EP1503040A1 - Leichte Zwischenschaufelplattform für eine Schaufelstützscheibe eines Turbotriebwerkes - Google Patents

Leichte Zwischenschaufelplattform für eine Schaufelstützscheibe eines Turbotriebwerkes Download PDF

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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
Application number
EP04291888A
Other languages
English (en)
French (fr)
Other versions
EP1503040B1 (de
Inventor
Michèle Jacqueline Queriault
Claude Robert Louis Lejars
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
SNECMA Moteurs SA
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.)
Filing date
Publication date
Application filed by SNECMA Moteurs SA, SNECMA SAS filed Critical SNECMA Moteurs SA
Publication of EP1503040A1 publication Critical patent/EP1503040A1/de
Application granted granted Critical
Publication of EP1503040B1 publication Critical patent/EP1503040B1/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
    • 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)
EP04291888A 2003-07-31 2004-07-23 Leichte Zwischenschaufelplattform für eine Schaufelstützscheibe eines Turbotriebwerkes Expired - Lifetime EP1503040B1 (de)

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 (de) 2005-02-02
EP1503040B1 EP1503040B1 (de) 2007-02-14

Family

ID=33523037

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04291888A Expired - Lifetime EP1503040B1 (de) 2003-07-31 2004-07-23 Leichte Zwischenschaufelplattform für eine Schaufelstützscheibe eines Turbotriebwerkes

Country Status (9)

Country Link
US (1) US7163375B2 (de)
EP (1) EP1503040B1 (de)
JP (1) JP4216782B2 (de)
CA (1) CA2475145C (de)
DE (1) DE602004004700T2 (de)
ES (1) ES2277662T3 (de)
FR (1) FR2858370B1 (de)
RU (1) RU2343292C2 (de)
UA (1) UA77742C2 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
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 (10)

* Cited by examiner, † Cited by third party
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
US10119423B2 (en) * 2012-09-20 2018-11-06 United Technologies Corporation Gas turbine engine fan spacer platform attachments
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
US12410720B2 (en) 2023-11-02 2025-09-09 General Electric Company Turbine engine having a rotatable disk and a blade

Citations (3)

* Cited by examiner, † Cited by third party
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 (de) * 1994-03-19 1995-10-18 ROLLS-ROYCE plc Anordnung der Blaserschaufeln bei einem Gasturbinentriebwerk

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR989839A (fr) * 1949-06-28 1951-09-13 Cem Comp Electro Mec Aube pour turbo-machine
US2751189A (en) * 1950-09-08 1956-06-19 United Aircraft Corp Blade fastening means
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

Patent Citations (3)

* Cited by examiner, † Cited by third party
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 (de) * 1994-03-19 1995-10-18 ROLLS-ROYCE plc Anordnung der Blaserschaufeln bei einem Gasturbinentriebwerk

Cited By (1)

* Cited by examiner, † Cited by third party
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
DE602004004700T2 (de) 2007-11-22
CA2475145A1 (fr) 2005-01-31
UA77742C2 (uk) 2007-01-15
US7163375B2 (en) 2007-01-16
FR2858370A1 (fr) 2005-02-04
EP1503040B1 (de) 2007-02-14
FR2858370B1 (fr) 2005-09-30
CA2475145C (fr) 2012-08-28
ES2277662T3 (es) 2007-07-16
JP4216782B2 (ja) 2009-01-28
DE602004004700D1 (de) 2007-03-29
RU2343292C2 (ru) 2009-01-10
US20050276692A1 (en) 2005-12-15
RU2004123584A (ru) 2006-01-27
JP2005054785A (ja) 2005-03-03

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