EP1400698A1 - Kontrolle der axialen Lage einer Verdichterschaufel - Google Patents

Kontrolle der axialen Lage einer Verdichterschaufel Download PDF

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Publication number
EP1400698A1
EP1400698A1 EP03292280A EP03292280A EP1400698A1 EP 1400698 A1 EP1400698 A1 EP 1400698A1 EP 03292280 A EP03292280 A EP 03292280A EP 03292280 A EP03292280 A EP 03292280A EP 1400698 A1 EP1400698 A1 EP 1400698A1
Authority
EP
European Patent Office
Prior art keywords
blade
upstream
disk
blades
flange
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
EP03292280A
Other languages
English (en)
French (fr)
Other versions
EP1400698B1 (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 Moteurs 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.)
Filing date
Publication date
Application filed by SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
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 control system of the position axial of the removable vanes of a blower of the turbojet engine.
  • a fan rotor having a disk whose rim has a plurality of grooves substantially axial and regularly distributed angularly, a pluralities of removable vanes that extend radially outward to the periphery of said disk, each blade having a dawn foot housing in a groove, a flange downstream secured to said disk and against which the downstream faces of the blade roots are in abutment, and an upstream flange removable integral with said disk and for retaining the blade roots in the grooves.
  • the upstream face refers to the directed face towards the front of the engine and the downstream face designates that directed towards the rear.
  • the upstream flange of a fan rotor is generally removable to allow the replacement of a blade in case of damage. This can happen if foreign bodies are swallowed, such as particularly during the take-off and approach phases of the aircraft equipped with turbojets.
  • US 4,033,705 discloses an axial retention system of vanes which has at each end of a blade root a tenon which cooperates with two oblique mortises formed in the rim of the disc of part and else of the groove receiving this foot of dawn.
  • the studs provided on each disc face are retained radially by a ring secured to the disc.
  • This document provides between each end face of the foot dawn and adjacent tenon a sheet forming spring whose role is to immobilize the tenon radially when assembling the blades, before the setting up and fixing the retaining ring. These springs create a mounting game at each end of dawn as this is shown on Figure 7 of this document, which is not controlled.
  • US 5,282,720 provides for interposing between the retaining flanges and the ends of the blade roots, honeycomb elements intended for to absorb some of the energy if you eat birds. During ingestion, the honeycomb is gradually deformed and thus dissipates a part of the energy. Honeycomb elements must retain their integrity when mounting the flanges, so there is inevitably a axial clearance after assembly, and random axial displacement is possible in operation of the blower.
  • the object of the invention is to propose a fan rotor such described in the introduction in which the axial position of the blades is controlled by a simple and inexpensive device, without creating a problem for the assembly and disassembly of the blades in case of repair possible.
  • the flange upstream is equipped on its downstream face with elastic means intended to on the upstream faces of the blade roots, after assembly, sufficient efforts to prevent axial displacement of the blades during operation normal engine.
  • the fan rotor further comprises a shim interposed between each blade root and the bottom of the groove corresponding, this wedge comprising a radial heel bearing against the upstream face of said blade root, the elastic means are advantageously bearing against said heels.
  • Figure 1 shows an X-axis fan rotor 1 which has a disc 2 and a plurality of blades 3 regularly spaced angularly around the X axis which extend radially outwards at the periphery of the disc 2.
  • Each of the blades 3 has a foot blade 4 which is retained in a groove or cell 5 substantially axial formed in the rim of the disk 2.
  • the blade roots 4 have a shape in dovetail, 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 disc 2, a heel 8 which bears against the upstream face 9 of the foot 4 of the dawn 3.
  • the role of the hold 6 is to prevent the dawn 3 from falling into the groove 5, when stopping the blower and cash a portion of the energy during 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, no shown in the drawings, against which the feet 4 of the blades 3 are in stop.
  • An upstream flange 12 is also provided on the upstream face 7 of the disk 2, whose role is to prevent the feet 4 of the blades 3 of to escape from the grooves 5 by sliding after mounting the rotor 1.
  • This upstream flange 12 is fixed on flanges of the disc 2 by screws, so that to allow its dismantling, in case of need of replacement of a dawn 3.
  • the upstream flange 12 has in front of each dawn foot 4 an orifice 15 which holds the drum 16 of a pin 17 in elastomer, this pin 17 having a head 18 of larger diameter 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 hold 6.
  • the pin 17 thus exerts elastic forces on the heel 8 in an axial direction.
  • the heel 8 is in support against the dawn foot 4 adjacent, it is permanently urged to the downstream flange, against which he is in abutment.
  • This simple arrangement allows you to control the axial play of the blades 3 and to prevent random axial displacement of the blades 3.
  • FIG. 4a and 4b show in perspective views of the pawn 17 and FIG. 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 it on disk 2.
  • Reference 20 designates an orifice formed in the upstream flange 12 and serving for fixing this last on flanges of disc 2 by means of screws. The tightening of these screws exerts on the heads 18 of the pins 17, a sufficient compressive force to prevent further axial displacement of the blades 3, depending the difference between the thicknesses of the heads 18 at rest and the mounting clearance J of origin. This compression effort may vary from one blade to another according to 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)
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 true EP1400698A1 (de) 2004-03-24
EP1400698B1 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)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2903154A1 (fr) * 2006-06-29 2008-01-04 Snecma Sa Rotor de turbomachine et turbomachine comportant un tel rotor
FR2929660A1 (fr) * 2008-04-07 2009-10-09 Snecma Sa 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
WO2009144401A1 (fr) * 2008-05-29 2009-12-03 Snecma Rotor de soufflante pour une turbomachine
FR2948725A1 (fr) * 2009-07-28 2011-02-04 Snecma Dispositif anti-usure d'un rotor de turbomachine
FR2964584A1 (fr) * 2010-09-10 2012-03-16 Snecma Dispositif et procede de frettage d'une piece anti-usure dans un trou localise dans un element de turboreacteur
FR3048448A1 (fr) * 2016-03-02 2017-09-08 Snecma Bouchon d'etancheite pour tambour de compresseur basse pression, tambour de compresseur basse pression et turbomachine associes
FR3119646A1 (fr) * 2021-02-11 2022-08-12 Safran Aircraft Engines Rotor de turbomachine
WO2022195207A1 (fr) 2021-03-16 2022-09-22 Safran Aircraft Engines Procédé de fabrication d'un disque de soufflante avec partie en fabrication additive

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2927997A1 (fr) * 2008-02-25 2009-08-28 Snecma Sa Procede pour tester un revetement de pied d'aube.
FR2927998A1 (fr) * 2008-02-25 2009-08-28 Snecma Sa Machine de test d'un revetement pour pied d'aube.
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
US8616849B2 (en) * 2009-02-18 2013-12-31 Pratt & Whitney Canada Corp. Fan blade platform
US8568102B2 (en) * 2009-02-18 2013-10-29 Pratt & Whitney Canada Corp. Fan blade anti-fretting insert
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
EP3129597B1 (de) * 2014-04-07 2018-10-24 Safran Aircraft Engines Keil eines rotors einer strömungsmaschine
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
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

Citations (5)

* 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
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
EP0690203A2 (de) * 1994-06-28 1996-01-03 ROLLS-ROYCE plc Befestigungssystem für die Bläserschaufeln bei einem Gasturbinentriebwerk

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
FR2715975B1 (fr) * 1994-02-10 1996-03-29 Snecma Rotor de turbomachine à rainures d'aube débouchantes axiales ou inclinées.
FR2803623B1 (fr) * 2000-01-06 2002-03-01 Snecma Moteurs Agencement de retenue axiale d'aubes dans un disque

Patent Citations (5)

* 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
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
EP0690203A2 (de) * 1994-06-28 1996-01-03 ROLLS-ROYCE plc Befestigungssystem für die Bläserschaufeln bei einem Gasturbinentriebwerk

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1873401A3 (de) * 2006-06-29 2017-04-12 Safran Aircraft Engines Strömungsmaschinenrotor und Strömungsmaschine, die einen solchen Rotor umfasst
RU2446287C2 (ru) * 2006-06-29 2012-03-27 Снекма Ротор турбинной установки и турбинная установка, содержащая такой ротор
FR2903154A1 (fr) * 2006-06-29 2008-01-04 Snecma Sa Rotor de turbomachine et turbomachine comportant un tel rotor
US8113785B2 (en) 2006-06-29 2012-02-14 Snecma Turbomachine rotor and turbomachine comprising such a rotor
WO2009124949A1 (fr) * 2008-04-07 2009-10-15 Carbone Lorraine Composants Rotor de turbomachine comportant un bouchon anti-usure, bouchon anti-usure
US8985961B2 (en) 2008-04-07 2015-03-24 Snecma Turbomachine rotor comprising an anti-wear plug, and anti-wear plug
FR2929660A1 (fr) * 2008-04-07 2009-10-09 Snecma Sa 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
WO2009144401A1 (fr) * 2008-05-29 2009-12-03 Snecma Rotor de soufflante pour une turbomachine
FR2931871A1 (fr) * 2008-05-29 2009-12-04 Snecma Rotor de soufflante pour une turbomachine.
US8740568B2 (en) 2008-05-29 2014-06-03 Snecma Turbomachine fan rotor
US8573944B2 (en) 2009-07-28 2013-11-05 Snecma Anti-wear device of a turbomachine rotor
FR2948725A1 (fr) * 2009-07-28 2011-02-04 Snecma Dispositif anti-usure d'un rotor de turbomachine
FR2964584A1 (fr) * 2010-09-10 2012-03-16 Snecma Dispositif et procede de frettage d'une piece anti-usure dans un trou localise dans un element de turboreacteur
FR3048448A1 (fr) * 2016-03-02 2017-09-08 Snecma Bouchon d'etancheite pour tambour de compresseur basse pression, tambour de compresseur basse pression et turbomachine associes
FR3119646A1 (fr) * 2021-02-11 2022-08-12 Safran Aircraft Engines Rotor de turbomachine
WO2022195207A1 (fr) 2021-03-16 2022-09-22 Safran Aircraft Engines Procédé de fabrication d'un disque de soufflante avec partie en fabrication additive
FR3120813A1 (fr) 2021-03-16 2022-09-23 Safran Aircraft Engines Procédé de fabrication d’un disque de soufflante avec partie en fabrication additive

Also Published As

Publication number Publication date
EP1400698B1 (de) 2008-09-03
US20040126240A1 (en) 2004-07-01
FR2844562A1 (fr) 2004-03-19
US6910866B2 (en) 2005-06-28
JP4059827B2 (ja) 2008-03-12
RU2315206C2 (ru) 2008-01-20
ES2314167T3 (es) 2009-03-16
RU2003128928A (ru) 2005-03-20
JP2004263688A (ja) 2004-09-24
UA79088C2 (uk) 2007-05-25
FR2844562B1 (fr) 2004-10-29
CA2440995C (fr) 2011-02-08
CA2440995A1 (fr) 2004-03-18
DE60323309D1 (de) 2008-10-16

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