EP0953729B1 - Leitbeschaufelung für eine Turbomaschine - Google Patents

Leitbeschaufelung für eine Turbomaschine Download PDF

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Publication number
EP0953729B1
EP0953729B1 EP98201416A EP98201416A EP0953729B1 EP 0953729 B1 EP0953729 B1 EP 0953729B1 EP 98201416 A EP98201416 A EP 98201416A EP 98201416 A EP98201416 A EP 98201416A EP 0953729 B1 EP0953729 B1 EP 0953729B1
Authority
EP
European Patent Office
Prior art keywords
platforms
platform
vane
outer shell
shell
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
EP98201416A
Other languages
English (en)
French (fr)
Other versions
EP0953729A1 (de
Inventor
Hung Quac Tran
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.)
Safran Aero Boosters SA
Original Assignee
Techspace Aero 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 Techspace Aero SA filed Critical Techspace Aero SA
Priority to DE69815815T priority Critical patent/DE69815815T2/de
Priority to EP98201416A priority patent/EP0953729B1/de
Priority to PCT/EP1999/003390 priority patent/WO2004074639A1/fr
Priority to US09/446,131 priority patent/US6296442B1/en
Publication of EP0953729A1 publication Critical patent/EP0953729A1/de
Application granted granted Critical
Publication of EP0953729B1 publication Critical patent/EP0953729B1/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
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Definitions

  • the present invention relates to a turbomachine stator vane comprising arrangements for fixing the stationary vanes which constitute it.
  • the invention is particularly applicable to a rectifier vane of a multi-flow turbojet engine.
  • FR-A-2 321 616 thus shows a fixing of the end platforms of the blades by bolting on the outer shroud.
  • FR-A-2 671 133 a straightening vane in which the blades are fixed by means of a socket placed in abutment on the external surface of the outer shell and crimped on a rod carried by the end of the 'dawn.
  • the object of the invention is to provide an alternative solution facilitating the attachment of the blades of a straightening vane.
  • One of the aims of the invention is also to ensure an anti-rotation blocking of the vanes of the stator vane during assembly and in operation.
  • the object is achieved according to the invention by the fact that the outer shell has a housing whose bottom has a non-planar, spherical or cylindrical surface with radius of curvature R, into which the platforms of the blades are introduced, the cooperating surface of which has a corresponding non-planar, spherical or cylindrical shape, with a greater radius of curvature R + delta R before installation and which is reduced to the radius R under stress, by the action of fixing rivets, assembling the platforms of blades and the outer shell.
  • FIGS. 1 to 7 show an embodiment of a rectifier vane 1 according to the invention and constituting a fixed stage of a multiflow turbojet engine.
  • the stator vane 1 is constituted by a crown of stationary vanes 2 arranged between a radially outer stator ferrule 3 and a radially inner stator ferrule 4.
  • the radially inner end 5 of each vane 2 is introduced into a slot 6 of complementary shape formed in said inner ferrule 4.
  • the blade of the blade 2 carries at its radially outer end a platform 7 which is placed in a housing 8 formed between two shoulders 9 on the inner face of the outer ferrule 3
  • Each platform 7 has holes 10, two in number per platform according to the preferred embodiment shown in the drawings and arranged one on each side of the blade of the blade, in an opposite position along a diagonal of the platform 7.
  • the outer shell 3 has corresponding holes 11.
  • the upper face 12 of the platform 7 has a non-planar shape whose radius of curvature before mounting the blade is R + delta R, as shown diagrammatically in FIG. 2.
  • the realized shape can be spherical or cylindrical.
  • the corresponding bottom 13 of the housing 8 of the outer shell 3 also has a non-planar surface whose radius of curvature R is less than the radius of curvature of the platform before mounting.
  • the shape produced by machining is spherical or cylindrical corresponding to that of the platform.
  • washers 19 can be placed under the rivet heads 14 to avoid a matting effect on the outer shell 3, depending on the materials used.
  • the shoulders 9 formed on each side of the housing 8 on the outer shell 3 guide the mounting of the platforms 7 in the housing 8 and also ensure the anti-rotation blocking of the blades during assembly and in operation.
  • additional arrangements can be made to the stator vane 1 according to the invention.
  • the adjacent edges 15 of the platforms 7 have a chamfer in one direction over half a length and in the other direction over the other half length, as shown in FIG. 8. As a variant, as shown in FIG.
  • a hollow triangular notch 16 can be formed on an edge 15 of the platform while the adjacent edge of the adjacent platform carries the corresponding prominent element 17.
  • an additional rivet can also be added, placed astride the two adjacent edges of neighboring platforms 7, as shown at 18 in FIG. 10.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (5)

  1. Leitbeschaufelung für eine Turbomaschine, bestehend aus einem Leitschaufelkranz (2), dessen Schaufeln zwischen einem in radialer Richtung äußeren Statorring (3) und einem in radialer Richtung inneren Statorring (4) angeordnet sind, wobei das innere Ende (5) jeder Schaufel (2) in einem Spalt (6) mit komplementärer Form placiert ist, der in diesem inneren Statorring (4) ausgeführt ist, und das äußere Ende jeder Schaufel (2) eine Plattform (7) trägt, die an der Innenseite des äußeren Statorrings (3) befestigt ist,
       dadurch gekennzeichnet,    dass der äußere Ring (3) eine Aufnahme (8) enthält, deren Boden (13) eine nicht ebene, kugelförmige oder zylindrische Oberfläche mit dem Krümmungsradius R aufweist, in die die Plattformen (7) der Schaufeln (2) eingesetzt sind, deren zusammenwirkende Oberfläche (12) eine entsprechende nicht ebene, kugelförmige oder zylindrische Oberfläche mit einem vor der Anbringung größeren Krümmungsradius R + delta R aufweist, der dann unter Belastung auf den Radius R reduziert wird, und zwar durch Einwirkung von Befestigungsnieten (14), die die Plattformen (7) der Schaufeln und den äußeren Ring (3) verbinden.
  2. Leitbeschaufelung für eine Turbomaschine nach Anspruch 1,
       dadurch gekennzeichnet,    dass die Aufnahme (8) auf der Innenseite des äußeren Rings (3) durch zwei Absätze (9) begrenzt wird, die die Einbauführung der Plattformen (7) und das Blockieren der Schaufeln (2) gegen Drehen während des Einbaus und in Betrieb gewährleisten, und die Befestigungsnieten (14) sind pro Plattform (7) zwei an der Zahl, wobei sie jeweils auf jeder Seite der Schaufel (2) entsprechend einer Diagonalen der Plattform (7) in der entgegngesetzten Position angeordnet sind.
  3. Leitbeschaufelung für eine Turbomaschine nach einem der Ansprüche 1 oder 2,
       dadurch gekennzeichnet,    dass die Ränder (15) der Plattformen (7) eine Abschrägung in einer Richtung über eine halbe Länge und in der anderen Richtung über die andere halbe Länge aufweisen, die eine komplementäre Form zu den angrenzenden Rändern (15) von zwei benachbarten Plattformen (7) haben.
  4. Leitbeschaufelung für eine Turbomaschine nach einem der Ansprüche 1 oder 2,
       dadurch gekennzeichnet,    dass an einem Rand (15) jeder Plattformen (7) eine dreieckige, hohle Einkerbung (16) ausgeführt ist, und dass der angrenzende Rand (15) der benachbarten Plattform (7) ein entsprechendes vorstehendes Element (17) trägt.
  5. Leitbeschaufelung für eine Turbomaschine nach einem der Ansprüche 1 oder 2,
       dadurch gekennzeichnet,    dass eine zusätzliche Niet überlappend auf den beiden angrenzenden Rändern (15) von zwei benachbarten Plattformen (7) angeordnet ist.
EP98201416A 1998-05-01 1998-05-01 Leitbeschaufelung für eine Turbomaschine Expired - Lifetime EP0953729B1 (de)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE69815815T DE69815815T2 (de) 1998-05-01 1998-05-01 Leitbeschaufelung für eine Turbomaschine
EP98201416A EP0953729B1 (de) 1998-05-01 1998-05-01 Leitbeschaufelung für eine Turbomaschine
PCT/EP1999/003390 WO2004074639A1 (fr) 1998-05-01 1999-04-27 Aubage redresseur de turbomachine
US09/446,131 US6296442B1 (en) 1998-05-01 1999-04-27 Turbomachine stator vane set

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98201416A EP0953729B1 (de) 1998-05-01 1998-05-01 Leitbeschaufelung für eine Turbomaschine

Publications (2)

Publication Number Publication Date
EP0953729A1 EP0953729A1 (de) 1999-11-03
EP0953729B1 true EP0953729B1 (de) 2003-06-25

Family

ID=8233667

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98201416A Expired - Lifetime EP0953729B1 (de) 1998-05-01 1998-05-01 Leitbeschaufelung für eine Turbomaschine

Country Status (4)

Country Link
US (1) US6296442B1 (de)
EP (1) EP0953729B1 (de)
DE (1) DE69815815T2 (de)
WO (1) WO2004074639A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2199544A1 (de) 2008-12-22 2010-06-23 Techspace Aero S.A. Aufbau eines Leitschaufelgitters

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7195453B2 (en) * 2004-08-30 2007-03-27 General Electric Company Compressor stator floating tip shroud and related method
ATE486195T1 (de) 2005-12-22 2010-11-15 Techspace Aero Schaufelleitring einer strömungsmaschine, strömungsmaschine mit einem solchen leitring und leitschaufel
FR2906296A1 (fr) * 2006-09-26 2008-03-28 Snecma Sa Dispositif de fixation d'une aube fixe dans un carter annulaire de turbomachine, turboreacteur incorporant le dispositif et procede de montage de l'aube.
EP1936121B1 (de) * 2006-12-22 2012-05-02 Techspace Aero Winkelfixierung für Leitschaufeln von Turbomachinen
EP2075412B1 (de) * 2007-12-26 2012-02-29 Techspace Aero Vorrichtung zur Befestigung durch Verschraubung von Leitschaufeln an den Mantelring einer Statorstufe einer Strömungsmaschine und entsprechendes Befestigungsverfahren durch Verschraubung
US8092165B2 (en) * 2008-01-21 2012-01-10 Pratt & Whitney Canada Corp. HP segment vanes
US8157507B1 (en) * 2010-01-19 2012-04-17 Florida Turbine Technologies, Inc. Damped stator assembly
US20130052004A1 (en) † 2011-08-25 2013-02-28 Nicholas D. Stilin Structural composite fan exit guide vane for a turbomachine
US10309235B2 (en) 2012-08-27 2019-06-04 United Technologies Corporation Shiplap cantilevered stator
EP2738356B1 (de) * 2012-11-29 2019-05-01 Safran Aero Boosters SA Statorschaufel einer Strömungsmaschine, Statorschaufelkranz einer Strömungsmaschine und zugehöriges Montageverfahren
CN106050322A (zh) * 2016-08-08 2016-10-26 中国船舶重工集团公司第七�三研究所 一种倾斜轴式变几何动力涡轮导叶
US10900364B2 (en) * 2017-07-12 2021-01-26 Raytheon Technologies Corporation Gas turbine engine stator vane support
US11286797B2 (en) 2018-06-06 2022-03-29 Raytheon Technologies Corporation Gas turbine engine stator vane base shape
CN109986489B (zh) * 2019-03-12 2021-03-02 上海应达风机股份有限公司 一种风机叶轮自动装配设备及风机叶轮装配工艺

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DE967089C (de) * 1940-12-21 1957-10-03 Kuehnle Kopp Kausch Ag Auswechselbare Axialleitapparat-Beschaufelung von Geblaesen, Pumpen u. dgl.
US2661147A (en) * 1949-01-19 1953-12-01 Ingersoll Rand Co Blower blade fastening device
DE1476928A1 (de) * 1965-05-29 1969-07-31 Bergmann Borsig Veb Leitschaufelfuss fuer Turbinen mit hoher Eintrittstemperatur
GB1366075A (en) * 1970-09-16 1974-09-11 Secr Defence Bladed fluid flow machines
FR2321616A1 (fr) * 1975-08-21 1977-03-18 Snecma Perfectionnements a la fixation des aubes statoriques d'une soufflante ou d'un compresseur a flux axial
GB2110768A (en) * 1981-12-01 1983-06-22 Rolls Royce Fixings for stator vanes
US4832568A (en) * 1982-02-26 1989-05-23 General Electric Company Turbomachine airfoil mounting assembly
US4722184A (en) * 1985-10-03 1988-02-02 United Technologies Corporation Annular stator structure for a rotary machine
FR2597921A1 (fr) * 1986-04-24 1987-10-30 Snecma Anneau de turbine sectorise
US4710097A (en) * 1986-05-27 1987-12-01 Avco Corporation Stator assembly for gas turbine engine
FR2671133B1 (fr) 1990-12-27 1994-10-21 Snecma Aube a pivot a fixation rapide pour aubage redresseur de turbomachine et procede de fixation de ladite aube.
FR2702242B1 (fr) * 1993-03-03 1995-04-07 Snecma Etage d'aubes libres à une extrémité.
US5622475A (en) * 1994-08-30 1997-04-22 General Electric Company Double rabbet rotor blade retention assembly

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2199544A1 (de) 2008-12-22 2010-06-23 Techspace Aero S.A. Aufbau eines Leitschaufelgitters

Also Published As

Publication number Publication date
DE69815815D1 (de) 2003-07-31
EP0953729A1 (de) 1999-11-03
US6296442B1 (en) 2001-10-02
WO2004074639A1 (fr) 2004-09-02
DE69815815T2 (de) 2004-05-13

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