EP1503040A1 - Plate-forme inter-aubes allégée, pour un disque de support d'aubes de turboréacteur - Google Patents
Plate-forme inter-aubes allégée, pour un disque de support d'aubes de turboréacteur Download PDFInfo
- Publication number
- EP1503040A1 EP1503040A1 EP04291888A EP04291888A EP1503040A1 EP 1503040 A1 EP1503040 A1 EP 1503040A1 EP 04291888 A EP04291888 A EP 04291888A EP 04291888 A EP04291888 A EP 04291888A EP 1503040 A1 EP1503040 A1 EP 1503040A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- fixing
- blade
- platform
- platform according
- orifices
- 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
Links
- 239000002131 composite material Substances 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 239000007769 metal material Substances 0.000 claims description 2
- 238000003754 machining Methods 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 210000003462 vein Anatomy 0.000 description 2
- CBVWMGCJNPPAAR-HJWRWDBZSA-N (nz)-n-(5-methylheptan-3-ylidene)hydroxylamine Chemical compound CCC(C)C\C(CC)=N/O CBVWMGCJNPPAAR-HJWRWDBZSA-N 0.000 description 1
- 230000002159 abnormal effect Effects 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000037406 food intake Effects 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000007787 solid Substances 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
- 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
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
Definitions
- the invention relates to the field of turbojets, and more particularly that of platforms inter-blades for blade support discs of turbojet blowers.
- Blowers (or "fan") of turbojet typically include blade support discs equipped with inter-blade platforms reported to optimize the flow of air between the blades, and more precisely to reconstitute the aerodynamic profile of the internal "vein” at the blades.
- the first mode is to arrange the three brackets in the form of flanges provided with an orifice for the passage of a fixing pin.
- the second mode is to arrange two of the three brackets under the form of flanges provided with an orifice for the passage of a fixing pin, and to be provided the third fastening lug of a bayonet type fastening device.
- the dawn when an incident occurs on a dawn, for example because of the ingestion of a foreign body by the turbojet, the dawn can move (or flex) and interfere with the side edge of one of the neighboring platforms.
- said platforms deform while remaining substantially in place, which can cause significant damage to the dawn, or even in the engine part of the turbojet engine located downstream of the blades, and / or induce a loss of efficiency of the turbojet, or even its decommissioning.
- the invention therefore aims to improve the situation.
- an inter-blade platform for a blade support disc of a turbojet fan comprising a deflecting portion having a lower face provided with a first fixing lug provided with a first orifice for the passage of a first securing pin, and a second securing tab provided with second and third orifices for the passage of second and third fixing pins, these pins of fixation being intended to secure the two fixing lugs (or flanges) to the disk of support between two adjacent blades.
- first and second orifices can be placed in the first and second fixing lugs, substantially opposite from one another, so that the first and second fixing pins are substantially aligned along the same axis.
- the platform in case of rupture of the third fixing pin, under the impact of a blade (or any other constraint, in particular centrifugal), the platform can be rotated around the axis defined by the two other fixing pins. This frees up space for constrained dawn and to prevent the platform from being deformed harmful to both neighboring blades and performance.
- the third pin may have a lower stress resistance than the first and second fixing pins.
- the sections of the first and second pieces may be greater than that of the third attachment pin and / or their materials may be different.
- Such a platform can be made of a metallic or composite material.
- the invention also relates to a blade support disk having a multiplicity inter-blade platforms of the type presented above and interspersed respectively between pairs of adjacent blades.
- the invention relates to an inter-blade platform for equipping a support disk of blades for a blower (or “fan”) of a turbojet engine equipped with blades with curvilinear feet (also called “wide rope” blades).
- a blade support disc 1 is a element of a blower (not shown), mounted on a rotor shaft and on which are fixed a multiplicity of blades 2, curvilinear foot, and a multiplicity of platforms inter-blades 3 reported, preferably metal (eg aluminum). More precisely, each reported platform 3 is installed on the support disc 1, between two blades 2 in order to reconstruct the aerodynamic profile of the internal "vein" blades.
- each platform 3 comprises a baffle portion 4 having a lower face 5 provided with a first fixing lug (or flange) 6 provided with a first orifice 7 for the passage of a first fixing pin 8, and a second fixing lug (or flange) 9 provided with second 10 and third 11 orifices for the passage of second 12 and third 13 fixing pins.
- the second 10 and third 11 orifices are placed one next to the other, substantially in one level, so that the third pawn 13 undergoes the least constraints possible. But, they could also be superimposed or staggered Laterally and in height.
- the fixing pins 8, 12 and 13 are preferably of the shouldered and threaded type. They each comprise a stem one end of which is provided with a shoulder head and the other end of a thread cooperating with a nut 14, 15 or 16, so as to immobilize the corresponding fixing lug 6 or 9 on one of the fixing lugs 17 or 18 of a element 19 of the support disk 1.
- the first fixing pin 8 is intended to immobilize the first fastening lug 6 on the fastening lug 17 of the element 19
- the second 12 and third 13 fixing pins are intended to immobilize the second fixing lug 9 on the fixing lug 18 of said element 19.
- the first port 7 and the second port 10 are placed in the first 6 and second 9 legs of fastening, substantially facing one another, so that the first 8 and second 12 fixing pins are substantially aligned along the same axis X.
- the platform 3 when the third attachment pin 13 breaks, by example because of a centrifugal stress or under the impact of a blade 2 object of a constrained, the platform 3 can pivot around the X axis defined by the alignment of the two securing pins 8 and 12. The released platform 3 can then follow the movements of the constraints (or afflicted) by the events, so that the whole finds a new equilibrium position, the platform 3 can indeed rely on a dawn flank 2 up to a certain point (beyond a certain displacement there is indeed a break in platform and pawns).
- the platform 3 is little or not deformed, which guarantees a little aerodynamic flow modified, but above all it remains fully in place, which prevents it from being ingested by the turbojet engine.
- the third broken attachment pin 13 remains prisoner of the "box” that defines the platform 3, so that it does not risk damaging elements located at the rear of the blower.
- this rotation of the platform 3 free space for dawn 2 which has moved under the effect of the constraint, which prevents it from being seriously damaged.
- the third fixing pin 13 In order to promote breaking of the third fixing pin 13 in the event of an incident, it may have the same dimensions as the first 8 and second 12 pieces of fixation but a resistance to stresses lower than theirs, ie to present a section transverse lower than that of the first 8 and second 12 fixing pins. This last solution is illustrated in Figure 2.
- the first 7 and second 10 orifices have dimensions that are substantially identical but superior to those of the third 11 to receive first 8 and second 12 fixing pins whose section transverse is greater than that of the third fixing pin 13.
- third fixing pin 13 "breakable"
- the first 8 and second 12 fixing pins thus support the centrifugal forces
- said third fixing pin 13 serves in normal operation to ensure the isostatism of the platform 3 and in abnormal operation to trigger, in case of rupture, the pivoting of said platform 3.
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)
Abstract
Description
- la figure 1 illustre de façon schématique une partie d'un disque de support d'aubes dans une vue de face,
- la figure 2 illustre de façon schématique, dans une vue en coupe transversale décalée, un mode de réalisation d'une plate-forme inter-aubes selon l'invention, et
- la figure 3 est une vue en coupe selon l'axe III-III de la figure 2, d'une plate-forme inter-aubes selon l'invention illustrant un exemple de réalisation d'une patte de fixation à deux orifices.
Claims (9)
- Plate-forme inter-aubes (3) pour un disque (1) de support d'aubes (2) d'une soufflante de turboréacteur, caractérisée en ce qu'elle comprend une partie déflectrice (4) comportant une face inférieure (5) munie d'une première patte de fixation (6) pourvue d'un premier orifice (7) pour le passage d'un premier pion de fixation (8), et d'une seconde patte de fixation (9) pourvue d'un deuxième (10) et d'un troisième (11) orifices pour le passage d'un deuxième (12) et d'un troisième (13) pions de fixation, lesdits pions de fixation (8,12,13) étant destinés à solidariser lesdites pattes de fixation (6,9) audit disque de support (1) entre deux aubes adjacentes (2).
- Plate-forme selon la revendication 1, caractérisée en ce que lesdits premier (7) et deuxième (10) orifices sont placés dans lesdites première (6) et seconde (9) pattes de fixation sensiblement en regard l'un de l'autre, de sorte que lesdits premier (8) et deuxième (12) pions de fixation soient sensiblement alignés suivant un même axe (X).
- Plate-forme selon l'une des revendications 1 et 2, caractérisée en ce que ledit troisième pion de fixation (13) présente une résistance aux contraintes inférieure à celle desdits premier (8) et deuxième (12) pions de fixation.
- Plate-forme selon la revendication 3, caractérisée en ce que lesdits premier (7) et deuxième (10) orifices présentent des dimensions sensiblement identiques et sont propres à recevoir des premier (8) et deuxième (12) pions de fixation présentant une première section choisie, et en ce que ledit troisième orifice (11) présente des dimensions sensiblement inférieures à celles desdits premier (7) et deuxième (10) orifices de manière à recevoir un troisième pion de fixation (13) présentant une seconde section inférieure à ladite première section.
- Plate-forme selon l'une des revendications 3 et 4, caractérisée en ce que ledit troisième pion de fixation (13) est réalisé dans un matériau dont la résistance aux contraintes est inférieure à celle des matériaux constituant lesdits premier (8) et deuxième (12) pions de fixation.
- Plate-forme selon l'une des revendications 1à 5, caractérisée en ce que lesdits second (10) et troisième (11) orifices de la seconde patte de fixation (9) sont placés l'un à côté de l'autre, sensiblement en un même niveau.
- Plate-forme selon l'une des revendications 1à 6, caractérisée en ce qu'elle est réalisée dans un matériau métallique.
- Plate-forme selon l'une des revendications 1à 6, caractérisée en ce qu'elle est réalisée dans un matériau composite.
- Disque de support d'aubes (1), caractérisé en ce qu'il comporte une multiplicité de plate-formes inter-aubes (3) selon l'une des revendications précédentes, respectivement intercalées entre des paires d'aubes (2) adjacentes.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0309452A FR2858370B1 (fr) | 2003-07-31 | 2003-07-31 | Plate-forme inter-aubes allegee, pour un disque de support d'aubes de turboreacteur |
FR0309452 | 2003-07-31 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1503040A1 true EP1503040A1 (fr) | 2005-02-02 |
EP1503040B1 EP1503040B1 (fr) | 2007-02-14 |
Family
ID=33523037
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04291888A Expired - Lifetime EP1503040B1 (fr) | 2003-07-31 | 2004-07-23 | Plate-forme inter-aubes allégée, pour un disque de support d'aubes de turboréacteur |
Country Status (9)
Country | Link |
---|---|
US (1) | US7163375B2 (fr) |
EP (1) | EP1503040B1 (fr) |
JP (1) | JP4216782B2 (fr) |
CA (1) | CA2475145C (fr) |
DE (1) | DE602004004700T2 (fr) |
ES (1) | ES2277662T3 (fr) |
FR (1) | FR2858370B1 (fr) |
RU (1) | RU2343292C2 (fr) |
UA (1) | UA77742C2 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2926613A1 (fr) * | 2008-01-23 | 2009-07-24 | Snecma Sa | Disque de soufflante de turbomachine |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2913734B1 (fr) * | 2007-03-16 | 2009-05-01 | Snecma Sa | Soufflante de turbomachine |
FR2933887B1 (fr) * | 2008-07-18 | 2010-09-17 | Snecma | Procede de reparation ou de reprise d'un disque de turbomachine et disque de turbomachine repare ou repris |
US8939727B2 (en) | 2011-09-08 | 2015-01-27 | Siemens Energy, Inc. | Turbine blade and non-integral platform with pin attachment |
WO2014088673A2 (fr) * | 2012-09-20 | 2014-06-12 | United Technologies Corporation | Dispositifs de fixation de plateforme d'élément d'espacement de ventilateur de turbine à gaz |
US9759226B2 (en) * | 2013-02-15 | 2017-09-12 | United Technologies Corporation | Low profile fan platform attachment |
US10584592B2 (en) * | 2015-11-23 | 2020-03-10 | United Technologies Corporation | Platform for an airfoil having bowed sidewalls |
US10458425B2 (en) | 2016-06-02 | 2019-10-29 | General Electric Company | Conical load spreader for composite bolted joint |
FR3089548B1 (fr) * | 2018-12-07 | 2021-03-19 | Safran Aircraft Engines | Soufflante comprenant une plateforme inter-aubes fixee a l’amont par une virole |
FR3097904B1 (fr) * | 2019-06-26 | 2021-06-11 | Safran Aircraft Engines | Plateforme inter-aube avec caisson sacrificiel |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4621979A (en) * | 1979-11-30 | 1986-11-11 | United Technologies Corporation | Fan rotor blades of turbofan engines |
US5277548A (en) * | 1991-12-31 | 1994-01-11 | United Technologies Corporation | Non-integral rotor blade platform |
EP0677645A1 (fr) * | 1994-03-19 | 1995-10-18 | ROLLS-ROYCE plc | Arrangement des aubes de soufflante d'un réacteur à turbine à gaz |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3455537A (en) * | 1967-09-27 | 1969-07-15 | Continental Aviat & Eng Corp | Air-cooled turbine rotor self-sustaining shroud plate |
US6447250B1 (en) * | 2000-11-27 | 2002-09-10 | General Electric Company | Non-integral fan platform |
-
2003
- 2003-07-31 FR FR0309452A patent/FR2858370B1/fr not_active Expired - Fee Related
-
2004
- 2004-07-19 US US10/893,272 patent/US7163375B2/en not_active Expired - Lifetime
- 2004-07-23 DE DE602004004700T patent/DE602004004700T2/de not_active Expired - Lifetime
- 2004-07-23 CA CA2475145A patent/CA2475145C/fr not_active Expired - Lifetime
- 2004-07-23 ES ES04291888T patent/ES2277662T3/es not_active Expired - Lifetime
- 2004-07-23 EP EP04291888A patent/EP1503040B1/fr not_active Expired - Lifetime
- 2004-07-29 JP JP2004221231A patent/JP4216782B2/ja not_active Expired - Lifetime
- 2004-07-30 UA UA20040706363A patent/UA77742C2/uk unknown
- 2004-07-30 RU RU2004123584/06A patent/RU2343292C2/ru active
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4621979A (en) * | 1979-11-30 | 1986-11-11 | United Technologies Corporation | Fan rotor blades of turbofan engines |
US5277548A (en) * | 1991-12-31 | 1994-01-11 | United Technologies Corporation | Non-integral rotor blade platform |
EP0677645A1 (fr) * | 1994-03-19 | 1995-10-18 | ROLLS-ROYCE plc | Arrangement des aubes de soufflante d'un réacteur à turbine à gaz |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2926613A1 (fr) * | 2008-01-23 | 2009-07-24 | Snecma Sa | Disque de soufflante de turbomachine |
Also Published As
Publication number | Publication date |
---|---|
RU2343292C2 (ru) | 2009-01-10 |
CA2475145C (fr) | 2012-08-28 |
UA77742C2 (uk) | 2007-01-15 |
JP2005054785A (ja) | 2005-03-03 |
JP4216782B2 (ja) | 2009-01-28 |
CA2475145A1 (fr) | 2005-01-31 |
DE602004004700D1 (de) | 2007-03-29 |
ES2277662T3 (es) | 2007-07-16 |
DE602004004700T2 (de) | 2007-11-22 |
EP1503040B1 (fr) | 2007-02-14 |
RU2004123584A (ru) | 2006-01-27 |
US20050276692A1 (en) | 2005-12-15 |
FR2858370B1 (fr) | 2005-09-30 |
FR2858370A1 (fr) | 2005-02-04 |
US7163375B2 (en) | 2007-01-16 |
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