EP0370899A1 - Schaufelplatte einer Turbine - Google Patents

Schaufelplatte einer Turbine Download PDF

Info

Publication number: EP0370899A1
Authority: EP; European Patent Office
Prior art keywords: disc; platform; foot; rotor; finned
Prior art date: 1988-11-23
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

EP89403217A

Other languages

English (en)

French (fr)

Other versions

EP0370899B1 (de

Inventor

François Marie Paul Marlin

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 Aircraft Engines SAS

Original Assignee

Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA

SNECMA SAS

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.)

1988-11-23

Filing date

1989-11-22

Publication date

1990-05-30

1989-11-22 Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA

1990-05-30 Publication of EP0370899A1 publication Critical patent/EP0370899A1/de

1992-01-02 Application granted granted Critical

1992-01-02 Publication of EP0370899B1 publication Critical patent/EP0370899B1/de

2009-11-22 Anticipated expiration legal-status Critical

Status 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
- F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
- 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
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations

Definitions

the present invention relates to a finned disc equipped with blades and separate platforms, intended in particular for a turbojet fan or for an aircraft engine compression stage.
GB-A- 2 171 151 thus describes a rotor comprising vanes which comprise only one blade and one foot, separate inter-blade platforms being mounted by a bulbous foot in an intermediate cell formed on the rim of the disc. between two cells carrying the blade roots.
this method of fixing imposing additional cells on the blade support disc does not give complete satisfaction for all applications.
the object of the invention is therefore to produce separate inter-blade platforms for turbomachine rotors, associated with improved means of attachment to a disc ensuring retention both in the radial direction and in the axial direction while taking into account the weight reduction requirements, the benefit of which is obvious for rotating parts and which is also an important criterion in the aeronautical applications targeted by the invention.
a finned turbomachine rotor disc of the type envisaged above, responding to these problems, is characterized in that that each platform comprises a plate delimiting the internal wall of the gas circulation stream and each axial end of which is connected to an element forming a fixing foot on the disc, cooperating with a cylindrical bearing formed on the rim of said disc, at least one of said platform feet being associated with a rider having a C-shaped section and securing said foot with a tooth-shaped element of the disc, a flange of an element neighboring the rotor and fixed to the disc being supported on said jumper so as to ensure axial locking.
FIGS. 1 to 4b relate to a turbojet fan and in particular in the case where the mobile rotor stage comprises large-rope blades associated with separate inter-blade platforms.
a fan disc 1 has axially oriented grooves, regularly distributed on the rim, at the periphery of the disc and forming cells 2 in which the feet are held of complementary shape to the fan blades 3.
Said rim of the disc 1 is extended on its front face, front and rear being defined with respect to the normal direction of gas flow in the turbomachine, by elements forming teeth 4, spaced from the front face 5 of the disc 1.
an annular ring 6 for axially locking the blades 3.
the front part of the rim of the disc 1 has a cylindrical bearing surface 7. On the rear part of said rim, a cylindrical bearing surface 8 surmounted by is also provided. an annular spoiler 9, thus creating an annular groove 10.
the disc 1 is also equipped with platforms 11 separate from the blades 3.
said platforms 11 are metallic and are, for example in the case described of an application to a turbojet fan, of a light metal such than titanium or one of its alloys.
Each platform 11, arranged between two consecutive blades 3 consists of an upper plate 12 which delimits the internal wall of the gas circulation stream, on the one hand peripherally between the two blades 3 and on the other hand longitudinally where the front edge 13 of the plate 12 is connected with the rear edge 14 of a support 15 of the inlet cone of the blower and the rear edge 16 comprises, for example, a connection groove at the front external edge 17 of a flange intermediate 18 fixed on the rear face 19 of the disc 1, for example by screw 20 at a fixing flange 21.
Said plate 12 is supported by legs, on each side, respectively 22 at the front and 23 at the rear, which are terminated by flanges forming fixing feet, respectively 24 at the front and 25 at the rear.
a reinforcing rib 26 is disposed under the internal face of the plate 12, in its middle, oriented in the axial direction, between the two legs 22 and 23.
Said foot 25 cooperates with said annular groove 10 of the disc 1 and rests on the bearing cylindrical 8 while the foot 24, at the front, rests on the cylindrical surface 7 of the disc 1.
a jumper-shaped element 27, arranged vertically so as to have in section a general shape of C keeps said front foot in place 24, the upper branch 28 of the rider cooperating with the upper surface of the foot 24 and the lower branch 29 cooperating with the internal faces of the disc tooth 4 and of the rod 6.
a flange 30 of the support 15 of the inlet cone, in support on the jumpers 27, ensures the axial locking of the assembly.
Each rider 27 and the disc tooth 4 further comprising respectively a corresponding bore in which is placed a pin 31 for positioning.
the method of mounting the platforms 11 which have just been described is as follows.
the rear foot 25 of the platform is introduced into the groove 10 of the disc 1 and the front foot 24 is supported on the front cylindrical surface 7 of the disc 1 then the rider 27 is positioned by placing the pin 31 on the tooth 4 disc.
the support 15 of the inlet cone is put in place, the flange 30 of its rear part coming to bear on the jumper 27 and finally, a fixing flange 32 of said support 15 is fixed by bolts at 33 on a flange 34 integral with the front of the disc 1.
each platform 111 comprises two box-shaped elements, respectively 111a and 111b, having a generally triangular or trapezoidal cross-section and joined along one side, thus constituting a central rib 126.
box elements 111a and 111b can be obtained by winding or by stripping of fabrics of composite material and after assembly, they are joined together by a winding or stripping of fabrics also of composite material, creating an outer skin 111c and also constituting an upper plate 112.
the platform 111 also comprises on each edge, a reinforcement element, respectively 35 at the front and 36 at the rear and these reinforcements also form the feet of platform mounting, 124 front and 125 rear respectively.
FIG. 4b shows the detail of embodiment of the reinforcement 35.
the peripheral lateral edges of the platform 111 each receive a seal, respectively 37 and 38 which provide the seal and the connection between the platform 111 and the blade 3 adjacent, on each side.
the other elements of the embodiment described with reference to FIGS. 1 and 2 are kept identical, in particular the fixing of the rear foot 125 engaging in the annular groove 10 of the disc 1 and at the front, the fixing of the front foot 124 by means of a jumper 27, axially blocked by the flange 30 of the support 15 of the fan inlet cone.
the assembly method previously described with reference to FIGS. 1 and 2 is also kept identical in the variant embodiment according to FIG. 3.
the means for fixing the platform can be provided at the rear identical to those which have been described for the front, namely using jumpers such as 27.

Landscapes

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

EP89403217A 1988-11-23 1989-11-22 Schaufelplatte einer Turbine Expired - Lifetime EP0370899B1 (de)

Applications Claiming Priority (2)

Application Number	Priority Date	Filing Date	Title
FR8815234A FR2639402B1 (fr)	1988-11-23	1988-11-23	Disque ailete de rotor de turbomachine
FR8815234		1988-11-23

Publications (2)

Publication Number	Publication Date
EP0370899A1 true EP0370899A1 (de)	1990-05-30
EP0370899B1 EP0370899B1 (de)	1992-01-02

Family

ID=9372135

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP89403217A Expired - Lifetime EP0370899B1 (de)	1988-11-23	1989-11-22	Schaufelplatte einer Turbine

Country Status (4)

Country	Link
US (1)	US5049035A (de)
EP (1)	EP0370899B1 (de)
DE (1)	DE68900646D1 (de)
FR (1)	FR2639402B1 (de)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
WO1993021425A1 (en) *	1992-04-16	1993-10-28	Rolls-Royce Plc	Rotors for gas turbine engines
WO1993022539A1 (en) *	1992-05-07	1993-11-11	Rolls-Royce Plc	Rotors for gas turbine engines
FR2706528A1 (fr) *	1993-06-10	1994-12-23	Snecma	Plate-forme séparée inter-aube de disque ailette de rotor de turbomachine.
FR2960589A1 (fr) *	2010-05-28	2011-12-02	Snecma	Roue a aubes pour une turbomachine, telle qu'un turboreacteur ou un turbopropulseur d'avion
FR2982635A1 (fr) *	2011-11-15	2013-05-17	Snecma	Roue a aubes pour une turbomachine
GB2519845A (en) *	2013-09-09	2015-05-06	Snecma	Blisk with low stresses at blade root, preferably for an aircraft turbine engine fan

Families Citing this family (30)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
FR2669686B1 (fr) *	1990-11-28	1994-09-02	Snecma	Rotor de soufflante avec aubes sans plates-formes et sabots reconstituant le profil de veine.
US5151013A (en) *	1990-12-27	1992-09-29	United Technologies Corporation	Blade lock for a rotor disk and rotor blade assembly
FR2679296B1 (fr) *	1991-07-17	1993-10-15	Snecma	Plate-forme separee inter-aube pour disque ailete de rotor de turbomachine.
US5277548A (en) *	1991-12-31	1994-01-11	United Technologies Corporation	Non-integral rotor blade platform
US5232346A (en) *	1992-08-11	1993-08-03	General Electric Company	Rotor assembly and platform spacer therefor
US5281096A (en) *	1992-09-10	1994-01-25	General Electric Company	Fan assembly having lightweight platforms
US6217283B1 (en) *	1999-04-20	2001-04-17	General Electric Company	Composite fan platform
US6435820B1 (en) *	1999-08-25	2002-08-20	General Electric Company	Shroud assembly having C-clip retainer
US6520742B1 (en) *	2000-11-27	2003-02-18	General Electric Company	Circular arc multi-bore fan disk
US6447250B1 (en) *	2000-11-27	2002-09-10	General Electric Company	Non-integral fan platform
GB0614640D0 (en) *	2006-07-22	2006-08-30	Rolls Royce Plc	An annulus filler seal
US8568102B2 (en) *	2009-02-18	2013-10-29	Pratt & Whitney Canada Corp.	Fan blade anti-fretting insert
US8616849B2 (en) *	2009-02-18	2013-12-31	Pratt & Whitney Canada Corp.	Fan blade platform
FR2963383B1 (fr) *	2010-07-27	2016-09-09	Snecma	Aube de turbomachine, rotor, turbine basse pression et turbomachine equipes d'une telle aube
FR2965843B1 (fr) *	2010-10-06	2012-11-09	Snecma	Rotor pour turbomachine
FR2973434A1 (fr) *	2011-03-30	2012-10-05	Snecma	Distributeur de turbine en cmc adapte au support d'un carter interne de turbine metallique par un contact radial
FR2974864B1 (fr) *	2011-05-04	2016-05-27	Snecma	Rotor de turbomachine avec moyen de retenue axiale des aubes
FR2974863B1 (fr) *	2011-05-06	2015-10-23	Snecma	Disque de soufflante de turbomachine
US8777576B2 (en) *	2011-08-22	2014-07-15	General Electric Company	Metallic fan blade platform
US10145268B2 (en) *	2013-03-15	2018-12-04	United Technologies Corporation	Injection molded composite fan platform
US9845699B2 (en) *	2013-03-15	2017-12-19	Gkn Aerospace Services Structures Corp.	Fan spacer having unitary over molded feature
FR3022944B1 (fr)	2014-06-26	2020-02-14	Safran Aircraft Engines	Ensemble rotatif pour turbomachine
US10024234B2 (en) *	2014-09-08	2018-07-17	Rolls-Royce Deutschland Ltd & Co Kg	Panels of a fan of a gas turbine
FR3035678B1 (fr) *	2015-04-29	2017-05-12	Snecma	Aube munie de plateformes possedant une jambe de retenue
FR3038653B1 (fr) *	2015-07-08	2017-08-04	Snecma	Assemblage d'une plateforme rapportee d'aube de soufflante sur un disque de soufflante
US9976426B2 (en) *	2015-07-21	2018-05-22	United Technologies Corporation	Fan platform with stiffening feature
US10215046B2 (en) *	2015-11-23	2019-02-26	United Technologies Corporation	Airfoil platform having dual pin apertures and a vertical stiffener
US10584592B2 (en) *	2015-11-23	2020-03-10	United Technologies Corporation	Platform for an airfoil having bowed sidewalls
FR3073907B1 (fr) *	2017-11-17	2020-12-11	Safran Aircraft Engines	Organe de retention pour plateforme de turbomachine
US12012857B2 (en) *	2022-10-14	2024-06-18	Rtx Corporation	Platform for an airfoil of a gas turbine engine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US3294364A (en) *	1962-01-02	1966-12-27	Gen Electric	Rotor assembly
US3712757A (en) *	1969-10-28	1973-01-23	Secr Defence	Bladed rotors for fluid flow machines
US4033705A (en) *	1976-04-26	1977-07-05	The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration	Blade retainer assembly
GB2006883A (en) *	1977-10-27	1979-05-10	Rolls Royce	Fan or Compressor Rotor Stage
FR2413543A1 (fr) *	1977-12-28	1979-07-27	Gen Electric	Dispositif de retenue d'aubes de turbomachine
GB2171151A (en) *	1985-02-20	1986-08-20	Rolls Royce	Rotors for gas turbine engines

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US2873088A (en) *	1953-05-21	1959-02-10	Gen Electric	Lightweight rotor construction
BE540433A (de) *	1954-08-12
NL102164C (de) *	1956-11-30
GB1093568A (en) *	1965-11-23	1967-12-06	Rolls Royce	Improvements in or relating to bladed rotors such as compressor rotors
GB1318654A (en) *	1970-12-05	1973-05-31	Secr Defence	Bladed rotors
US3888601A (en) *	1974-05-23	1975-06-10	Gen Electric	Turbomachine with balancing means

1988
- 1988-11-23 FR FR8815234A patent/FR2639402B1/fr not_active Expired - Lifetime
1989
- 1989-11-22 EP EP89403217A patent/EP0370899B1/de not_active Expired - Lifetime
- 1989-11-22 DE DE8989403217T patent/DE68900646D1/de not_active Expired - Lifetime
- 1989-11-24 US US07/441,045 patent/US5049035A/en not_active Expired - Lifetime

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US3294364A (en) *	1962-01-02	1966-12-27	Gen Electric	Rotor assembly
US3712757A (en) *	1969-10-28	1973-01-23	Secr Defence	Bladed rotors for fluid flow machines
US4033705A (en) *	1976-04-26	1977-07-05	The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration	Blade retainer assembly
GB2006883A (en) *	1977-10-27	1979-05-10	Rolls Royce	Fan or Compressor Rotor Stage
FR2413543A1 (fr) *	1977-12-28	1979-07-27	Gen Electric	Dispositif de retenue d'aubes de turbomachine
GB2171151A (en) *	1985-02-20	1986-08-20	Rolls Royce	Rotors for gas turbine engines

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
WO1993021425A1 (en) *	1992-04-16	1993-10-28	Rolls-Royce Plc	Rotors for gas turbine engines
US5466125A (en) *	1992-04-16	1995-11-14	Rolls-Royce Plc	Rotors for gas turbine engines
WO1993022539A1 (en) *	1992-05-07	1993-11-11	Rolls-Royce Plc	Rotors for gas turbine engines
US5464326A (en) *	1992-05-07	1995-11-07	Rolls-Royce, Plc	Rotors for gas turbine engines
FR2706528A1 (fr) *	1993-06-10	1994-12-23	Snecma	Plate-forme séparée inter-aube de disque ailette de rotor de turbomachine.
US5421704A (en) *	1993-06-10	1995-06-06	Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma"	Inter-blade platform for a bladed disc of a turbomachine rotor
FR2960589A1 (fr) *	2010-05-28	2011-12-02	Snecma	Roue a aubes pour une turbomachine, telle qu'un turboreacteur ou un turbopropulseur d'avion
FR2982635A1 (fr) *	2011-11-15	2013-05-17	Snecma	Roue a aubes pour une turbomachine
WO2013072605A1 (fr) *	2011-11-15	2013-05-23	Snecma	Roue a aubes pour une turbomachine
US9726033B2 (en)	2011-11-15	2017-08-08	Snecma	Rotor wheel for a turbine engine
GB2519845A (en) *	2013-09-09	2015-05-06	Snecma	Blisk with low stresses at blade root, preferably for an aircraft turbine engine fan
GB2519845B (en) *	2013-09-09	2020-03-18	Snecma	Blisk with low stresses at blade root, preferably for an aircraft turbine engine fan

Also Published As

Publication number	Publication date
EP0370899B1 (de)	1992-01-02
FR2639402A1 (fr)	1990-05-25
FR2639402B1 (fr)	1990-12-28
DE68900646D1 (de)	1992-02-13
US5049035A (en)	1991-09-17

Legal Events

Date	Code	Title	Description
1990-04-13	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
1990-05-30	17P	Request for examination filed	Effective date: 19891204
1990-05-30	AK	Designated contracting states	Kind code of ref document: A1 Designated state(s): DE FR GB
1991-03-13	17Q	First examination report despatched	Effective date: 19910130
1991-11-15	GRAA	(expected) grant	Free format text: ORIGINAL CODE: 0009210
1992-01-02	AK	Designated contracting states	Kind code of ref document: B1 Designated state(s): DE FR GB
1992-02-13	REF	Corresponds to:	Ref document number: 68900646 Country of ref document: DE Date of ref document: 19920213
1992-02-19	GBT	Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
1992-11-05	PLBE	No opposition filed within time limit	Free format text: ORIGINAL CODE: 0009261
1992-11-05	STAA	Information on the status of an ep patent application or granted ep patent	Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT
1992-12-23	26N	No opposition filed
2002-01-01	REG	Reference to a national code	Ref country code: GB Ref legal event code: IF02
2002-01-25	REG	Reference to a national code	Ref country code: FR Ref legal event code: TP Ref country code: FR Ref legal event code: CD
2006-02-10	REG	Reference to a national code	Ref country code: FR Ref legal event code: CD
2008-01-31	PGFP	Annual fee paid to national office [announced via postgrant information from national office to epo]	Ref country code: DE Payment date: 20071113 Year of fee payment: 19
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2009-07-29	GBPC	Gb: european patent ceased through non-payment of renewal fee	Effective date: 20081122
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Publication	Publication Date	Title
EP0370899B1 (de)	1992-01-02	Schaufelplatte einer Turbine
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FR2943984A1 (fr)	2010-10-08	Helice pour turbomachine d'aeronef comprenant un moyeu support d'aubes scinde en deux portions annulaires montees l'une sur l'autre.
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FR2729709A1 (fr)	1996-07-26	Dispositif d'etancheite et de retention des aubes de rotor de turbomachine
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FR2636378A1 (fr)	1990-03-16	Redresseur de soufflante de turboreacteur a double flux
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