EP0020426B1 - Grille d'aubes pour turbine - Google Patents

Grille d'aubes pour turbine Download PDF

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Publication number
EP0020426B1
EP0020426B1 EP79901202A EP79901202A EP0020426B1 EP 0020426 B1 EP0020426 B1 EP 0020426B1 EP 79901202 A EP79901202 A EP 79901202A EP 79901202 A EP79901202 A EP 79901202A EP 0020426 B1 EP0020426 B1 EP 0020426B1
Authority
EP
European Patent Office
Prior art keywords
grid
blade
blades
channel
turbine
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.)
Expired
Application number
EP79901202A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0020426A1 (fr
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.)
Alstom 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
Publication of EP0020426A1 publication Critical patent/EP0020426A1/fr
Application granted granted Critical
Publication of EP0020426B1 publication Critical patent/EP0020426B1/fr
Expired legal-status Critical Current

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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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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

Definitions

  • the present invention relates to a grid of blades for a turbine comprising a series of blades arranged between a ceiling and a floor.
  • This series of blades thus defines a series of channels traversed by a fluid, each channel being limited by the upper surface of a blade and by the lower surface of the neighboring blade as well as by the floor and the ceiling.
  • the slippage generates a whirlwind of trigonometric direction at the ceiling of the channel and in the opposite direction to the floor for an observer placed downstream of the grid of blades.
  • One known way of reducing secondary losses consists in reducing the aerodynamic load of the blades, which amounts to decreasing the difference in average pressure between lower and upper surfaces by decreasing for example the pitch pitch ratio of the blade grid.
  • this method has the drawback of increasing the friction losses in the healthy zone of the channel, so that the gain obtained on the secondary losses can be canceled out by increasing the friction losses in the main flow.
  • the invention aims to reduce secondary losses without affecting the friction losses in the main flow.
  • This object is achieved by a grid of blades which is characterized in that it comprises for each blade at least two pierced communications, one in the ceiling and the other in the floor, each communication opening at one end in the vicinity of the upper surface of the blade at the neck of the channel limited by the upper surface of said blade at a point remote from the middle part of this channel, and at the other end at a point located upstream of said grid.
  • the neck of the canal is where the upper surface of the dawn and the lower surface of the neighboring dawn which delimits it are closest.
  • the grid is characterized in that it comprises communications associated with the blades and pierced in the ceiling, each communication opening at one end in the vicinity of the upper surface of the blade at the neck of the channel limited by the 'extrados of said blade at a point remote from the middle part of this channel, and at the other end at a point located upstream of said grid.
  • the grid is characterized in that it comprises communications associated with the blades and drilled in the floor, each communication opening at one end in the vicinity of the upper surface of the blade at the neck of the channel limited by the upper surface of said blade at a point distant from the middle part of this channel, and at the other end at a point situated upstream of said grid.
  • the grid is characterized in that it comprises communications associated with the blades drilled in the floor, each communication opening at one end in the vicinity of the upper surface of the blade at the neck of the channel limited by the 'extrados of said blade at a point remote from the middle part of this channel, and at the other end at a point located upstream of said grid.
  • the grid is characterized in that it includes communications associated with the blades and pierced in the ceiling, each communication opening at one end in the vicinity of the upper surface of the blade at the neck of the channel limited by the upper surface of said blade at a point distant from the middle part of this channel, and at the other end at a point situated upstream of said grid.
  • the point located near the upper surface of the dawn in the neck of the canal is the point of the canal where the pressure is minimal.
  • the suction surface pressure is reduced by communication with a higher pressure chamber, thereby reducing the average pressure difference between suction and pressure surfaces.
  • this pressure reduction takes place only in line with the floor and / or the ceiling of the canal, thereby reducing secondary losses, while the aerodynamic load remains optimal in the healthy part of the canal.
  • This reduction in depression at the level of the upper surface results in a reduction in the slip of the boundary layers and in losses by secondary flow.
  • FIG. 1 there are shown two blades A and B which are part of a crown and whose foot is fixed on a floor 1 and the head on a ceiling 2.
  • the floor and the ceiling are usually cylindrical or frustoconical surfaces.
  • Channel 3 has a neck 6 (see Figure 3) which is where the upper surface of the dawn A is closest to the lower surface of dawn B.
  • FIG. 2 there is shown in axial section a turbine provided with fixed vane grids 4 and movable 5 according to the invention.
  • the fixed blade grid 4 comprises for each blade a communication 13 hollowed out in the floor 11 between a point located in the vicinity of the upper surface of the blade at the level of the neck 6 of the channel at a point distant from the middle part of this channel and a point located upstream of the vane grid 4 (see Figure 3) in a region where the pressure is high.
  • the neck 6 of the canal is the minimum pressure point along the upper surface.
  • the fixed grid 4 also includes, for each blade, a communication 14 hollowed out in the ceiling 12 between a point located in the vicinity of the upper surface of the blade at the level of the neck 6 of the channel at a point distant from the middle part of this channel and ending upstream of said blade grid in a region 30 where the pressure is high.
  • the movable blade grid 5 includes, for each blade, a communication 24 hollowed out in the ceiling 22 which starts from a point located in the vicinity of the upper surface of the blade at the neck 6 of the channel (minimum pressure point ) at a point distant from the middle part of this channel and which ends upstream of said grid 5 (high pressure region).
  • the movable blade grid 5 also includes for each blade a communication 23 hollowed out in the floor 21 which starts from a point located in the vicinity of the upper surface of the blade at the neck 6 of the channel (minimum pressure point) at a point distant from the middle part of this channel and which ends upstream of the grid 5 (high pressure region).
  • the turbine according to the invention could comprise such communications only on the movable grids or on the fixed grids hollowed out in the floor and / or the ceiling of these grids.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP79901202A 1978-10-05 1980-04-22 Grille d'aubes pour turbine Expired EP0020426B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR7828461A FR2438157A1 (fr) 1978-10-05 1978-10-05 Grille d'aubes pour turbine ou compresseur
FR7828461 1978-10-05

Publications (2)

Publication Number Publication Date
EP0020426A1 EP0020426A1 (fr) 1981-01-07
EP0020426B1 true EP0020426B1 (fr) 1983-03-09

Family

ID=9213367

Family Applications (1)

Application Number Title Priority Date Filing Date
EP79901202A Expired EP0020426B1 (fr) 1978-10-05 1980-04-22 Grille d'aubes pour turbine

Country Status (7)

Country Link
US (1) US4362465A (enrdf_load_stackoverflow)
EP (1) EP0020426B1 (enrdf_load_stackoverflow)
JP (1) JPS55500757A (enrdf_load_stackoverflow)
BE (1) BE886658A (enrdf_load_stackoverflow)
DE (1) DE2964997D1 (enrdf_load_stackoverflow)
FR (1) FR2438157A1 (enrdf_load_stackoverflow)
WO (1) WO1980000729A1 (enrdf_load_stackoverflow)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ZA8234B (en) * 1981-01-05 1982-11-24 Alsthom Atlantique A turbine stage
US4463552A (en) * 1981-12-14 1984-08-07 United Technologies Corporation Combined surge bleed and dust removal system for a fan-jet engine
JPH0833098B2 (ja) * 1989-02-27 1996-03-29 株式会社次世代航空機基盤技術研究所 軸流圧縮機の翼列構造
JPH0399803U (enrdf_load_stackoverflow) * 1990-01-29 1991-10-18
FR2666846B1 (fr) * 1990-09-13 1992-10-16 Alsthom Gec Grille d'aubes pour turbomachine munie de fentes d'aspiration dans le plafond et/ou dans le plancher et turbomachine comportant ces grilles.
US5382135A (en) * 1992-11-24 1995-01-17 United Technologies Corporation Rotor blade with cooled integral platform
ATE371097T1 (de) 1998-02-26 2007-09-15 Allison Advanced Dev Co Zapfsystem für eine kompressorwand sowie betriebsverfahren
DE102004030597A1 (de) * 2004-06-24 2006-01-26 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Aussenradstrahlerzeugung am Stator
DE102008036294A1 (de) * 2008-08-04 2010-02-11 Mtu Aero Engines Gmbh Axialverdichter mit Verdichtergitter
DE102008052409A1 (de) 2008-10-21 2010-04-22 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit saugseitennaher Randenergetisierung
FR2958694B1 (fr) * 2010-04-07 2014-04-18 Snecma Compresseur de moteur, en particulier de turboreacteur d'aeronef, muni d'un systeme de prelevement d'air
PL3181613T3 (pl) 2015-12-17 2019-01-31 Henkel Ag & Co. Kgaa Kompleksy tytanu jako katalizatory wulkanizacji
JP7356285B2 (ja) * 2019-07-31 2023-10-04 三菱重工業株式会社 軸流タービン

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR341014A (fr) * 1903-10-15 1904-07-27 Georges Westinghouse Perfectionnements dans les turbines à fluide sous pression
FR833985A (fr) * 1937-02-24 1938-11-08 Rheinmetall Borsig Ag Perfectionnements apportés aux turbo-compresseurs en vue d'empêcher les filets fluides de se détacher de la paroi
US2291828A (en) * 1940-05-04 1942-08-04 Westinghouse Electric & Mfg Co Turbine blading
DE876282C (de) * 1942-12-22 1953-05-11 Siemens Ag Verdichter mit radial beaufschlagtem Schaufelgitter und Grenzschichtabsaugung
DE1106027B (de) 1955-07-18 1961-05-04 Power Jets Res & Dev Ltd Axialverdichter, dessen Lauf- und/oder Leitschaufeln mit einem Deckband versehen sind
JPS51149406A (en) * 1975-06-18 1976-12-22 Toshiba Corp Turbine
JPS5254807A (en) * 1975-10-31 1977-05-04 Hitachi Ltd Axial-flow fluid machine
JPS5254809A (en) * 1975-10-31 1977-05-04 Hitachi Ltd Axial-flow fluid machine construction
JPS6014161A (ja) * 1983-07-06 1985-01-24 Ngk Spark Plug Co Ltd 空燃比センサ

Also Published As

Publication number Publication date
FR2438157B1 (enrdf_load_stackoverflow) 1981-07-17
JPS55500757A (enrdf_load_stackoverflow) 1980-10-09
FR2438157A1 (fr) 1980-04-30
WO1980000729A1 (fr) 1980-04-17
EP0020426A1 (fr) 1981-01-07
DE2964997D1 (en) 1983-04-14
US4362465A (en) 1982-12-07
BE886658A (fr) 1981-06-15

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