EP0754838B1 - Auskuppelbare manuelle Rotordrehvorrichtung für eine Turbomaschine - Google Patents

Auskuppelbare manuelle Rotordrehvorrichtung für eine Turbomaschine Download PDF

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Publication number
EP0754838B1
EP0754838B1 EP96401418A EP96401418A EP0754838B1 EP 0754838 B1 EP0754838 B1 EP 0754838B1 EP 96401418 A EP96401418 A EP 96401418A EP 96401418 A EP96401418 A EP 96401418A EP 0754838 B1 EP0754838 B1 EP 0754838B1
Authority
EP
European Patent Office
Prior art keywords
shaft
casing
drive shaft
rotor
turbomachine
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
EP96401418A
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English (en)
French (fr)
Other versions
EP0754838A1 (de
Inventor
Patrice Mazzotta
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0754838A1 publication Critical patent/EP0754838A1/de
Application granted granted Critical
Publication of EP0754838B1 publication Critical patent/EP0754838B1/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/34—Turning or inching gear

Definitions

  • the invention relates to a turbomachine, and more particularly a way to manually train the rotor rotation for endoscopic control of the blades of this rotor.
  • Turbomachinery and in particular turboshaft engines for aircraft are subject to inspections and controls regular. Some inspections are done using endoscopes that are introduced inside the turbine engine by closable openings provided for this purpose and which allow examination without disassembly of non- visible from the outside.
  • an endoscope is introduced into the fluid vein by closable openings of the turbine engine housing, and successively each dawn in front of the endoscope by making turn the rotor step by step. This step-by-step rotation of the rotor is usually done by hand training an organ turning mechanically connected to the rotor.
  • This opening is usually closed by a cover that must be removed and then put back when the operation is finished. Sometimes it's a piece of equipment that needs to be removed to access the shaft transmitting the movement to this equipment.
  • the invention proposes to train a turbomachine shaft connected in rotation to the rotor, to the by means of a drive shaft passing through the wall of the casing surrounding the tree to be trained, the training tree and the tree to train being connected together by a disengageable coupling controlled by a declutching means automatic.
  • An at least static sealing means effective at least in the disengaged position, is arranged between the drive shaft and the housing.
  • the training tree will be rotated by its end outside the casing.
  • the drive shaft, the means of automatic declutching and the sealing means at least static are mounted on a removable support fixed to the housing on the opening to reach the tree to train.
  • the drive shaft will be coaxial with the shaft to train, which simplifies the coupling of which the automatic release can be ensured by a spring pushing the drive shaft outward.
  • Figure 1 is a simplified sectional view of a turbofan of the turbofan type with double body and double flow showing the kinematic chain from the rotor to the gearbox.
  • FIG. 2 illustrates an example of the state of the art.
  • FIG. 3 illustrates an example of implementation of the invention.
  • the turbomachine 1 is a double-body turbofan and double flow of a well known and commonly used type for propel transport aircraft. We will not describe this fact that the parts of the turbomachine 1 related to the invention.
  • the high pressure rotor 2 has a shaft 3 integral with several stages of blades 4 of the high compressor pressure at the front of the combustion chamber 5, and integral with one or more stages of blades 6 of the turbine the rear of said chamber 5.
  • the low pressure rotor 7 comprises a shaft 8 coaxial and inside the shaft 3, this shaft 8 being integral with the front of a stage of fan blades 9 and of several stages of blades 10 of the low pressure compressor, this shaft 8 also being integral with the back of one or several stages of blades 11 of the low pressure turbine.
  • the kinematic chain going from the shaft 3 of the high rotor pressure at the equipment support 14 comprises a succession of shafts 16 operating inside housings 20 and connected in rotation directly or indirectly to the rotor 2. There is thus successively a first bevel gear 15 to 90 ° with two bevel gears, a first shaft transmission 16a perpendicular to shaft 3, a second angle gear 17 at 90 ° with two bevel gears, and one second transmission shaft 16b parallel to the shaft 3 and driving in rotation one of the shafts and pinions 16c of equipment support 14.
  • Different equipment, such as starter or oil or fuel pumps are connected to the shafts and pinions 16c of the equipment support 14. Because difficult operating conditions, the components 16 of the drive train operate at inside of waterproof housings 20 and are lubricated by oil or oil mists.
  • the low pressure rotor 7 is directly accessible from the outside of the engine from the front or rear, and the step by step rotation of said low pressure rotor is done simply by hand.
  • the high pressure rotor 2 is not directly accessible from outside the motor, and the stepwise rotation of said rotor 2 takes place in hand-driving one of the trees 16.
  • the equipment support 14 comprises a casing 20c surrounding and supporting a plurality of shafts and pinions 16c meshing with each other.
  • the shaft referenced 16b in FIG. 1 transmits the movement to one of the shafts and pinions 16c of the equipment support 14 by means of a coupling generally of the fluted type 21. This movement is transmitted gradually. with different trees and gables 16c.
  • An opening 22 in the casing 20c is arranged opposite the end of a shaft 16c and is closed by a removable cover 23, while a non-circular bore, for example square 24 is arranged in the geometric axis 25 and at the end 26 of the shaft 16c.
  • a drive shaft 30 of geometric axis 31 aligned with the geometric axis 25 is held by a support 32 opposite the end 26 of the shaft 16c.
  • the shaft 30 ends on the side of the shaft 16c by a non-circular male end piece 33 of shape complementary to that of the bore 24 and capable of being introduced into this bore by a translation of the shaft 30 in the direction of the shaft 16c along the geometric axis 31.
  • the end piece 33 and the bore 24 constitute a disengageable coupling which will be generally referenced 34.
  • the drive shaft 30 is guided in translation and rotation by a bearing 35 located in its middle part. This guidance is sufficient when the end piece 33 is introduced into the bore 24, that is to say when the shaft 31 is in the engaged position.
  • the shaft 31 will also be guided by a second bearing 36 which can be reduced to a simple bore in the support 32, the shaft 31 being supported in this bearing 36 by the outermost parts of the end cap 33.
  • the shaft 30 has in its middle part a shoulder 37 against which comes to rest the end of a spring helical 38 surrounding the shaft 31, while the other end of the spring 38 bears against the support 32.
  • the shoulder 37 can also be constituted by a circlip.
  • the spring 38 pushes the shaft 31 outwards into position disengaged, the spring 38 and the shoulder 37 constituting more usually an automatic declutching means 39 of the coupling 34.
  • the shaft 30 arrives by its shoulder 37 abutting against the bearing 35, said shoulder 37 thus ensuring an axial retention function from tree 30.
  • the sealing means 40 of the shaft 30 relative to the casing 20c is preferably ensured by a lip seal 40a mounted in the support 32 and pressing on a circular surface 40b of the tree 30.
  • the surface 40b will be slightly conical with a slightly smaller diameter towards the end 41 of the shaft 30 furthest from the casing 20c, this reduction in diameter being sufficient for the contact between seal 40a and surface 40b becomes weak or nonexistent during manual rotation of the rotor.
  • a joint will be used 40a graphite-loaded Teflon ring with a section U-shaped opening opening facing the inside of the housing parallel to the geometric axis 31 of the shaft 30, sealing being achieved by the support of the U-shaped wings respectively on the surface 40b in its most part large diameter and against the bore not referenced in which is placed the seal 40a.
  • an annular spring not referenced surrounds the inner wing of the U and increases the pressure exerted by the seal 40a on the surface 40b.
  • seal 40a is available for example under the brand BALSEAL commercial.
  • a lip seal 40a with the lip turned inward is the preferred solution because during the operation of the turbomachine, it creates an overpressure inside the casing 20c which presses said lip on the surface 40b, which improves the sealing and reliability of the present device. Conversely when stationary, the overpressure no longer exists, the support of the lip of the seal 40a on the surface 40b is relaxed, which reduces the friction of the medium seal 40 and facilitates the operation of the shaft 30.
  • the reliability of the seal 40 is further improved by the taper of the surface 40b. Indeed, when we operate the shaft 30 to rotate the shaft 16c, it is necessary to press the shaft 30 in the casing to couple it to the shaft 16c, the joint 40a then being on surface 40b towards the end 41 of the shaft 31, the cylindrical surface 40b having a smaller diameter towards the end 41, the seal 40a no longer pressing lightly or not at all on the surface 40b, the seal 40a no longer risking being deteriorated or worn by the rotation of the shaft 30 or the radial deflection of this shaft 30 resulting from the play on the stages 35 and 36.
  • the support 32 will advantageously include a base 45 positioned in the bore 22a and the outer face 22b of the opening 22, and a cylinder 46, one end 46a of which is positioned on the base 45 while its other end 46b the outermost of the casing 20c receives the means 40.
  • the bearing 36 is positioned in the base 45 and the bearing 35 in the cylinder 46, the spring 38 taking support on the base 45.
  • the base 45 is statically sealed relative to the casing 20a, and the cylinder 46 is sealed by compared to base 45 for example by simple seals toric.
  • the cylinder 46 surrounds the middle part of the shaft 33, the bearing 35 and the automatic declutching means 39, and thus ensures the protection of these organs.
  • Support 32 is fixed on the casing 20c, for example by screws not depicted, as would be the cover of art prior.
  • the end 41 of the shaft 30 has a bore 50 no circular, for example square, and centered on its axis geometric 31. This bore makes it possible to couple a means of removable preemption of the shaft 30, for example a wrench standard ratchet or flywheel not shown, for manipulate this tree 30.
  • the end 41 of the shaft 31 will be protected protruding from cylinder 46 by a removable cap 51, fixed on cylinder 46, and at least dustproof by compared to this cylinder 46.
  • the relative arrangement and the mode of coupling of the shafts 16 and 30 may be subject to variants.
  • the static seal between the shaft 30 and the support 32 can also be ensured by a steep conical shoulder on the shaft 30 penetrating in the disengaged position in a bore of complementary shape of the support 32, the conical shoulder comprising at its surface a groove and an O-ring which ensures a perfect seal with the tapered bore without rubbing against it during disengagement.

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 (6)

  1. Turbomaschine, die mit einer Vorrichtung für den manuellen Antrieb ihres Rotors (2) ausgestattet ist,
       gekennzeichnet durch
    a) ein Gehäuse (20), das eine Welle (16) enthält, die mit dem Rotor (2) drehfest verbunden ist, wobei das Gehäuse (20) eine Öffnung (22) aufweist, durch die diese Welle (16) zugänglich ist,
    b) eine Antriebswelle (30), die die Wand des Gehäuses (20) durch die Öffnung (22) durchdringt, wobei diese Antriebswelle (30) von einem auf der Öffnung (22) montierten abnehmbaren Träger (32) gehalten wird,
    c) ein Mittel (34) zur drehfesten Kupplung der Wellen (16 und 30),
    d) ein Mittel (39) zum automatischen Auskuppeln der Kupplung,
    e) ein Mittel (40) für die zumindest statische Abdichtung zwischen der Antriebswelle (30) und der Wand des Gehäuses (20), wobei dieses Abdichtungsmittel (40) zumindest dann aktiv ist, wenn die Antriebswelle (30) sich in ihrer ausgekuppelten Position befindet.
  2. Turbomaschine nach Anspruch 1, dadurch gekennzeichnet, daß die Antriebswelle (30) eine axiale Translationsbewegung ausführen kann und von einer Feder (38) nach außen in die ausgekuppelte Position vorgespannt ist.
  3. Turbomaschine nach Anspruch 2, bei der das Abdichtungsmittel (40) eine mit dem abnehmbaren Träger (32) fest verbundene Dichtung (40a) aufweist, die sich auf einer kreisrunden Fläche (40b) der Antriebswelle (30) abstützt, dadurch gekennzeichnet, daß die kreisrunde Fläche (40b) konisch ist und in Richtung auf das von dem Gehäuse (20) am weitesten entfernte Ende (41) der Welle (30) einen geringeren Durchmesser hat, um den Kontakt zwischen der Dichtung (40a) und der genannten Fläche (40b) während der manuellen Drehung des Rotors zu verringern oder aufzuheben
  4. Turbomaschine nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß die Antriebswelle (30) koaxial zu der anzutreibenden Welle (16) angeordnet ist und daß die Kupplung durch die gegenseitige Durchdringung einer nicht kreisrunden Bohrung (24) der Welle (16) und eines Ansatzstücks (33) der Welle (30) erfolgt, wobei das Ansatzstück (33) eine zu der genannten Bohrung (24) komplementäre Form hat.
  5. Turbomaschine nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß das Gehäuse (20) das Gehäuse (20c) des Trägers (14) der Ausrüstung ist.
  6. Turbomaschine nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß das außerhalb des Gehäuses (20) liegende Ende (41) der Antriebswelle mit einer zumindest gegen Staub statisch abdichtenden abnehmbaren Schutzkappe (51) abgedeckt ist.
EP96401418A 1995-06-28 1996-06-27 Auskuppelbare manuelle Rotordrehvorrichtung für eine Turbomaschine Expired - Lifetime EP0754838B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9507754A FR2736092B1 (fr) 1995-06-28 1995-06-28 Commande manuelle debrayable pour l'entrainement du rotor d'une turbomachine
FR9507754 1995-06-28

Publications (2)

Publication Number Publication Date
EP0754838A1 EP0754838A1 (de) 1997-01-22
EP0754838B1 true EP0754838B1 (de) 1999-03-10

Family

ID=9480460

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96401418A Expired - Lifetime EP0754838B1 (de) 1995-06-28 1996-06-27 Auskuppelbare manuelle Rotordrehvorrichtung für eine Turbomaschine

Country Status (4)

Country Link
US (1) US5813829A (de)
EP (1) EP0754838B1 (de)
DE (1) DE69601672T2 (de)
FR (1) FR2736092B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7685826B2 (en) 2005-12-12 2010-03-30 General Electric Company Methods and apparatus for performing engine maintenance
CN1940253B (zh) * 2005-08-02 2010-11-10 诺沃皮尼奥内有限公司 用于涡轮机检查的运动系统

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US6553327B2 (en) * 1998-09-16 2003-04-22 Yeda Research & Development Co., Ltd. Apparatus for monitoring a system with time in space and method therefor
US6382909B1 (en) * 1999-05-14 2002-05-07 Dresser-Rand Company Rotary turning apparatus
DE10334448B4 (de) * 2003-07-29 2005-09-01 Renk Ag Windkraftanlage
US7354216B2 (en) * 2005-04-12 2008-04-08 Honeywell International, Inc. Grease seal cup to retain lubrication for life extension in existing splined joint
US7866234B2 (en) * 2007-08-15 2011-01-11 General Electric Company Manual core rotation device
GB0901059D0 (en) * 2009-01-23 2009-03-11 Rolls Royce Plc Rotation arrangement
FR2952121B1 (fr) * 2009-10-29 2011-12-23 Snecma Dispositif d'entrainement mecanique du corps haute pression d'un moteur d'avion
JP5409604B2 (ja) 2010-02-03 2014-02-05 三菱重工業株式会社 風力発電装置用のロータターニング装置およびロータターニング方法
US8438949B2 (en) * 2010-08-02 2013-05-14 Hamilton Sundstrand Corporation Sealed rotator shaft for borescopic inspection
US8845275B2 (en) 2010-11-11 2014-09-30 Hamilton Sundstrand Corporation Cranking pad interlock
US8813607B2 (en) * 2011-06-20 2014-08-26 Hamilton Sundstrand Corporation Fail-safe manual rotator cover
EP2602442B1 (de) * 2011-12-05 2014-08-13 Hamilton Sundstrand Corporation Verriegelung für Antriebskurbel
FR2986568B1 (fr) * 2012-02-07 2016-06-10 Snecma Dispositif d'etancheite avec joint hydraulique du passage d'un arbre rotatif au travers d'une paroi d'une enceinte.
FR2995361B1 (fr) * 2012-09-07 2014-08-29 Snecma Dispositif de bouchage d'une ouverture d'une paroi d'enceinte pour l'acces a un arbre rotatif.
FR3038715B1 (fr) * 2015-07-07 2020-12-25 Snecma Identification de capteurs dans une turbomachine
US10823014B2 (en) 2017-12-13 2020-11-03 General Electric Company Turbine engine for reducing rotor bow and method thereof
FR3108660B1 (fr) 2020-03-24 2022-03-11 Safran Aircraft Engines Actionneur de mise en rotation d’un rotor de turboréacteur pour une opération d’inspection et/ou de maintenance
US11608757B2 (en) * 2020-04-02 2023-03-21 Parker-Hannifin Corporation Crank device for performing turbine engine maintenance
US11549443B2 (en) 2020-08-28 2023-01-10 Pratt & Whitney Canada Corp. Sealing arrangement with vent for an engine component with a service port
US11629648B2 (en) 2020-12-17 2023-04-18 Hamilton Sundstrand Corporation Quick access engine rotator pad
CN112846341B (zh) * 2021-01-05 2022-02-01 山东省章丘鼓风机股份有限公司 一种小尺寸冷却风扇插床工装
CN112761744B (zh) * 2021-01-26 2022-09-27 东方电气集团东方汽轮机有限公司 一种独立的手动盘车装置及盘车结构

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Publication number Priority date Publication date Assignee Title
CN1940253B (zh) * 2005-08-02 2010-11-10 诺沃皮尼奥内有限公司 用于涡轮机检查的运动系统
US7685826B2 (en) 2005-12-12 2010-03-30 General Electric Company Methods and apparatus for performing engine maintenance

Also Published As

Publication number Publication date
DE69601672D1 (de) 1999-04-15
DE69601672T2 (de) 1999-09-09
FR2736092B1 (fr) 1997-08-01
US5813829A (en) 1998-09-29
FR2736092A1 (fr) 1997-01-03
EP0754838A1 (de) 1997-01-22

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