EP0953729A1 - Leitbeschaufelung für eine Turbomaschine - Google Patents

Leitbeschaufelung für eine Turbomaschine Download PDF

Info

Publication number: EP0953729A1
Authority: EP; European Patent Office
Prior art keywords: platforms; platform; blades; blade; shell
Prior art date: 1998-05-01
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

EP98201416A

Other languages

English (en)

French (fr)

Other versions

EP0953729B1 (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.)

1998-05-01

Filing date

1998-05-01

Publication date

1999-11-03

1998-05-01 Application filed by Techspace Aero SA filed Critical Techspace Aero SA

1998-05-01 Priority to EP98201416A priority Critical patent/EP0953729B1/de

1998-05-01 Priority to DE69815815T priority patent/DE69815815T2/de

1999-04-27 Priority to PCT/EP1999/003390 priority patent/WO2004074639A1/fr

1999-04-27 Priority to US09/446,131 priority patent/US6296442B1/en

1999-11-03 Publication of EP0953729A1 publication Critical patent/EP0953729A1/de

2003-06-25 Application granted granted Critical

2003-06-25 Publication of EP0953729B1 publication Critical patent/EP0953729B1/de

2018-05-01 Anticipated expiration legal-status Critical

Status Expired - Lifetime legal-status Critical Current

Links

230000000903 blocking effect Effects 0.000 claims description 5
230000000295 complement effect Effects 0.000 claims description 3
238000005422 blasting Methods 0.000 claims 3
230000000694 effects Effects 0.000 description 1
238000009434 installation Methods 0.000 description 1
238000003754 machining Methods 0.000 description 1
210000003462 vein Anatomy 0.000 description 1

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
- 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 straightening vane of turbomachine comprising arrangements for fixing the fixed vanes which constitute it.
the invention is particularly applicable to a blading multi-flow turbojet rectifier.
the blades are arranged between a ferrule radially outer stator and a stator shell radially inner which delimit the profile of the vein of the flow flowing in the channel.
FR-A-2 321 616 thus shows a fixing of the platforms blade tip by bolting on the ferrule outside.
the object of the invention is to provide an alternative solution facilitating the attachment of the blades of a straightening vane.
a aims of the invention is also to ensure a blocking anti-rotation of the blades of the stator vane during assembly and operation.
the outer shell has a housing whose bottom has a non-planar, spherical or cylindrical surface with a radius of curvature R, where the platforms of the blades are introduced whose cooperating surface has a corresponding shape not planar, spherical or cylindrical, with radius of curvature upper R + delta R before positioning and which is brought back at radius R under stress, by the action of rivets of fixing, assembling the blade platforms and the ferrule outside.
FIGS 1 to 7 show an embodiment of a rectifier vane 1 according to the invention and constituting a fixed stage of multi-flow turbojet.
rectifier vane 1 is constituted by a crown of blades fixed 2 arranged between a stator shell radially outer 3 and a radially inner stator shell 4.
the radially inner end 5 of each blade 2 is inserted into a slot 6 of complementary shape formed in said inner shroud 4.
the blade of the blade 2 brings to its radially outer end a platform 7 which is place in a housing 8 formed between two shoulders 9 on the inner face of the outer shell 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 holes correspondents 11.
the face upper 12 of platform 7 has a shape not plane whose radius of curvature before mounting the blade is R + delta R, as shown schematically in Figure 2.
the shape realized can be spherical or cylindrical.
the bottom 13 correspondent 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.
the platforms 7 of the blades 2 are fixed to the outer shell 3 by means of rivets 14 introduced in the corresponding holes 10 and 11.
the upper face 12 of the platform 7 and the bottom 13 of the housing 8 come into contact, by deformation of platforms whose radius R + delta R is made equal to the radius R of the housing, thus making the contact spherical or cylindrical depending on the shape adopted, between the platform 7 and housing 8.
washers 15 can be placed under the rivet heads 14 to avoid a matting effect on the outer shell 3, according to the used materials.
the shoulders 9 formed on each side of the housing 8 on the outer shell 3 allow the assembly of the platforms 7 in the housing 8 and also provide the anti-rotation locking of the blades during assembly and operation.
the adjacent edges 15 of the platforms 7 have a chamfer in one direction over half a length and the other way around on the other half length, like shown in figure 8.
a notch 16 triangular hollow can be formed on an edge 15 of platform while the adjacent platform edge neighbor 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 in 18 on the figure 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)

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
EP98201416A EP0953729B1 (de)	1998-05-01	1998-05-01	Leitbeschaufelung für eine Turbomaschine
DE69815815T DE69815815T2 (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 true EP0953729A1 (de)	1999-11-03
EP0953729B1 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 (7)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP1801357A1 (de)	2005-12-22	2007-06-27	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.
EP1936121A1 (de) *	2006-12-22	2008-06-25	Techspace aero	Winkelfixierung für Leitschaufeln von Turbomachinen
EP2075412A1 (de) *	2007-12-26	2009-07-01	Techspace aero	Vorrichtung zur Befestigung durch Verschraubung von Leitschaufeln an den Mantelring einer Statorstufe einer Strömungsmaschine und entsprechendes Befestigungsverfahren durch Verschraubung
US8469662B2 (en)	2008-12-22	2013-06-25	Techspace Aero S.A.	Guide vane architecture
EP2562361B2 (de) †	2011-08-25	2019-04-10	United Technologies Corporation	Strukturverbundfanleitschaufel für eine Turbomaschine
CN109986489A (zh) *	2019-03-12	2019-07-09	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

Families Citing this family (8)

* 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
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
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

Citations (9)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
DE967089C (de) *	1940-12-21	1957-10-03	Kuehnle Kopp Kausch Ag	Auswechselbare Axialleitapparat-Beschaufelung von Geblaesen, Pumpen u. dgl.
DE1476928A1 (de) *	1965-05-29	1969-07-31	Bergmann Borsig Veb	Leitschaufelfuss fuer Turbinen mit hoher Eintrittstemperatur
FR2106561A1 (de) *	1970-09-16	1972-05-05	United Kingdom Government
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
EP0243274A1 (de) *	1986-04-24	1987-10-28	Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A."	Unterteilter Dichtring für Turbinen
US4710097A (en) *	1986-05-27	1987-12-01	Avco Corporation	Stator assembly for gas turbine engine
US4722184A (en) *	1985-10-03	1988-02-02	United Technologies Corporation	Annular stator structure for a rotary machine
FR2671133A1 (fr)	1990-12-27	1992-07-03	Snecma	Aube a pivot a fixation rapide pour aubage redresseur de turbomachine et procede de fixation de ladite aube.
EP0616110A1 (de) *	1993-03-03	1994-09-21	Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma"	Schaufelnstufe mit freien Schaufelnenden

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US2661147A (en) *	1949-01-19	1953-12-01	Ingersoll Rand Co	Blower blade fastening device
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
US5622475A (en) *	1994-08-30	1997-04-22	General Electric Company	Double rabbet rotor blade retention assembly

1998
- 1998-05-01 EP EP98201416A patent/EP0953729B1/de not_active Expired - Lifetime
- 1998-05-01 DE DE69815815T patent/DE69815815T2/de not_active Expired - Lifetime
1999
- 1999-04-27 WO PCT/EP1999/003390 patent/WO2004074639A1/fr not_active Ceased
- 1999-04-27 US US09/446,131 patent/US6296442B1/en not_active Expired - Lifetime

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
DE967089C (de) *	1940-12-21	1957-10-03	Kuehnle Kopp Kausch Ag	Auswechselbare Axialleitapparat-Beschaufelung von Geblaesen, Pumpen u. dgl.
DE1476928A1 (de) *	1965-05-29	1969-07-31	Bergmann Borsig Veb	Leitschaufelfuss fuer Turbinen mit hoher Eintrittstemperatur
FR2106561A1 (de) *	1970-09-16	1972-05-05	United Kingdom Government
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
US4722184A (en) *	1985-10-03	1988-02-02	United Technologies Corporation	Annular stator structure for a rotary machine
EP0243274A1 (de) *	1986-04-24	1987-10-28	Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A."	Unterteilter Dichtring für Turbinen
US4710097A (en) *	1986-05-27	1987-12-01	Avco Corporation	Stator assembly for gas turbine engine
FR2671133A1 (fr)	1990-12-27	1992-07-03	Snecma	Aube a pivot a fixation rapide pour aubage redresseur de turbomachine et procede de fixation de ladite aube.
EP0616110A1 (de) *	1993-03-03	1994-09-21	Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma"	Schaufelnstufe mit freien Schaufelnenden

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP1801357A1 (de)	2005-12-22	2007-06-27	Techspace aero	Schaufelleitring einer Strömungsmaschine, Strömungsmaschine mit einem solchen Leitring und Leitschaufel
RU2435037C2 (ru) *	2006-09-26	2011-11-27	Снекма	Устройство крепления неподвижной лопатки в кольцевом картере турбомашины, турбореактивный двигатель, содержащий данное устройство, и способ монтажа лопатки
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.
EP1908923A1 (de) *	2006-09-26	2008-04-09	Snecma	Vorrichtung zur Befestigung einer Leitschaufel in einem ringförmigen Gehäuse einer Strömungsmaschine, Turbinentriebwerk, mit einer solche Vorrichtung, und Verfahren zur Montage der Leitschaufel
CN101153547B (zh) *	2006-09-26	2012-10-24	斯奈克玛	安装定子叶片的装置和涡轮喷气发动机及安装方法
US7959408B2 (en)	2006-09-26	2011-06-14	Snecma	Device for attaching a stator vane to a turbomachine annular casing, turbojet engine incorporating the device and method for mounting the vane
EP1936121A1 (de) *	2006-12-22	2008-06-25	Techspace aero	Winkelfixierung für Leitschaufeln von Turbomachinen
US8075264B2 (en)	2006-12-22	2011-12-13	Techspace Aero	Blade angle setting for a turbomachine
EP2075412A1 (de) *	2007-12-26	2009-07-01	Techspace aero	Vorrichtung zur Befestigung durch Verschraubung von Leitschaufeln an den Mantelring einer Statorstufe einer Strömungsmaschine und entsprechendes Befestigungsverfahren durch Verschraubung
US8469662B2 (en)	2008-12-22	2013-06-25	Techspace Aero S.A.	Guide vane architecture
EP2562361B2 (de) †	2011-08-25	2019-04-10	United Technologies Corporation	Strukturverbundfanleitschaufel für eine Turbomaschine
CN109986489A (zh) *	2019-03-12	2019-07-09	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
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

Also Published As

Publication number	Publication date
US6296442B1 (en)	2001-10-02
DE69815815D1 (de)	2003-07-31
DE69815815T2 (de)	2004-05-13
WO2004074639A1 (fr)	2004-09-02
EP0953729B1 (de)	2003-06-25

Legal Events

Date	Code	Title	Description
1999-09-17	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
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1999-11-03	AX	Request for extension of the european patent	Free format text: AL;LT;LV;MK;RO;SI
2000-01-26	17P	Request for examination filed	Effective date: 19991201
2000-07-12	AKX	Designation fees paid	Free format text: BE DE FR GB
2002-09-06	GRAH	Despatch of communication of intention to grant a patent	Free format text: ORIGINAL CODE: EPIDOS IGRA
2002-10-23	GRAH	Despatch of communication of intention to grant a patent	Free format text: ORIGINAL CODE: EPIDOS IGRA
2003-05-09	GRAA	(expected) grant	Free format text: ORIGINAL CODE: 0009210
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Publication	Publication Date	Title
EP0953729B1 (de)	2003-06-25	Leitbeschaufelung für eine Turbomaschine
CA2626118C (fr)	2015-09-08	Ensemble rotatif d'une soufflante de turbomachine
EP2937517B1 (de)	2019-03-06	Stator einer axialen Turbomaschine und zugehörige Turbomaschine
EP1262633B1 (de)	2005-03-16	Turbinenschaufel mit Labyrinthschneidendichtung
CA2639206C (fr)	2016-12-13	Etage d'aubes a calage variable pour une turbomachine
FR2688264A1 (fr)	1993-09-10	Redresseur de turbomachine a aubes ayant une face alveolee chargee en materiau composite.
CA2537672C (fr)	2013-10-08	Carter interne de turbomachine equipe d'un bouclier thermique
EP0214876B1 (de)	1989-03-15	Mehrzweck-Labyrinthträgerscheibe für einen Turbomaschinenrotor
EP0370899A1 (de)	1990-05-30	Schaufelplatte einer Turbine
EP0616110B1 (de)	1996-05-22	Schaufelnstufe mit freien Schaufelnenden
CA2734524A1 (fr)	2010-03-04	Aubage fixe de turbomachine a masse reduite et turbomachine comportant au moins un tel aubage fixe
WO2012114032A1 (fr)	2012-08-30	Rotor de soufflante et turboréacteur associé
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FR2971022A1 (fr)	2012-08-03	Etage redresseur de compresseur pour une turbomachine
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FR2671140A1 (fr)	1992-07-03	Aubage redresseur pour compresseur de turbomachine.
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