EP0475329A2 - Schaufelgitter für Turbomaschinen mit Saugschlitzen - Google Patents

Schaufelgitter für Turbomaschinen mit Saugschlitzen Download PDF

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Publication number
EP0475329A2
EP0475329A2 EP91115218A EP91115218A EP0475329A2 EP 0475329 A2 EP0475329 A2 EP 0475329A2 EP 91115218 A EP91115218 A EP 91115218A EP 91115218 A EP91115218 A EP 91115218A EP 0475329 A2 EP0475329 A2 EP 0475329A2
Authority
EP
European Patent Office
Prior art keywords
blade
slot
blades
grid
channel
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
EP91115218A
Other languages
English (en)
French (fr)
Other versions
EP0475329B1 (de
EP0475329A3 (en
Inventor
Michel Vincent De Paul
François Detanne
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 Holdings SA
Original Assignee
GEC Alsthom 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 GEC Alsthom SA filed Critical GEC Alsthom SA
Publication of EP0475329A2 publication Critical patent/EP0475329A2/de
Publication of EP0475329A3 publication Critical patent/EP0475329A3/fr
Application granted granted Critical
Publication of EP0475329B1 publication Critical patent/EP0475329B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Definitions

  • the present invention relates to a grid of blades for a turbomachine comprising blades arranged between a floor and a ceiling and the floor and / or the ceiling of which is provided with a suction slot in the vicinity of at least certain blades, said slot having a first end situated along the upper surface in a region of the dawn going from the zone of maximum curvature to the neck of the channel between this dawn and the neighboring dawn.
  • the known slits cross the channel and leave from the upper surface of a dawn to join the lower surface of the neighboring dawn.
  • the slot making it possible to increase the efficiency is oriented along an isobaric line and has a length such that the second end is spaced from the upper surface of the blade by a distance between a quarter and the half the width of the canal neck.
  • the pressure along the slit is constant so that the sucked fluid will not be discharged to another place in the slit as in the known grids.
  • the invention also relates to a turbomachine comprising several stages each consisting of a grid of fixed blades followed by a grid of movable blades, said blades of a grid being arranged between a floor and a ceiling, the ceiling of the grids being provided with a seal defining several chambers with the part of the rotor facing, the ceiling of the grid of fixed blades being provided with a suction slot in the vicinity of at least some blades, said slot having a first end situated along the upper surfaces in a range from the zone of maximum curvature to the neck of the channel between this blade and the neighboring blade, characterized in that said slot is oriented along an isobaric line and has a length such that the second end is spaced from the upper surface a distance of between a quarter and a half of the width of the neck of the channel, said slot being connected to a point at lower pressure of the turbomachine.
  • the slot is connected by a channel to one of the sealing chambers situated in the downstream part of the lining of the movable grid of the following stage.
  • the floor of the grid of movable blades is provided with a suction slot in the vicinity of at least certain blades, said slot having a first end situated at the along the upper surface in a range from the zone of maximum curvature to the neck of the channel between this blade and the neighboring blade, said slot being oriented along an isobaric line and having a length such that the second end is spaced from the upper surfaces of a distance between a quarter and a half of the width of the neck of the channel, and in that said slot is connected by a conduit passing through the blade from bottom to top and opening downstream of the seal or in one of the last chambers of this trim.
  • the second end of the slot is spaced from the upper surface of the corresponding blade by a distance close to one third of the width of the neck of the corresponding channel.
  • 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 1 and the ceiling 2 are usually cylindrical surfaces or frustoconical.
  • the lower surface of dawn B, the upper surface of dawn A, the floor 1 and the ceiling 2 define a channel 3 with its neck 8 passing through the outlet edge of dawn B, said neck 8 corresponding to the minimum width of the channel.
  • Figure 2 shows a slot arrangement 4 according to Japanese patent 52-54807.
  • This slot 4 disposed in the floor and / or the ceiling is to aspirate part of the boundary layer.
  • Figure 3 shows measurements of local loss P along the distance (y) to floor 1 or ceiling 2 of the blade grid.
  • the curve in solid line (a) shows the evolution of the loss for a grid having no suction in the channel. Near the wall the loss is significant because of the boundary layer which forms on this wall. It decreases when one moves away from the wall and then starts to grow again: these are the losses dissipated in the passing vortex: then the loss decreases again when one moves further from the wall; far enough from the walls the loss is simply due to the boundary layers which develop on the blades.
  • Curves (b) and (c) represent these same changes in loss in the case of a grid of blades having a suction slot as shown in FIG. 2.
  • the loss (curve b) is very clearly increased.
  • the loss decreases (curve c) but for a percentage of suction flow of 3% of the main flow, which becomes very important, the overall loss is even greater than the loss in the grid of blades without suction .
  • the reason for this poor performance is to be found in the flow in the suction slot.
  • the pressure is not constant along the suction slot; also in certain places of the slit, where the pressure is the highest, the fluid will be effectively sucked up, but it can be reinjected into the vein at another place in the slit where the pressure is weakest; this reinjection is accompanied, of course, by significant losses.
  • Figure 4 shows two extreme positions of the slot according to the invention.
  • the isobaric lines 5 drawn from a calculation of the grid of two-dimensional blades have been drawn.
  • Such a calculation (accessible to all those skilled in the art who deal with turbomachines) makes it possible to know the characteristics of the flow sufficiently far from the walls. Near the walls the characteristics of the flow are very different, as regards the modulus and the direction of the velocities of the fluid, but we know that the static pressures are only very little modified compared to the static pressures in a section distant from the walls.
  • Figure 4 shows two extreme positions of the slot 4, 4 '.
  • the suction slot 4, 4 ′ is arranged in the vicinity of the blade A. Its first end 6 is located along the upper surface in a range from the zone of maximum curvature 7 to the neck 8 of channel 3.
  • the slot 4, 4 ′ is rectilinear and directed along an isobaric line. Its second end 9 is separated by a third of the minimum width of the channel 3 which corresponds to the width of the neck 8.
  • the slot is limited in length to its useful part near the upper surface to minimize the suction flow.
  • FIG. 5 shows (curve d) the losses measured P with an aspiration by a slot 4 according to the invention. There is a significant gain compared to the losses measured in the absence of any suction device (curve a).
  • FIG. 6 shows another case of application of the invention to a grid of movable blades where the isobaric lines have a shape quite different from that of FIG. 4.
  • FIG. 7 shows two stages 10 of the turbine, each consisting of a grid of fixed blades 11 and a grid of movable blades 12. This figure makes it possible to understand how the suction is carried out.
  • the suction slot 4 is connected by a channel 13 which opens out through an orifice 14 in a chamber of the seal 15 located at the top of the movable grid 12 of the next stage.
  • the significant expansion in the fixed grates allows to obtain the pressure difference necessary for suction.
  • a radial (or oblique) conduit 16 is drilled in the thickness of the blade which places the slot 4 in communication, formed in the base floor of the channel (radius R1) with the chamber 17 furthest downstream from the gasket. sealing located at the top (radius R2). The communication between the slot 4 and the radial duct 16 takes place via a link 18 (see FIG. 8).
  • the total flow that arrives in the lining through the orifice 14 or through the conduit 16 is less than or equal to the leakage flow which would normally pass through these linings in the absence of these aspirations: almost all of the gain due to the the improvement of secondary losses is thus saved.

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)
EP91115218A 1990-09-13 1991-09-09 Schaufelgitter für Turbomaschinen mit Saugschlitzen Expired - Lifetime EP0475329B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9011336A FR2666846B1 (fr) 1990-09-13 1990-09-13 Grille d'aubes pour turbomachine munie de fentes d'aspiration dans le plafond et/ou dans le plancher et turbomachine comportant ces grilles.
FR9011336 1990-09-13

Publications (3)

Publication Number Publication Date
EP0475329A2 true EP0475329A2 (de) 1992-03-18
EP0475329A3 EP0475329A3 (en) 1992-06-03
EP0475329B1 EP0475329B1 (de) 1994-11-30

Family

ID=9400301

Family Applications (1)

Application Number Title Priority Date Filing Date
EP91115218A Expired - Lifetime EP0475329B1 (de) 1990-09-13 1991-09-09 Schaufelgitter für Turbomaschinen mit Saugschlitzen

Country Status (10)

Country Link
US (1) US5232338A (de)
EP (1) EP0475329B1 (de)
JP (1) JPH04279701A (de)
CN (1) CN1060891A (de)
AT (1) ATE114780T1 (de)
CS (1) CS281991A3 (de)
DE (1) DE69105418T2 (de)
FR (1) FR2666846B1 (de)
MX (1) MX9101073A (de)
ZA (1) ZA917326B (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2003292A3 (de) * 2007-06-14 2012-04-04 Rolls-Royce Deutschland Ltd & Co KG Schaufeldeckband mit Überstand

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2675536B1 (fr) * 1991-04-19 1994-12-09 Alsthom Gec Turbine a action a rotor tambour et perfectionnement a ces turbines.
US5632598A (en) * 1995-01-17 1997-05-27 Dresser-Rand Shrouded axial flow turbo machine utilizing multiple labrinth seals
DE19620828C1 (de) * 1996-05-23 1997-09-04 Siemens Ag Turbinenwelle sowie Verfahren zur Kühlung einer Turbinenwelle
US6004095A (en) * 1996-06-10 1999-12-21 Massachusetts Institute Of Technology Reduction of turbomachinery noise
US5904470A (en) * 1997-01-13 1999-05-18 Massachusetts Institute Of Technology Counter-rotating compressors with control of boundary layers by fluid removal
EP0894944A1 (de) * 1997-07-29 1999-02-03 Siemens Aktiengesellschaft Turbinenbeschaufelung
EP1147291B1 (de) 1998-02-26 2007-08-22 Allison Advanced Development Company Zapfsystem für eine kompressorwand sowie betriebsverfahren
US6595743B1 (en) * 1999-07-26 2003-07-22 Impsa International Inc. Hydraulic seal for rotary pumps
US20040101410A1 (en) * 2001-10-02 2004-05-27 Oleg Naljotov Axial flow fluid machine
US6632069B1 (en) * 2001-10-02 2003-10-14 Oleg Naljotov Step of pressure of the steam and gas turbine with universal belt
US6682301B2 (en) * 2001-10-05 2004-01-27 General Electric Company Reduced shock transonic airfoil
GB0200992D0 (en) * 2002-01-17 2002-03-06 Rolls Royce Plc Gas turbine cooling system
UA81314C2 (en) * 2003-04-18 2007-12-25 Steam/gas turbine with shroud
US20070069477A1 (en) * 2003-06-20 2007-03-29 Elliott Company Stepped labyrinth damper seal
US20060267289A1 (en) * 2003-06-20 2006-11-30 Elliott Company Hybrid abradable labyrinth damper seal
JP4346412B2 (ja) 2003-10-31 2009-10-21 株式会社東芝 タービン翼列装置
DE10355241A1 (de) * 2003-11-26 2005-06-30 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Fluidzufuhr
DE10355240A1 (de) * 2003-11-26 2005-07-07 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Fluidentnahme
RU2279551C1 (ru) * 2005-01-11 2006-07-10 Открытое акционерное общество "Научно-производственное объединение по исследованию и проектированию энергетического оборудования им. И.И. Ползунова" (ОАО "НПО ЦКТИ") Высокотемпературная многоступенчатая паровая турбина
DE102008029605A1 (de) * 2008-06-23 2009-12-24 Rolls-Royce Deutschland Ltd & Co Kg Schaufeldeckband mit Durchlass
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
CN102364098A (zh) * 2011-11-18 2012-02-29 三一电气有限责任公司 一种风力发电机组及其叶片
EP2713009B1 (de) * 2012-09-26 2015-03-11 Alstom Technology Ltd Kühlverfahren und -system zur Kühlung von Schaufeln mindestens einer Schaufelreihe in einer drehenden Strömungsmaschine
CN109413711B (zh) * 2018-10-17 2021-02-05 中国运载火箭技术研究院 一种飞行器协同信息网络协议栈
US11674406B2 (en) * 2021-08-06 2023-06-13 Pratt & Whitney Canada Corp. Variable gap between impeller rotor and static structure

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JPS501646B1 (de) * 1970-07-11 1975-01-20
DE2135286A1 (de) * 1971-07-15 1973-01-25 Wilhelm Prof Dr Ing Dettmering Lauf- und leitradgitter fuer turbomaschinen
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JPS5254809A (en) * 1975-10-31 1977-05-04 Hitachi Ltd Axial-flow fluid machine construction
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FR2438157A1 (fr) * 1978-10-05 1980-04-30 Alsthom Atlantique Grille d'aubes pour turbine ou compresseur
FR2438155A1 (fr) * 1978-10-05 1980-04-30 Alsthom Atlantique Grille d'aubes pour turbine ou compresseur et turbine ou compresseur comportant une telle grille d'aubes
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2003292A3 (de) * 2007-06-14 2012-04-04 Rolls-Royce Deutschland Ltd & Co KG Schaufeldeckband mit Überstand

Also Published As

Publication number Publication date
MX9101073A (es) 1994-06-30
DE69105418D1 (de) 1995-01-12
US5232338A (en) 1993-08-03
ATE114780T1 (de) 1994-12-15
FR2666846A1 (fr) 1992-03-20
EP0475329B1 (de) 1994-11-30
DE69105418T2 (de) 1995-04-20
ZA917326B (en) 1992-05-27
JPH04279701A (ja) 1992-10-05
EP0475329A3 (en) 1992-06-03
CS281991A3 (en) 1992-03-18
FR2666846B1 (fr) 1992-10-16
CN1060891A (zh) 1992-05-06

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