2011530526A patent/JP5710488B2/ja not_active Expired - Fee Related
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3578264A (en) * | 1968-07-09 | 1971-05-11 | Battelle Development Corp | Boundary layer control of flow separation and heat exchange |
US3578264B1 (fr) * | 1968-07-09 | 1991-11-19 | Univ Michigan | |
US3588005A (en) * | 1969-01-10 | 1971-06-28 | Scott C Rethorst | Ridge surface system for maintaining laminar flow |
US4830315A (en) * | 1986-04-30 | 1989-05-16 | United Technologies Corporation | Airfoil-shaped body |
US20020079405A1 (en) * | 2000-07-24 | 2002-06-27 | Thombi Layukallo | Control of flow separation and related phenomena on aerodynamic surfaces |
Also Published As
Publication number | Publication date |
---|---|
US8794926B2 (en) | 2014-08-05 |
CA2740030A1 (fr) | 2010-04-22 |
RU2520273C2 (ru) | 2014-06-20 |
EP2344720B2 (fr) | 2019-10-23 |
US20110200442A1 (en) | 2011-08-18 |
CN102187063A (zh) | 2011-09-14 |
EP2344720A1 (fr) | 2011-07-20 |
FR2937078A1 (fr) | 2010-04-16 |
CN102187063B (zh) | 2015-01-14 |
CA2740030C (fr) | 2017-01-17 |
JP5710488B2 (ja) | 2015-04-30 |
JP2012505340A (ja) | 2012-03-01 |
EP2344720B1 (fr) | 2016-04-20 |
FR2937078B1 (fr) | 2011-09-23 |
RU2011119021A (ru) | 2012-11-20 |
BRPI0920177A2 (pt) | 2015-12-29 |
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