EP1617046A1 - Wellen- und Lageranordnung - Google Patents

Wellen- und Lageranordnung Download PDF

Info

Publication number
EP1617046A1
EP1617046A1 EP05105982A EP05105982A EP1617046A1 EP 1617046 A1 EP1617046 A1 EP 1617046A1 EP 05105982 A EP05105982 A EP 05105982A EP 05105982 A EP05105982 A EP 05105982A EP 1617046 A1 EP1617046 A1 EP 1617046A1
Authority
EP
European Patent Office
Prior art keywords
ring
shaft
bearing
tenons
teeth
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
EP05105982A
Other languages
English (en)
French (fr)
Other versions
EP1617046B1 (de
Inventor
Jean-Philippe Maffre
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
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 SAS filed Critical SNECMA SAS
Publication of EP1617046A1 publication Critical patent/EP1617046A1/de
Application granted granted Critical
Publication of EP1617046B1 publication Critical patent/EP1617046B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T403/00—Joints and connections
    • Y10T403/70—Interfitted members
    • Y10T403/7026—Longitudinally splined or fluted rod

Definitions

  • the present invention relates to an assembly comprising a shaft or a rotating shaft portion about its axis and a rolling bearing by which it is supported.
  • the present invention applies in particular to the mounting of a bearing for a turbine shaft a gas turbine engine.
  • FIG. 1 shows a partial view of a gas turbine engine 1.
  • the high pressure turbine rotor 2 is immediately downstream of the combustion chamber 3 and is rotated by the action of the gases which are derived from the blades 4 mounted on the disk 5 of the rotor 2.
  • the turbine disc 5 is integral with a pin 6, disposed downstream relative to the direction of the gas flow.
  • a bearing by which the rotating assembly is supported At the end of the pin 6 is mounted a bearing by which the rotating assembly is supported.
  • the rotor 2 is integral upstream of a drum 7 connected to the high pressure compressor, not shown, itself rotated by an upstream bearing.
  • This rotating assembly forming the high pressure body of the engine is supported by means of these two bearings either by the fixed structure of the engine in the case of a single-body engine or by another rotating assembly in the case of a double or triple body motor for independent low pressure or intermediate pressure stages.
  • the inner ring is secured to the shaft or journal by hooping. By this operation the ring is mounted with clamping on the shaft or trunnion.
  • the coupling can thus both withstand the rotational torques to which the ring is subjected during engine operation as axial forces.
  • the applicant has therefore set as a first objective a method of assembling a rolling bearing ring, the shaft on which it is mounted to overcome these disadvantages by providing the same mechanical characteristics as those proposed by a nut .
  • the applicant has also set as another objective the realization of a method of assembling a rolling bearing ring on a shaft, which is both easy to assemble and disassemble.
  • the invention solves this problem with an assembly of a rotary shaft and a rolling bearing, the bearing comprising a ring integral with the shaft and forming a raceway for the rolling members of the bearing, characterized in that the ring is immobilized in rotation on the shaft by a coupling consisting of a plurality of teeth on the shaft cooperating with tenons integral with the ring, the tenons being housed between said teeth, and in the axial direction by a transverse rod shaped of ring portion.
  • shaft designates a shaft, a shaft portion, a trunnion or more generally any part on which a rolling bearing is mounted.
  • the nut in the case of a bearing assembly at the end of the trunnion on the side of its free end, the nut, because of the assembly constraints, must be placed in abutment against the ring on its edge near the end free of the trunnion, can be arranged a clutch coupling on the opposite side relative to the free end.
  • the corresponding portion of the trunnion can thus be shortened.
  • the axial retaining means can be associated with the clutch coupling.
  • the coupling consists of a plurality of teeth, respectively tenons, spaced apart from each other along the circumference of the shaft.
  • the number of teeth and associated tenons, as well as the size thereof, are determined by the circumferential loads that the coupling is called to support during the operation of the engine.
  • it advantageously has the elements symmetrically around the axis of the shaft.
  • the rolling bearing can be any, ball, roller or other.
  • a bearing comprises at least two concentric rings: an inner ring and an outer ring, between which are arranged a plurality of rolling members, for example rollers, held apart from each other by a cage.
  • the rings each define a rolling track for the rolling members
  • the axial retention means is constituted by a rod reported transversely to the axis of the shaft.
  • the ring is in the form of a ring portion and is made of an elastic material. It takes a first form in radial extension and where it constitutes said axial retention between the shaft and the ring, and a radially retracted form where it allows the axial displacement of the ring relative to the shaft.
  • the rod in the retaining position, is arranged to be in contact with both a tooth and at least one tenon.
  • the shaft comprises a cylindrical portion forming an outer radial abutment of the free end of the tenon or tenons.
  • FIG. 2 shows a pin 16 or a turbine shaft connected to the turbine rotor, not shown, according to the invention.
  • Figure 6 partially shows a representation of the arrangement of Figure 2 perspective view.
  • the trunnion comprises a flange with bores 161 by which is bolted to 161 the turbine rotor.
  • the trunnion also comprises a straight cylinder 162 for mounting an inner rolling bearing ring 18.
  • the ring 18 comprises an inner cylindrical member 181 on the cylindrical portion 162 of the trunnion.
  • the track 182 comprises an outer bearing for the rolling members, here rollers, not shown, as well as the rest of the bearing.
  • the ring is extended, along the common axis of the ring and the shaft, by tenons 17.
  • These tenons 17 are clearly visible in Figure 3 which is a partial perspective view of the ring 18
  • Each tenon has an internal groove 171, facing the axis of the ring and transversely thereto. The tenons are distributed here over the entire ring 17 with a determined spacing corresponding to the width of the teeth described below.
  • the ring 18 is abutted by the surface 172, oriented transversely to the axis, against an axial abutment 167 formed on the cylindrical portion 162.
  • the surface 172 is clearly shown in Figure 4 showing the end of the trunnion in a view in perspective, in isolation.
  • Radial teeth 164 are disposed at the periphery thereof, being spaced apart from each other with a spacing corresponding to the width of the tenons 17.
  • the tenons 17 are placed between the teeth 164, the ring being supported by the face 172 against the face 167 forming a stop.
  • the ring 18 and the trunnion 16 thus form a dog clutch coupling. By this coupling the ring is firmly immobilized in rotation, even if the tightening of the ring on the shaft is weakened.
  • the teeth are aligned transversely to the axis of the shaft and provide a transverse groove 166, radially open, the opposite side to that of the faces 165.
  • the groove 166 is screwed to grooves 171 formed on the tenons 17.
  • a ring 19, transverse to the axis is housed in the continuity of the grooves 171, and forms said axial retaining means. Indeed, being housed in all the grooves 171, its height is sufficient to engage against all the teeth 164. As seen in Figure 2, it prevents any withdrawal movement of the ring towards the right on the figure.
  • Figure 7 shows an enlarged detail of Figure 6, the rod 19 in the locking position.
  • This ring has a rectangular section here. It extends on the circumference. It forms a ring with a missing portion. It is elastic, preferably metal, and can be retracted by appropriate means to be housed in the groove 166 of the pin. When it is in this last position, it does not interfere with the axial movement of the ring. The depth of the groove 166 is sufficient to accommodate the rod and retract completely relative to the tenons of the ring.
  • the free portion of the tenons 17 is engaged in a downstream axial groove formed between the cylindrical portion 163 and the surface of the cylindrical trunnion portion.
  • the pins 17 are in external radial support against the surface of this cylindrical portion 163. Since the assembly is capable of rotating at very high speeds of rotation, the radial support provided by the element 163 reduces the deformations and stresses due to centrifugal forces exerted on the tenons. This considerably increases the durability of the parts.
  • the rod When mounting the ring 18 on the trunnion 16, the rod is first fitted by sliding it behind the teeth 164, as shown in FIG. 5; it is elastic enough to be deformed. Then, by means of a suitable tool the ring is forced to retract into the groove 166. While holding the ring in this position, the ring is slid along the cylindrical portion 162, until the faces 172 of the ring abut against the surface 167. The engagement of the tenons between the teeth forming a dog clutch coupling. Then relaxes the ring which relaxes and is housed in the grooves 171, axially locking the ring 18.
  • annular notch 20 through which one can extract the ring by means of a suitable tool. It is also observed that it is easy to introduce a tool between the teeth 164 to retract the rod 19.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Rolling Contact Bearings (AREA)
  • Mounting Of Bearings Or Others (AREA)
EP05105982A 2004-07-15 2005-06-30 Wellen- und Lageranordnung Active EP1617046B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0407854A FR2873161B1 (fr) 2004-07-15 2004-07-15 Ensemble comprenant un arbre rotatif et un palier a roulement

Publications (2)

Publication Number Publication Date
EP1617046A1 true EP1617046A1 (de) 2006-01-18
EP1617046B1 EP1617046B1 (de) 2007-01-24

Family

ID=34940264

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05105982A Active EP1617046B1 (de) 2004-07-15 2005-06-30 Wellen- und Lageranordnung

Country Status (5)

Country Link
US (1) US7775723B2 (de)
EP (1) EP1617046B1 (de)
DE (1) DE602005000494T2 (de)
ES (1) ES2281056T3 (de)
FR (1) FR2873161B1 (de)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0524929D0 (en) * 2005-12-06 2006-01-18 Rolls Royce Plc Retention arrangement
FR2917783B1 (fr) * 2007-06-25 2013-04-12 Snecma Systeme de liaison d'arbre moteur avec ecrou auto-extracteur
FR2931874B1 (fr) * 2008-05-29 2010-06-25 Snecma Dispositif de blocage axial d'un palier de guidage d'arbre dans une turbomachine.
US8840375B2 (en) * 2011-03-21 2014-09-23 United Technologies Corporation Component lock for a gas turbine engine
US10323519B2 (en) * 2016-06-23 2019-06-18 United Technologies Corporation Gas turbine engine having a turbine rotor with torque transfer and balance features
US10669877B2 (en) 2017-12-21 2020-06-02 United Technologies Corporation Air seal attachment
FR3105981B1 (fr) 2020-01-08 2023-01-06 Safran Aircraft Engines Jonc d’assemblage pour turbomachine
US11480071B2 (en) * 2020-06-02 2022-10-25 Pratt & Whitney Canada Corp. Balancing ring geometry

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3393533A (en) * 1965-07-19 1968-07-23 Rolls Royce Rotatable shafting
FR2629537A1 (fr) * 1988-03-30 1989-10-06 Snecma Palier inter-arbres de turbomachine multi-corps muni d'un dispositif de pilotage de jeu
EP0359659A1 (de) * 1988-09-14 1990-03-21 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Wellenkupplung in einer Lagerstütze einer Turbomaschine und Verfahren zur Entkupplung
US5863137A (en) * 1997-02-07 1999-01-26 Emerson Power Transmission Corp. Shaft locking device for bearing assemblies

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2439161A (en) * 1946-10-09 1948-04-06 Wright Aeronautical Corp Attaching means
US2553220A (en) * 1948-05-25 1951-05-15 Bendix Aviat Corp Quick detachable means
US2785550A (en) * 1952-07-25 1957-03-19 Rolls Royce Rotary drive-transmitting coupling arrangements
US2890900A (en) * 1955-06-27 1959-06-16 Goodall Rubber Co Hose coupling having longitudinal locking means
US2913261A (en) * 1957-07-16 1959-11-17 Perlman William Tube couplings
DE1400287A1 (de) * 1961-11-14 1968-10-24 Elektro Und Feinmechanik Aache Geteiltes Maschinenelement aus gepressten Sinterwerkstoffen
US3616958A (en) * 1969-04-16 1971-11-02 Orson L Mitchell Separable pressure tank apparatus
US3571886A (en) * 1969-05-27 1971-03-23 Gen Electric Attachment device and cooperating tool means
US3637238A (en) * 1970-01-15 1972-01-25 Gottlieb W Grosch Drill pipe couplings
US3631735A (en) * 1970-07-02 1972-01-04 Gen Electric Gas turbine engine gearboxes
BE789470A (fr) * 1971-09-30 1973-01-15 Gen Electric Dispositif de fixation et outil pour celui-ci
US3750489A (en) * 1972-06-07 1973-08-07 Caterpillar Tractor Co Composite drive assembly
US3900270A (en) * 1973-09-22 1975-08-19 Rolls Royce 1971 Ltd Shaft couplings
US4290515A (en) * 1978-08-15 1981-09-22 Eaton Corporation Transmission with resilient shifting mechanism
US4653984A (en) * 1985-05-01 1987-03-31 United Technologies Corporation Turbine module assembly device
US4687084A (en) * 1985-07-22 1987-08-18 Automotive Products Plc Clutch release apparatus for pull type clutches
US5236302A (en) * 1991-10-30 1993-08-17 General Electric Company Turbine disk interstage seal system
US5320488A (en) * 1993-01-21 1994-06-14 General Electric Company Turbine disk interstage seal anti-rotation system
US5685650A (en) * 1996-01-16 1997-11-11 Allen-Bradley Company, Inc. Bearing assembly utilizing improved clamping arrangement
DE19751855C1 (de) * 1997-11-22 1999-04-29 Gkn Automotive Ag Verbindungsanordnung an einer Gelenkwelle
GB9925261D0 (en) * 1999-10-27 1999-12-29 Rolls Royce Plc Locking devices

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3393533A (en) * 1965-07-19 1968-07-23 Rolls Royce Rotatable shafting
FR2629537A1 (fr) * 1988-03-30 1989-10-06 Snecma Palier inter-arbres de turbomachine multi-corps muni d'un dispositif de pilotage de jeu
EP0359659A1 (de) * 1988-09-14 1990-03-21 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Wellenkupplung in einer Lagerstütze einer Turbomaschine und Verfahren zur Entkupplung
US5863137A (en) * 1997-02-07 1999-01-26 Emerson Power Transmission Corp. Shaft locking device for bearing assemblies

Also Published As

Publication number Publication date
FR2873161B1 (fr) 2008-10-10
FR2873161A1 (fr) 2006-01-20
US7775723B2 (en) 2010-08-17
ES2281056T3 (es) 2007-09-16
DE602005000494D1 (de) 2007-03-15
EP1617046B1 (de) 2007-01-24
US20060291955A1 (en) 2006-12-28
DE602005000494T2 (de) 2007-10-31

Similar Documents

Publication Publication Date Title
EP1617046B1 (de) Wellen- und Lageranordnung
EP1561907B1 (de) Turbostrahltriebwerk mit doppeltgelagerter Gebläseantriebswelle
EP1717415B1 (de) Turbinenmodul für einen Gasturbinentriebwerk
CA2518355C (fr) Retenue des clavettes de centrage des anneaux sous aubes de stator a calage variable d'un moteur a turbine a gaz
EP0063993B1 (de) Lageranordnung, insbesondere für Turbomaschinen
EP1564352B1 (de) Lagerungsvorrichtung mit zwei Lagern für die Bläserwelle eines Turbostrahltriebwerks
EP2529083B1 (de) Vorrichtung zur blockierung eines dichtungsrings auf einem turbinenrad
EP1605139B1 (de) Turbomaschine mit axialer Rückhalteeinrichtung für den Rotor
EP1598524B1 (de) Verfahren der Montage beschaufelter Rotorscheiben und Dämpfungsvorrichung dieser Schaufeln
EP1712806B1 (de) Montageanordnung zwischen einem Lagerinnenring und einem Zapfen, zur Anordnung geeigneter Lagerinnenring und Zapfen, und eine mit diesem ausgerüstete Turbomaschine
FR2896827A1 (fr) Assemblage a encombrement radial reduit entre un arbre de turbine et un tourillon d'arbre de compresseur de turbomachine
EP3256698B1 (de) Mutter zur axialen arretierung eines lagerrings in einer turbomaschine
FR3017163A1 (fr) Dispositif pour une helice non carenee a pales a calage variable d'une turbomachine
CA2641017A1 (fr) Perfectionnement a un anneau de commande de calage des aubes fixes d'une turbomachine
FR2856440A1 (fr) Compresseur de turbomachine et roue dudit compresseur
FR2968363A1 (fr) Rotor de turbomachine avec une cale anti-usure entre un disque et un anneau
FR2948725A1 (fr) Dispositif anti-usure d'un rotor de turbomachine
EP2071141B1 (de) Dichte Befestigung eines Lagerträgers in einem Turbotriebwerk
FR3009740A1 (fr) Amelioration pour le verrouillage de pieces de support d'aubage
FR2949138A1 (fr) Turbomachine comportant des moyens d'anti-rotation d'un ecrou de palier
FR3011585A1 (fr) Assemblage pour turbomachine d'aeronef comprenant une bague frettee de maintien axial d'un joint a brosse
EP3931427B1 (de) Anordnung für eine turbine einer turbomaschine
EP3935273B1 (de) Gegenläufige gasturbine für ein flugzeug
FR3105981A1 (fr) Jonc d’assemblage pour turbomachine
FR3068741A1 (fr) Arbre d’entrainement pour une turbomachine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20050701

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR LV MK YU

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

AKX Designation fees paid

Designated state(s): DE ES FR GB IT SE

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE ES FR GB IT SE

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 602005000494

Country of ref document: DE

Date of ref document: 20070315

Kind code of ref document: P

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20070504

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2281056

Country of ref document: ES

Kind code of ref document: T3

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20071025

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 11

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 12

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 13

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES

Effective date: 20170713

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: ES

Payment date: 20230703

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20240521

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240521

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20240522

Year of fee payment: 20

Ref country code: FR

Payment date: 20240521

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 20240521

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: ES

Payment date: 20240701

Year of fee payment: 20