EP1498579A1 - Halterung eines Lagerschildes am Rotor - Google Patents

Halterung eines Lagerschildes am Rotor Download PDF

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Publication number
EP1498579A1
EP1498579A1 EP20040291803 EP04291803A EP1498579A1 EP 1498579 A1 EP1498579 A1 EP 1498579A1 EP 20040291803 EP20040291803 EP 20040291803 EP 04291803 A EP04291803 A EP 04291803A EP 1498579 A1 EP1498579 A1 EP 1498579A1
Authority
EP
European Patent Office
Prior art keywords
flange
diameter
foot
rod
recess
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
EP20040291803
Other languages
English (en)
French (fr)
Other versions
EP1498579B1 (de
Inventor
Kamel Benderradji
Marc Marchi
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 EP1498579A1 publication Critical patent/EP1498579A1/de
Application granted granted Critical
Publication of EP1498579B1 publication Critical patent/EP1498579B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • 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
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity

Definitions

  • the invention relates to a device for retaining a flange annular against a radial face of a disk and rotor.
  • a device for retaining a annular flange against a radial face of a rotor disc said disc having in said radial face an annular recess delimited by several walls, one of which is formed by the inner face of a flange which extends radially outwards, and said flange having, in its radially inner part, an annular base bearing against the wall radially outside the recess and a foot that extends radially inwards in the recess from the base, said device having a split annular retaining ring disposed in the recess, this ring having a first radial surface abutting against the inner face of the flange, a second radial surface abutting against the axially outer face of the foot and a peripheral surface in stop against said foot or said base.
  • the flange is intended to prevent the Axial displacement of fir-type vane blades whose feet are mounted in axial notches provided on the periphery of the disc of rotor.
  • To mount the flange we first have the annular ring split in the recess of the disc, and then compressed radially towards inside the recess by means of tools pressing on the wall ring device until these tools come to press the flange of the disc. Then, slide the base of the flange along the radially outer wall of the recess.
  • the ring has at its axially inner end a rabbet device in which the radially inner portion of the foot.
  • the outer diameter of the ring is smaller than the inner diameter the base of the flange to allow the release of the tools of compression during assembly and their introduction during disassembly possible.
  • the diameter of the bore of the flange foot is greater than diameter of the flange to allow the introduction of the inner portion of the flange in the recess around the compression tools in support against the periphery of the flange.
  • the flange being subjected to axial stresses during shocks on blades because of the ingestion of debris, which is taken up by the retaining ring there are shear moments on the ring because of the differences in diameter between the bore of the foot and the flange.
  • the manufacture of this ring requires expensive machining.
  • the retaining ring remains in the recess when dismounting the flange for repair or replacement of a dawn for example.
  • This ring is thus different from a circlip traditional that is expanded by means of a piece for its implementation around a tree and retracts elastically into a throat arranged on the periphery of the tree.
  • the object of the invention is to propose a retention system axial axis of a rotor disc flange that is simple to perform and little expensive and which makes it easier to assemble the parts.
  • the invention achieves its goal by the fact that the ring is formed by a rod interposed axially between the foot of the flange and the flange, and whose peripheral surface abuts against the base, said peripheral surface and said flange comprising in correspondence notches opening outwards and intended to receive tools for compression of said ring which retract into the contour of the flange when mounting or dismounting said flange.
  • This groove preferably has a U-shaped section and the rod has opposite planar radial faces.
  • the axial width of the groove is equal to or slightly greater than the thickness of the ring.
  • the foot of the flange has a bore whose diameter is substantially equal to the diameter of the flange.
  • the terms “inside” and “outside” designate a wall or a surface respectively near or far from the axis of rotation of the disk
  • the terms “internal” and “external” refer to a wall or a surface respectively close to or distant from the plane median of the disc 1.
  • the annular recess 7 is delimited radially on the outside by a substantially cylindrical wall 9 connected by a surface concave 10a an annular groove 12, of U-section, arranged behind a flange 13 which extends radially outwards and whose diameter is slightly greater than the diameter of the shoulder 14 formed by the concave surface 10 and the inner axial face of the groove 12.
  • the radially inner portion 6 of the flange 5 has a base 15 which extends into the recess 7 and which has a surface cylindrical peripheral 15a which bears against the cylindrical wall 9, and a foot 16 disposed under the base 15 and which extends radially towards inside.
  • the diameter of the bore 17 of the foot 16 is substantially equal or slightly greater than the diameter of the flange 13, in order to allow introducing the radially inner portion 6 of the flange 5 into the recess 7 during assembly, or its extraction for the needs of repair or maintenance of the blades 3.
  • the outer face 18 of the foot 16 is disposed in a radial plane passing through the groove 12 in the vicinity of the shoulder 14. This face 18 is connected to the radially inner face of the base 15, and forms with the latter a rabbet 19.
  • the ring 8 has two parallel axial faces perpendicular to the axis of rotation of the disc 1, namely an axial face external 20 bearing against the inner face of the flange 13 and a face internal axial 21 bearing against the outer face 18 of the foot 16 and its peripheral surface 22 bears against the radially inner face from the base 15.
  • the depth of the groove 7 is calculated to allow the retraction of the claws 25, during the compression of the rod 8.
  • the inner diameter of the rod 8, not subject to constraints, is preferably smaller than the diameter of the shoulder 14, so that the 8 is correctly positioned with respect to the groove when setting in place of the claws 25 in the notches 30b of the ring 8.
  • the rod 8 which is in the form of a split washer, is easy to manufacture and inexpensive.
  • the volume of the recess 7 can be limited to the maximum, which reinforces the periphery of the disc 1 which, in general, is subject to considerable centrifugal forces.

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)
  • Rotary Pumps (AREA)
  • Snaps, Bayonet Connections, Set Pins, And Snap Rings (AREA)
EP04291803.7A 2003-07-17 2004-07-15 Rotorscheibe mit einem ringförmigen Flansch Active EP1498579B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0308713 2003-07-17
FR0308713A FR2857691B1 (fr) 2003-07-17 2003-07-17 Retention de flasque de rotor

Publications (2)

Publication Number Publication Date
EP1498579A1 true EP1498579A1 (de) 2005-01-19
EP1498579B1 EP1498579B1 (de) 2015-12-02

Family

ID=33462547

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04291803.7A Active EP1498579B1 (de) 2003-07-17 2004-07-15 Rotorscheibe mit einem ringförmigen Flansch

Country Status (7)

Country Link
US (1) US7217100B2 (de)
EP (1) EP1498579B1 (de)
JP (1) JP4181528B2 (de)
CA (1) CA2475043C (de)
FR (1) FR2857691B1 (de)
RU (1) RU2340799C2 (de)
UA (1) UA82660C2 (de)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2899636A1 (fr) * 2006-04-10 2007-10-12 Snecma Sa Dispositif de retention axiale d'un flasque de disque de rotor de turbomachine
EP1956194A1 (de) * 2007-02-06 2008-08-13 Siemens Aktiengesellschaft Turbinenanordnung mit einem Sicherungselement sowie Verfahren zur Sicherung einer Deckplatte
EP2009244A1 (de) 2007-06-27 2008-12-31 Snecma Axiale Haltevorrichtung für Laufradschaufeln, die auf einer Rotorscheibe einer Strömungsmaschine montiert sind
WO2010049196A1 (de) * 2008-10-30 2010-05-06 Siemens Aktiengesellschaft Gasturbine mit dichtplatten an der turbinenscheibe
FR2939834A1 (fr) * 2008-12-17 2010-06-18 Turbomeca Roue de turbine avec systeme de retention axiale des aubes
EP2514923A1 (de) * 2011-04-18 2012-10-24 MTU Aero Engines GmbH Blendeneinrichtung, integral beschaufelter Rotorgrundkörper, Verfahren und Strömungsmaschine
WO2014137435A3 (en) * 2013-03-05 2014-11-13 Rolls-Royce North American Technologies, Inc. Turbine segmented cover plate retention method
GB2518945A (en) * 2013-07-30 2015-04-08 Snecma A device for guiding variable pitch diffuser vanes of a turbine engine
FR3026430A1 (fr) * 2014-09-29 2016-04-01 Snecma Roue de turbine dans une turbomachine
FR3091719A1 (fr) * 2019-01-15 2020-07-17 Safran Aircraft Engines secteur de flasque d’etancheite de disque de rotor
FR3108669A1 (fr) * 2020-03-25 2021-10-01 Safran Aircraft Engines Roue à aubes d’une turbine d’un aéronef, turbine comportant une telle roue à aubes et procede de montage d’une telle roue à aubes

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0505186D0 (en) * 2005-03-14 2005-04-20 Cross Mfg 1938 Company Ltd Improvements to a retaining ring
FR2893093B1 (fr) * 2005-11-08 2008-02-08 Snecma Sa Montage d'un anneau composite sur un disque de rotor d'une turbomachine.
US8643244B2 (en) 2011-07-25 2014-02-04 Hamilton Sundstrand Corporation Strength cast rotor for an induction motor
FR2982635B1 (fr) * 2011-11-15 2013-11-15 Snecma Roue a aubes pour une turbomachine
RU2493371C1 (ru) * 2012-05-11 2013-09-20 Открытое акционерное общество "Авиадвигатель" Ротор турбины турбореактивного двигателя
US9228443B2 (en) * 2012-10-31 2016-01-05 Solar Turbines Incorporated Turbine rotor assembly
US9453422B2 (en) * 2013-03-08 2016-09-27 General Electric Company Device, system and method for preventing leakage in a turbine
FR3020408B1 (fr) * 2014-04-24 2018-04-06 Safran Aircraft Engines Ensemble rotatif pour turbomachine
US10215037B2 (en) * 2016-05-13 2019-02-26 United Technologies Corporation Contoured retaining ring
US10502061B2 (en) 2016-09-28 2019-12-10 Pratt & Whitney Canada Corp. Damper groove with strain derivative amplifying pockets
FR3092609B1 (fr) * 2019-02-12 2021-02-12 Safran Aircraft Engines Ensemble de turbine pour turbomachine d’aeronef a circuit de refroidissement de disque ameliore
US11525464B2 (en) 2021-03-23 2022-12-13 Pratt & Whitney Canada Corp. Rotor with centrifugally wedged damper
US11391157B1 (en) 2021-03-23 2022-07-19 Pratt & Whitney Canada Corp. Damped rotor assembly

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4304523A (en) * 1980-06-23 1981-12-08 General Electric Company Means and method for securing a member to a structure
US4349318A (en) * 1980-01-04 1982-09-14 Avco Corporation Boltless blade retainer for a turbine wheel
US5622475A (en) * 1994-08-30 1997-04-22 General Electric Company Double rabbet rotor blade retention assembly
EP0921272A2 (de) * 1997-12-03 1999-06-09 Rolls-Royce Plc Turbinenrotorscheibenanordnung
FR2812906A1 (fr) * 2000-08-10 2002-02-15 Snecma Moteurs Bague de retention axiale d'un flasque sur un disque

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4349318A (en) * 1980-01-04 1982-09-14 Avco Corporation Boltless blade retainer for a turbine wheel
US4304523A (en) * 1980-06-23 1981-12-08 General Electric Company Means and method for securing a member to a structure
US5622475A (en) * 1994-08-30 1997-04-22 General Electric Company Double rabbet rotor blade retention assembly
EP0921272A2 (de) * 1997-12-03 1999-06-09 Rolls-Royce Plc Turbinenrotorscheibenanordnung
FR2812906A1 (fr) * 2000-08-10 2002-02-15 Snecma Moteurs Bague de retention axiale d'un flasque sur un disque

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1845235A1 (de) 2006-04-10 2007-10-17 Snecma Axiale Haltevorrichtung für eine Schaufeldeckplatte einer Turbinenscheibe
FR2899636A1 (fr) * 2006-04-10 2007-10-12 Snecma Sa Dispositif de retention axiale d'un flasque de disque de rotor de turbomachine
US7857593B2 (en) 2006-04-10 2010-12-28 Snecma Retaining device for axially retaining a rotor disk flange in a turbomachine
EP1956194A1 (de) * 2007-02-06 2008-08-13 Siemens Aktiengesellschaft Turbinenanordnung mit einem Sicherungselement sowie Verfahren zur Sicherung einer Deckplatte
US8348620B2 (en) 2007-06-27 2013-01-08 Snecma Device for axially retaining blades mounted on a turbomachine rotor disk
EP2009244A1 (de) 2007-06-27 2008-12-31 Snecma Axiale Haltevorrichtung für Laufradschaufeln, die auf einer Rotorscheibe einer Strömungsmaschine montiert sind
FR2918106A1 (fr) * 2007-06-27 2009-01-02 Snecma Sa Dispositif de retenue axiale d'aubes montees sur un disque de rotor de turbomachine.
WO2010049196A1 (de) * 2008-10-30 2010-05-06 Siemens Aktiengesellschaft Gasturbine mit dichtplatten an der turbinenscheibe
CN102203389B (zh) * 2008-10-30 2014-03-05 西门子公司 具有设置在涡轮叶轮盘上的密封板的燃气涡轮机
CN102203389A (zh) * 2008-10-30 2011-09-28 西门子公司 具有设置在涡轮叶轮盘上的密封板的燃气涡轮机
US8573943B2 (en) 2008-10-30 2013-11-05 Siemens Aktiengesellschaft Gas turbine having sealing plates on the turbine disc
FR2939834A1 (fr) * 2008-12-17 2010-06-18 Turbomeca Roue de turbine avec systeme de retention axiale des aubes
WO2010076493A1 (fr) * 2008-12-17 2010-07-08 Turbomeca Roue de turbine avec système de rétention axiale des aubes
US8721293B2 (en) 2008-12-17 2014-05-13 Turbomeca Turbine wheel with an axial retention system for vanes
EP2514923A1 (de) * 2011-04-18 2012-10-24 MTU Aero Engines GmbH Blendeneinrichtung, integral beschaufelter Rotorgrundkörper, Verfahren und Strömungsmaschine
WO2014137435A3 (en) * 2013-03-05 2014-11-13 Rolls-Royce North American Technologies, Inc. Turbine segmented cover plate retention method
US9803485B2 (en) 2013-03-05 2017-10-31 Rolls-Royce North American Technologies, Inc. Turbine segmented cover plate retention method
GB2518945A (en) * 2013-07-30 2015-04-08 Snecma A device for guiding variable pitch diffuser vanes of a turbine engine
GB2518945B (en) * 2013-07-30 2020-04-08 Snecma A device for guiding variable pitch diffuser vanes of a turbine engine
FR3026430A1 (fr) * 2014-09-29 2016-04-01 Snecma Roue de turbine dans une turbomachine
US9890652B2 (en) 2014-09-29 2018-02-13 Snecma Turbine wheel for a turbine engine
FR3091719A1 (fr) * 2019-01-15 2020-07-17 Safran Aircraft Engines secteur de flasque d’etancheite de disque de rotor
US11365643B2 (en) 2019-01-15 2022-06-21 Safran Aircraft Engines Rotor disc sealing flange sector
FR3108669A1 (fr) * 2020-03-25 2021-10-01 Safran Aircraft Engines Roue à aubes d’une turbine d’un aéronef, turbine comportant une telle roue à aubes et procede de montage d’une telle roue à aubes

Also Published As

Publication number Publication date
US7217100B2 (en) 2007-05-15
FR2857691A1 (fr) 2005-01-21
CA2475043C (fr) 2011-09-27
FR2857691B1 (fr) 2006-02-03
CA2475043A1 (fr) 2005-01-17
JP2005036811A (ja) 2005-02-10
JP4181528B2 (ja) 2008-11-19
EP1498579B1 (de) 2015-12-02
RU2340799C2 (ru) 2008-12-10
UA82660C2 (uk) 2008-05-12
RU2004122000A (ru) 2006-01-27
US20050042108A1 (en) 2005-02-24

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