EP1400698B1 - Kontrolle der axialen Lage einer Verdichterschaufel - Google Patents

Kontrolle der axialen Lage einer Verdichterschaufel Download PDF

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Publication number
EP1400698B1
EP1400698B1 EP03292280A EP03292280A EP1400698B1 EP 1400698 B1 EP1400698 B1 EP 1400698B1 EP 03292280 A EP03292280 A EP 03292280A EP 03292280 A EP03292280 A EP 03292280A EP 1400698 B1 EP1400698 B1 EP 1400698B1
Authority
EP
European Patent Office
Prior art keywords
blade
disk
upstream
fact
blade root
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
EP03292280A
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English (en)
French (fr)
Other versions
EP1400698A1 (de
Inventor
Alain Jacques Michel Bassot
Jean-Claude Bonny
Philippe Even
Pierre Antoine Lamothe
Alain Madec
Patrick Jean-Louis Reghezza
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 SAS
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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1400698A1 publication Critical patent/EP1400698A1/de
Application granted granted Critical
Publication of EP1400698B1 publication Critical patent/EP1400698B1/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber

Definitions

  • the invention relates to a system for controlling the axial position of the removable vanes of a blower of the turbojet engine.
  • a fan rotor comprising a disk whose rim comprises a plurality of substantially axial grooves and regularly distributed angularly, a plurality of removable blades which extend radially outwardly to the periphery of said disk, each blade comprising a blade root housed in a groove, a downstream flange integral with said disk and a removable upstream flange integral with said disk and for retaining the blade roots in the grooves, as defined in the preamble of claim 1.
  • a rotor is known from the document US-A-4,033,705 .
  • the upstream face refers to the forward facing face of the engine and the downstream face refers to the rearward facing face.
  • the upstream flange of a fan rotor is generally removable to allow the replacement of a blade in case of damage. This can occur in case of ingestion of foreign bodies, such as birds, especially during the take-off and approach phases of the aircraft equipped with turbojets.
  • the blade assembly on the disk has axial clearance.
  • the random axial positioning of the fan blades inside this set imbalances the rotor and generates vibrations during operation. This is all the more important as the fan blades has large-rope blades.
  • the considerable centrifugal forces supported by the blades of the blades in operation can also cause a random axial displacement of the blades within this set of mounting.
  • US 4,033,705 reveals an axial blade retention system which comprises at each end of a blade root a pin which cooperates with two oblique mortises formed in the rim of the disk on either side of the groove receiving the blade root.
  • the pins provided on each disk face are retained radially by a ring secured to the disk.
  • This document provides between each end face of the blade root and the adjacent post a spring plate whose role is to immobilize the tenon radially during assembly of the blades, before the establishment and fixing of the ring restraint. These springs create a mounting set at each end of blade, as shown in Figure 7 of this document, which is not mastered.
  • US 5,282,720 provides to insert between the retaining flanges and the ends of the blade roots, honeycomb elements for absorbing part of the energy in case of ingestion of birds. During ingestion, the honeycomb gradually deforms and dissipates some of the energy. The honeycomb elements must maintain their integrity during the mounting of the flanges, so inevitably there is an axial play after assembly, and a random axial displacement is possible in operation of the blower.
  • the object of the invention is to provide a fan rotor as described in the introduction in which the axial position of the blades is controlled by a simple and inexpensive device, without creating any problem for the assembly and disassembly of the blades in case of possible repair.
  • the fan rotor further comprises a wedge interposed between each blade root and the bottom of the corresponding groove, this wedge having a radial heel bearing against the upstream face of said blade root, the elastic means are advantageously in support against said heels.
  • the figure 1 shows an X-axis fan rotor 1 which has a disk 2 and a plurality of vanes 3 regularly angularly spaced about the X axis which extend radially outwardly around the periphery of the disk 2.
  • Each of the vanes 3 comprises a blade root 4 which is retained in a groove or substantially axial cavity 5 formed in the rim of the disk 2.
  • the blade roots 4 have a dovetail shape, and the grooves 5 have a complementary shape . Under the action of the centrifugal forces, when the fan is in operation, the blade roots 4 are retained in the grooves 5 by the radially outer walls of these grooves 5.
  • a shim 6 is disposed between the base of each blade root 4 and the bottom of the groove 5.
  • This shim 6 comprises, on the side of the upstream face 7 of the disk 2, a heel 8 which bears against the upstream face. 9 of the foot 4 of the blade 3.
  • the role of the shim 6 is to prevent the blade 3 from falling into the groove 5, when stopping the fan and to collect a portion of the energy when of a shock on the blade of the dawn as a result of the ingestion of a foreign body for example or the rupture of a neighboring dawn.
  • downstream face 10 of the disk 2 On the downstream face 10 of the disk 2 is fixed a downstream flange, not shown in the drawings, against which the feet 4 of the vanes 3 abut.
  • An upstream flange 12 is also provided on the upstream face 7 of the disk 2, the role of which is to prevent the feet 4 of the blades 3 from escaping from the grooves 5 by sliding after the mounting of the rotor 1.
  • This upstream flange 12 is fixed on disk 2 flanges by screws, so to allow its disassembly, in case of need to replace a blade 3.
  • the upstream flange 12 comprises, in front of each blade root 4, an orifice 15 which holds the barrel 16 of a pin 17 made of elastomer, this pin 17 comprising a head 18 of diameter greater than that of the orifice 15, and having a thickness at least equal to the set J.
  • the head 18 of the pin 17 is disposed on the downstream face 13 of the upstream flange 12, and this head 18 is compressed between the downstream face 13 of the upstream flange 12 and the upstream face of the heel 8 of the spacer 6.
  • the pin 17 thus exerts elastic forces on the heel 8 in an axial direction.
  • the heel 8 is in abutment against the adjacent blade root 4, the latter is constantly urged towards the downstream flange, against which it is in abutment.
  • This simple arrangement makes it possible to control the axial play of the blades 3 and to prevent random axial displacement of the blades 3.
  • FIGS. 4a and 4b show in perspective views of pawn 17 and the figure 5 shows in perspective the downstream face 13 of the upstream flange 12.
  • the pins 17 are obviously mounted on the upstream flange 12 before mounting the latter on the disc 2.
  • the reference 20 designates a hole in the upstream flange 12 and for fixing the latter on flanges of the disc 2 by means quote. The tightening of these screws exerts on the heads 18 of the pins 17, a compressive force sufficient to prevent any subsequent axial displacement of the blades 3, as a function of the difference between the thicknesses of the heads 18 at rest and the mounting clearance J d 'origin. This compressive force may vary from one blade to another depending on the manufacturing tolerances of blades 3 and pins 17.

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 (4)

  1. Gebläserotor eines Turbostrahltriebwerks, umfassend eine Scheibe (2), deren Felge eine Vielzahl von im wesentlichen axialen und winkelmäßig gleichmäßig verteilten Nuten (5) aufweist, eine Vielzahl von lösbaren Schaufeln (3), die sich am Umfang der Scheibe (2) radial nach außen erstrecken, wobei jede Schaufel (3) einen in einer Nut (5) aufgenommenen Schaufelfuß (4) aufweist, einen mit der Scheibe (2) fest verbundenen stromabwärtigen Flansch sowie einen mit der Scheibe (2) fest verbundenen, lösbaren stromaufwärtigen Flansch (12), der dazu bestimmt ist, die Schaufelfüße (4) in den Nuten (5) zu halten, dadurch gekennzeichnet, daß der stromabwärtige Flansch, an dem die stromabwärtigen Seiten der Schaufelfüße in Anschlag sind, an der Scheibe (2) befestigt ist und der stromaufwärtige Flansch (12) vor der Montage an seiner stromabwärtigen Seite (13) Federmittel (17) trägt, die dazu bestimmt sind, nach der Montage auf die stromaufwärtigen Seiten der Schaufelfüße Kräfte auszuüben, die groß genug sind, um jegliche axiale Bewegung der Schaufeln (3) während des normalen Betriebs des Turbostrahltriebwerks zu verhindern.
  2. Gebläserotor nach Anspruch 1, dadurch gekennzeichnet, daß für jeden Schaufelfuß (4) eigene Federmittel (17) vorgesehen sind.
  3. Gebläserotor nach Anspruch 2, dadurch gekennzeichnet, daß die jedem Schaufelfuß (4) eigenen Federmittel von einem Elastomerstift (17) gebildet sind, der in einer im stromaufwärtigen Flansch (12) ausgebildeten Öffnung (15) gehalten ist.
  4. Gebläserotor nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß er ferner einen zwischen jedem Schaufelfuß (4) und dem Grund der entsprechenden Nut (5) eingefügten Keil (6) umfaßt, wobei dieser Keil (6) einen radialen Ansatz (8) aufweist, der an der stromaufwärtigen Seite (9) des Schaufelfußes (4) in Anlage ist, und daß die Federmittel an den Ansätzen (8) in Anlage sind.
EP03292280A 2002-09-18 2003-09-16 Kontrolle der axialen Lage einer Verdichterschaufel Expired - Lifetime EP1400698B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0211539A FR2844562B1 (fr) 2002-09-18 2002-09-18 Maitrise de la position axiale d'une aube de rotor de soufflante
FR0211539 2002-09-18

Publications (2)

Publication Number Publication Date
EP1400698A1 EP1400698A1 (de) 2004-03-24
EP1400698B1 true EP1400698B1 (de) 2008-09-03

Family

ID=31897464

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03292280A Expired - Lifetime EP1400698B1 (de) 2002-09-18 2003-09-16 Kontrolle der axialen Lage einer Verdichterschaufel

Country Status (9)

Country Link
US (1) US6910866B2 (de)
EP (1) EP1400698B1 (de)
JP (1) JP4059827B2 (de)
CA (1) CA2440995C (de)
DE (1) DE60323309D1 (de)
ES (1) ES2314167T3 (de)
FR (1) FR2844562B1 (de)
RU (1) RU2315206C2 (de)
UA (1) UA79088C2 (de)

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2903154B1 (fr) * 2006-06-29 2011-10-28 Snecma Rotor de turbomachine et turbomachine comportant un tel rotor
FR2927998A1 (fr) * 2008-02-25 2009-08-28 Snecma Sa Machine de test d'un revetement pour pied d'aube.
FR2927997A1 (fr) * 2008-02-25 2009-08-28 Snecma Sa Procede pour tester un revetement de pied d'aube.
FR2929660B1 (fr) * 2008-04-07 2012-11-16 Snecma Dispositif anti-usure pour rotor de turbomachine, bouchon formant dispositif anti-usure et rotor de compresseur de moteur a turbine a gaz comportant un bouchon anti-usure
FR2931871B1 (fr) * 2008-05-29 2011-08-19 Snecma Rotor de soufflante pour une 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
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
FR2948725B1 (fr) * 2009-07-28 2012-10-05 Snecma Dispositif anti-usure d'un rotor de turbomachine
FR2964584B1 (fr) * 2010-09-10 2013-08-16 Snecma Dispositif et procede de frettage d'une piece anti-usure dans un trou localise dans un element de turboreacteur
RU2461717C1 (ru) * 2011-03-17 2012-09-20 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Устройство демпфирования колебаний широкохордных рабочих лопаток вентиляторов с большой конусностью втулки и вентилятор газотурбинного двигателя
GB201104994D0 (en) * 2011-03-25 2011-05-11 Rolls Royce Plc a rotor having an annulus filler
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
FR2986284B1 (fr) * 2012-01-31 2014-03-28 Snecma Procede de reparation de marques d’usure.
RU2494365C1 (ru) * 2012-03-27 2013-09-27 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Нагрузочное устройство для исследования торцевого демпфирования колебаний лопаток вентилятора газотурбинного двигателя на вибростенде
US9410439B2 (en) * 2012-09-14 2016-08-09 United Technologies Corporation CMC blade attachment shim relief
US11220920B2 (en) * 2014-04-07 2022-01-11 Safran Aircraft Engines Turbine engine rotor lock
FR3033359B1 (fr) * 2015-03-02 2017-04-07 Snecma Disque aubage monobloc comportant un moyeu ayant une face evidee a laquelle est rapporte un organe de comblement
FR3048448B1 (fr) * 2016-03-02 2018-03-30 Safran Aircraft Engines Bouchon d'etancheite pour tambour de compresseur basse pression, tambour de compresseur basse pression et turbomachine associes
CN109488390B (zh) * 2018-12-18 2021-10-01 中国航发沈阳发动机研究所 一种转子叶片连接组件及涡轮性能试验组件
FR3106615B1 (fr) * 2020-01-23 2021-12-31 Safran Aircraft Engines Ensemble pour turbomachine
FR3119646B1 (fr) * 2021-02-11 2024-03-01 Safran Aircraft Engines Rotor de turbomachine
FR3120813B1 (fr) 2021-03-16 2024-02-09 Safran Aircraft Engines Procédé de fabrication d’un disque de soufflante avec partie en fabrication additive

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
FR2502690B1 (fr) * 1981-03-27 1985-09-13 Snecma Dispositif de verrouillage d'aubes de soufflante et de fixation de capot avant d'un turboreacteur
US4523890A (en) * 1983-10-19 1985-06-18 General Motors Corporation End seal for turbine blade base
FR2561307B1 (fr) * 1984-03-14 1986-09-12 Snecma Dispositif de verrouillage d'aubes de soufflantes
GB2262139A (en) * 1991-12-04 1993-06-09 Rolls Royce Plc Fan blade retainer
US5259728A (en) * 1992-05-08 1993-11-09 General Electric Company Bladed disk assembly
US5282720A (en) * 1992-09-15 1994-02-01 General Electric Company Fan blade retainer
FR2715975B1 (fr) * 1994-02-10 1996-03-29 Snecma Rotor de turbomachine à rainures d'aube débouchantes axiales ou inclinées.
GB9412963D0 (en) * 1994-06-28 1994-09-28 Rolls Royce Plc Gas turbine engine fan blade assembly
FR2803623B1 (fr) * 2000-01-06 2002-03-01 Snecma Moteurs Agencement de retenue axiale d'aubes dans un disque

Also Published As

Publication number Publication date
FR2844562B1 (fr) 2004-10-29
US20040126240A1 (en) 2004-07-01
US6910866B2 (en) 2005-06-28
EP1400698A1 (de) 2004-03-24
UA79088C2 (uk) 2007-05-25
ES2314167T3 (es) 2009-03-16
JP2004263688A (ja) 2004-09-24
RU2315206C2 (ru) 2008-01-20
CA2440995C (fr) 2011-02-08
DE60323309D1 (de) 2008-10-16
FR2844562A1 (fr) 2004-03-19
RU2003128928A (ru) 2005-03-20
JP4059827B2 (ja) 2008-03-12
CA2440995A1 (fr) 2004-03-18

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