EP0916812B1 - Etage final pour turbine axial - Google Patents

Etage final pour turbine axial Download PDF

Info

Publication number
EP0916812B1
EP0916812B1 EP97810873A EP97810873A EP0916812B1 EP 0916812 B1 EP0916812 B1 EP 0916812B1 EP 97810873 A EP97810873 A EP 97810873A EP 97810873 A EP97810873 A EP 97810873A EP 0916812 B1 EP0916812 B1 EP 0916812B1
Authority
EP
European Patent Office
Prior art keywords
vane
blade
rotor
sweep
side end
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 - Lifetime
Application number
EP97810873A
Other languages
German (de)
English (en)
Other versions
EP0916812A1 (fr
Inventor
Carsten Mumm
Andreas Dr. Weiss
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.)
General Electric Switzerland GmbH
Original Assignee
Alstom Schweiz AG
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 Alstom Schweiz AG filed Critical Alstom Schweiz AG
Priority to EP97810873A priority Critical patent/EP0916812B1/fr
Priority to DE59709447T priority patent/DE59709447D1/de
Priority to US09/190,366 priority patent/US6099248A/en
Priority to KR1019980049088A priority patent/KR19990045318A/ko
Priority to CN98123390.2A priority patent/CN1250863C/zh
Publication of EP0916812A1 publication Critical patent/EP0916812A1/fr
Application granted granted Critical
Publication of EP0916812B1 publication Critical patent/EP0916812B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades

Definitions

  • the invention relates to the final stage of a turbine with a large axial flow Channel divergence with a series of curved guide vanes and a series of tapered, twisted blades.
  • Curved guide vanes are used in particular to reduce secondary losses reduce by redirecting the boundary layers in the Guide vanes are created.
  • Turbines with guide blades curved in the axial direction and in the circumferential direction are known, for example, from DE-A-42 28 879.
  • a fixed guide grid is arranged upstream of the playpen. Its blades are fluidically optimized for full load with regard to the number and their ratio of chord to pitch. They give the flow the swirl required to enter the playpen.
  • the curvature of the blades is perpendicular to the chord, which is achieved by moving the profile cuts both in the circumferential direction and in the axial direction.
  • the curvature of the guide vanes is directed against the pressure side of the guide vane which is adjacent in the circumferential direction. This curvature is formed by a continuous arc, which forms an acute angle with the blade carrier and with the hub.
  • the blade area projected in the radial direction is larger than in the known curvature in the circumferential direction. This increases the radial force on the flow medium; this is pressed against the channel walls, whereby the boundary layer thickness is reduced there.
  • a blade grille for an axially flow-through turbomachine the blade leading edges of which are swept in the area of the blade root and in the area of the blade tip with respect to the direction of flow, is shown in more detail in EP-A-0661413.
  • the airfoil essentially consists of a radially oriented middle part of the blade , which takes up about 50% of the blade height and the two swept end sections, which can take up to 10% of the blade height. These rectilinear sections are connected via curved transition regions.
  • the trailing edge of the blade follows a course analogous to the leading edge in accordance with the tapering depth of the blade.
  • the present invention has for its object in an axially flow Turbine of the type mentioned, especially one with small hub ratio to create a measure by which the detachment the flow from the hub can be avoided and with the more even Pressure distribution over the blading height can be achieved.
  • FIG. 1 In the steam turbine shown schematically in FIG. 1, these are the flow through Wall 1 delimiting walls on the one hand the channel limitation on the rotor side 3 and on the other hand the stator-side channel limitation 5.
  • the output stage exists from a row of guide vanes 10 and a row of moving blades 20.
  • the guide vanes 10 are fixed in a manner not shown in the stator 4, the Blade carrier itself is suspended in a suitable manner in an outer housing.
  • the blades 20 are fastened in the rotor 2 in a manner not shown.
  • the The blade airfoil is tapered in its longitudinal extension and strongly twisted (Twisted). The airfoil seals against the stator-side channel boundary 5 with its top.
  • the channel boundary 3 on the rotor side runs in the entire blading area cylindrical while due to the volume increase of the expanding working medium the stator-side channel boundary 5 is conical and at highly loaded machines can have an opening angle of up to 60 °. It goes without saying that the inner channel contour 3 is also conical can.
  • the guide vanes 10 are on their in the axial direction rotor on the rotor end positive and negative arrow on its stator end.
  • the Arrow which both the leading edge 11 and the The guide vane trailing edge 12 relates here to the cylindrical Course of the rotor-side channel boundary 3.
  • the arrow angle A is selected so that the guide vane trailing edge 12 is at least approximately parallel to the leading edge 21 of the blade 20 runs. This positive sweep extends to approx. 2/3 of the bucket height. It causes a channel limitation radially to the rotor side 3 acting force on the flow, as evidenced by the course of the Meridian streamlines 6 can be seen.
  • the selected contour which is adapted to the shape of the blade leading edge 21 the guide vane trailing edge 12 also allows in the lower 2/3 of the flowed channel the setting of the radially variable optimal length of the blade-free axial diffuser between the guide and barrel rows.
  • This axial diffuser that occurs in the blade-free space due to the strong channel divergence, has a width C in the example. The narrower this axial diffuser is is, the cheaper this affects the design of the following Blade from. The less the fluid in this area in his Axial component is delayed, the greater the stagger angle of the subsequent blade profile can be selected. About the considered bucket height has the consequence that the airfoil is less twisted overall (twisted) must be.
  • FIG. 2 A further measure is shown in FIG. 2, which advantageously affects the displacement the flow affects the rotor-side channel boundary.
  • the guide vanes 10 over a large part of their radial extent in the circumferential direction inclined in such a way that the inclination towards the suction side 13 which is directed in the circumferential direction adjacent vane 10 '.
  • On the end of the rotor is directed radially. From about 15% of the radial extension it inclines in the circumferential direction and returns on its stator side End back in the radial R. It has been shown that a Tilt angle B to the radial R in the range of 10-17 °, preferably 12-15 ° a sufficiently large force acting radially towards the rotor on the flow generated and pushes them against the rotor.

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)

Claims (4)

  1. Etage final pour une turbine axiale avec une grande divergence de canal pouvant atteindre 60° avec une rangée d'aubes directrices courbes (10) et une rangée d'aubes mobiles amincies tordues (20), dans lequel les aubes directrices (10) sont, en direction axiale, inclinées positivement à leur extrémité du côté du rotor et négativement à leur extrémité du côté du stator, par rapport au tracé de la paroi du canal (3) du côté du rotor, caractérisé en ce que l'inclinaison positive des aubes directrices (10) s'étend sur les 2/3 de la hauteur des aubes et devient ensuite une inclinaison négative, dans lequel l'arête de fuite (12) des aubes directrices est parallèle à l'arête d'attaque (21) des aubes mobiles dans la région de l'inclinaison positive et un diffuseur axial s'évasant en continu vers la paroi (5) se forme, dans la région de l'inclinaison négative, entre des aubes directrices (10) et mobiles (20) avec un ralentissement croissant de la composante axiale du fluide en écoulement.
  2. Etage final suivant la revendication 1, caractérisé en ce que l'inclinaison négative à l'extrémité du côté du stator est choisie de telle manière que l'arête de fuite (12) des aubes directrices et/ou l'arête d'attaque (11) des aubes directrices soit orientée au moins approximativement perpendiculairement à la paroi (5) de limitation de l'écoulement.
  3. Etage final suivant la revendication 1, caractérisé en ce que l'aube directrice (10) est orientée radialement à son extrémité du côté du rotor, s'incline vers le côté d'aspiration (13) de l'aube directrice voisine (10') dans le sens périphérique à partir d'environ 15 % de sa dimension radiale et s'incline à nouveau en sens inverse au moins approximativement en direction radiale (R) à son extrémité du côté du stator.
  4. Etage final suivant la revendication 3, caractérisé en ce que l'angle d'inclinaison (B) par rapport à la direction radiale (R) vaut environ 12°-15°.
EP97810873A 1997-11-17 1997-11-17 Etage final pour turbine axial Expired - Lifetime EP0916812B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP97810873A EP0916812B1 (fr) 1997-11-17 1997-11-17 Etage final pour turbine axial
DE59709447T DE59709447D1 (de) 1997-11-17 1997-11-17 Endstufe für axialdurchströmte Turbine
US09/190,366 US6099248A (en) 1997-11-17 1998-11-12 Output stage for an axial-flow turbine
KR1019980049088A KR19990045318A (ko) 1997-11-17 1998-11-16 축류터빈의 출력단
CN98123390.2A CN1250863C (zh) 1997-11-17 1998-11-17 轴流式透平的输出级

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP97810873A EP0916812B1 (fr) 1997-11-17 1997-11-17 Etage final pour turbine axial

Publications (2)

Publication Number Publication Date
EP0916812A1 EP0916812A1 (fr) 1999-05-19
EP0916812B1 true EP0916812B1 (fr) 2003-03-05

Family

ID=8230472

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97810873A Expired - Lifetime EP0916812B1 (fr) 1997-11-17 1997-11-17 Etage final pour turbine axial

Country Status (5)

Country Link
US (1) US6099248A (fr)
EP (1) EP0916812B1 (fr)
KR (1) KR19990045318A (fr)
CN (1) CN1250863C (fr)
DE (1) DE59709447D1 (fr)

Families Citing this family (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7025576B2 (en) 2001-03-30 2006-04-11 Chaffee Robert B Pump with axial conduit
CA2408536C (fr) * 2000-05-17 2008-09-30 Robert B. Chaffee Dispositif gonflable a regulateur de fluide en retrait et systeme de reglage modifie
US7644724B2 (en) 2000-05-17 2010-01-12 Robert Chaffee Valve with electromechanical device for actuating the valve
DE10051223A1 (de) 2000-10-16 2002-04-25 Alstom Switzerland Ltd Verbindbare Statorelemente
EP1688067B1 (fr) 2001-07-10 2008-11-05 CHAFFEE, Robert B. Dispositif de soutien pneumatique et configurable
JP2006506212A (ja) 2002-11-18 2006-02-23 チャフィー，ロバート，ビー． 膨張式デバイス
CA2528332A1 (fr) * 2003-06-09 2005-01-06 Aero International Products, Inc. Systeme de gonflage reversible
EP1642005B1 (fr) * 2003-07-09 2009-10-14 Siemens Aktiengesellschaft Aube de turbine
US7547187B2 (en) * 2005-03-31 2009-06-16 Hitachi, Ltd. Axial turbine
US7588425B2 (en) * 2005-03-18 2009-09-15 Aero Products International, Inc. Reversible inflation system
US7510371B2 (en) * 2005-06-06 2009-03-31 General Electric Company Forward tilted turbine nozzle
WO2007113149A1 (fr) * 2006-03-31 2007-10-11 Alstom Technology Ltd Aube directrice de turbomachine, notamment de turbine à vapeur
US7806653B2 (en) * 2006-12-22 2010-10-05 General Electric Company Gas turbine engines including multi-curve stator vanes and methods of assembling the same
WO2008128877A1 (fr) 2007-04-24 2008-10-30 Alstom Technology Ltd Turbomachine
DE102008055824B4 (de) 2007-11-09 2016-08-11 Alstom Technology Ltd. Dampfturbine
ITMI20072441A1 (it) * 2007-12-28 2009-06-29 Ansaldo Energia Spa Pala statorica di ultimo stadio di sezione di bassa pressione di una turbina a vapore
DE102008004014A1 (de) * 2008-01-11 2009-07-23 Continental Automotive Gmbh Leitschaufel für eine variable Turbinengeometrie
WO2009118234A1 (fr) * 2008-03-28 2009-10-01 Alstom Technology Ltd Aube pour moteur thermique rotatif
US20100303604A1 (en) * 2009-05-27 2010-12-02 Dresser-Rand Company System and method to reduce acoustic signature using profiled stage design
EP2434094A3 (fr) 2010-09-28 2018-02-21 Mitsubishi Hitachi Power Systems, Ltd. Aube statorique de turbine à vapeur et turbine à vapeur
CN102235241A (zh) * 2011-06-28 2011-11-09 北京动力机械研究所 入口带大扩张通道的低压涡轮结构
GB201115581D0 (en) * 2011-09-09 2011-10-26 Rolls Royce Plc A turbine engine stator and method of assembly of the same
US9488055B2 (en) 2012-06-08 2016-11-08 General Electric Company Turbine engine and aerodynamic element of turbine engine
US20160201468A1 (en) * 2015-01-13 2016-07-14 General Electric Company Turbine airfoil
DE102018202888A1 (de) * 2018-02-26 2019-08-29 MTU Aero Engines AG Leitschaufelblatt für den Heissgaskanal einer Strömungsmaschine
JP7061497B2 (ja) * 2018-03-30 2022-04-28 三菱重工航空エンジン株式会社 航空機用ガスタービン
US11566530B2 (en) 2019-11-26 2023-01-31 General Electric Company Turbomachine nozzle with an airfoil having a circular trailing edge
US11629599B2 (en) 2019-11-26 2023-04-18 General Electric Company Turbomachine nozzle with an airfoil having a curvilinear trailing edge

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2663493A (en) * 1949-04-26 1953-12-22 A V Roe Canada Ltd Blading for compressors, turbines, and the like
GB1080015A (en) * 1963-11-13 1967-08-23 English Electric Co Ltd Steam turbines
GB1116580A (en) * 1965-11-17 1968-06-06 Bristol Siddeley Engines Ltd Stator blade assemblies for axial-flow turbine engines
US4433955A (en) * 1981-03-26 1984-02-28 General Electric Company Turbine arrangement
FR2505399A1 (fr) * 1981-05-05 1982-11-12 Alsthom Atlantique Aubage directeur pour veines divergentes de turbine a vapeur
FR2523642A1 (fr) * 1982-03-19 1983-09-23 Alsthom Atlantique Aubage directeur pour veines divergentes de turbine a vapeur
GB2164098B (en) * 1984-09-07 1988-12-07 Rolls Royce Improvements in or relating to aerofoil section members for turbine engines
FR2603953B1 (fr) * 1986-09-12 1991-02-22 Peugeot Aciers Et Outillage Pale profilee d'helice et son application aux motoventilateurs
US4826400A (en) * 1986-12-29 1989-05-02 General Electric Company Curvilinear turbine airfoil
JP2753382B2 (ja) * 1990-09-17 1998-05-20 株式会社日立製作所 軸流タービン静翼装置及び軸流タービン
DE4228879A1 (de) * 1992-08-29 1994-03-03 Asea Brown Boveri Axialdurchströmte Turbine
DE4344189C1 (de) * 1993-12-23 1995-08-03 Mtu Muenchen Gmbh Axial-Schaufelgitter mit gepfeilten Schaufelvorderkanten

Also Published As

Publication number Publication date
CN1217419A (zh) 1999-05-26
KR19990045318A (ko) 1999-06-25
DE59709447D1 (de) 2003-04-10
CN1250863C (zh) 2006-04-12
US6099248A (en) 2000-08-08
EP0916812A1 (fr) 1999-05-19

Similar Documents

Publication Publication Date Title
EP0916812B1 (fr) Etage final pour turbine axial
EP2025945B1 (fr) Machine de traitement des écoulements dotée d'un creux de paroi de canal de ceinture
EP0799973B1 (fr) Contour de paroi pour une turbomachine axiale
DE112006001614B4 (de) Turbomaschinenschaufel
DE60112551T2 (de) Schaufel für eine axial durchströmte turbomaschine
DE112006002658B4 (de) Turbomaschinenschaufel
DE3530769C2 (de) Schaufel für ein Gasturbinentriebwerk
DE69520061T2 (de) Turbinenschaufel
DE69423789T2 (de) Stroemungsleiteinrichtung fuer den kompressorteil einer stroemungsmaschine
DE60017541T2 (de) Schaufelblatt für eine axiale Turbomaschine
EP1632662B1 (fr) Turbomachine avec soutirage
WO2007113149A1 (fr) Aube directrice de turbomachine, notamment de turbine à vapeur
DE69721114T3 (de) Gekrümmte Gebläseschaufel
EP2473743B1 (fr) Aube mobile de compresseur pour un compresseur axial
DE60314024T2 (de) Anordnung von Leit- und Rotorschaufeln im Abgasbereich einer Turbine
EP2194232B1 (fr) Turbomachine dotée d'une barrière à couche frontière sur la paroi latérale
EP0528138B1 (fr) Anneau d'aube de turbine axiale
EP2003292B1 (fr) Machine de travail fluidique avec virole d'aube dotée d'un rebord
EP2320030B1 (fr) Rotor et aube de rotor pour une turbomachine axiale
EP1766192B1 (fr) Roue a aubes d'une turbine presentant une aube et au moins un canal refrigerant
EP2455585B1 (fr) Agencement pour une turbomachine axiale et turbomachine axiale
DE4228879A1 (de) Axialdurchströmte Turbine
WO2005116404A1 (fr) Aube comportant une zone de transition
WO2008122507A1 (fr) Agencement en feuillure
EP2538024A1 (fr) Aube dans une turbomachine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

17P Request for examination filed

Effective date: 19990923

AKX Designation fees paid

Free format text: DE GB IT

RBV Designated contracting states (corrected)

Designated state(s): DE FR GB

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ALSTOM

17Q First examination report despatched

Effective date: 20011207

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ALSTOM (SWITZERLAND) LTD

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Designated state(s): DE FR GB

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20030305

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20030305

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 59709447

Country of ref document: DE

Date of ref document: 20030410

Kind code of ref document: P

GBV Gb: ep patent (uk) treated as always having been void in accordance with gb section 77(7)/1977 [no translation filed]

Effective date: 20030305

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

EN Fr: translation not filed
26N No opposition filed

Effective date: 20031208

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 59709447

Country of ref document: DE

Representative=s name: UWE ROESLER, DE

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 59709447

Country of ref document: DE

Representative=s name: RUEGER, BARTHELT & ABEL, DE

Effective date: 20120713

Ref country code: DE

Ref legal event code: R082

Ref document number: 59709447

Country of ref document: DE

Representative=s name: ROESLER, UWE, DIPL.-PHYS.UNIV., DE

Effective date: 20120713

Ref country code: DE

Ref legal event code: R081

Ref document number: 59709447

Country of ref document: DE

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER: ALSTOM (SWITZERLAND) LTD., BADEN, CH

Effective date: 20120713

Ref country code: DE

Ref legal event code: R081

Ref document number: 59709447

Country of ref document: DE

Owner name: ALSTOM TECHNOLOGY LTD., CH

Free format text: FORMER OWNER: ALSTOM (SWITZERLAND) LTD., BADEN, CH

Effective date: 20120713

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 59709447

Country of ref document: DE

Representative=s name: RUEGER, BARTHELT & ABEL, DE

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 59709447

Country of ref document: DE

Representative=s name: RUEGER, BARTHELT & ABEL, DE

Ref country code: DE

Ref legal event code: R081

Ref document number: 59709447

Country of ref document: DE

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20161123

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R071

Ref document number: 59709447

Country of ref document: DE