EP3022405B1 - Dispositif de dépose pour aubes et procédé de dépose correspondant - Google Patents

Dispositif de dépose pour aubes et procédé de dépose correspondant Download PDF

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Publication number
EP3022405B1
EP3022405B1 EP14747094.2A EP14747094A EP3022405B1 EP 3022405 B1 EP3022405 B1 EP 3022405B1 EP 14747094 A EP14747094 A EP 14747094A EP 3022405 B1 EP3022405 B1 EP 3022405B1
Authority
EP
European Patent Office
Prior art keywords
turbine
ring
dismantling
holding element
blades
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.)
Active
Application number
EP14747094.2A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3022405A1 (fr
Inventor
Jean Marie FRAUCA
Yann MERSCHAERT
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
Safran Aircraft Engines SAS
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Filing date
Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3022405A1 publication Critical patent/EP3022405A1/fr
Application granted granted Critical
Publication of EP3022405B1 publication Critical patent/EP3022405B1/fr
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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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • 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
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • F01D5/12—Blades
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • 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
    • 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
    • F05D2230/70—Disassembly methods
    • 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
    • F05D2240/00—Components
    • F05D2240/60—Shafts
    • 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

Definitions

  • the invention relates to a device for depositing at least one blade of a turbine; a system for removing at least one blade of a turbine, a method of mounting such a dispensing device and also a method of removing at least one turbine blade.
  • the invention relates more particularly to the field of aircraft engine turbines, and in particular high pressure turbines.
  • the figure 1 schematically illustrates a general section of an aircraft engine and the different parts of said engine.
  • the air entering through the air inlet of the ADMISSION part of the cold section is compressed in a compressor (COMPRESSION part on the figure 1 ) before being mixed with a fuel and burned in one of the combustion chambers of the COMBUSTION part.
  • the hot gases produced in the combustion chamber reach the vanes of the turbine and drive the turbine (or several turbines) and are ejected at the EXHAUST portion of the engine which generates a thrust causing the aircraft.
  • a turbine stage generally consists of a fixed blade followed by a moving blade.
  • a turbine may comprise one or more stages. The invention relates more particularly to the removal of the mobile blade of the turbine.
  • the axis of insertion of the vanes into the cells of the turbine in which they are received is inclined with respect to the motor axis in order to contribute to the maintenance of the vanes between them during the high speed rotation of the turbine, the removal blades are progressively and radially elliptical.
  • the inclination of the axis of insertion of the blades with respect to the motor axis can be about thirty degrees for example.
  • the figure 2 allows to visualize the inclination of an angle ⁇ of the insertion axis Xi of a blade A with respect to the shaft of the turbine Ar (turbine shaft and motor shaft are combined).
  • a sealing liner is furthermore generally inserted between two successive blades in order to reduce almost completely the clearance between the vanes.
  • the withdrawal is gradual, i.e. dawn after dawn, small distance a short distance until each dawn is maintained only a few millimeters in the cell in which his foot is inserted. These few millimeters, for example two millimeters, allow to have a sufficient clearance between the blades to extract them one by one.
  • the invention aims to remedy all or some of the disadvantages of the state of the art identified above, and in particular to propose means for to make it possible to secure the removal of the blades by limiting as much as possible the risk of falling blades during operation in the horizontal position of the engine.
  • one aspect of the invention relates to a device for depositing at least one blade of a turbine described in claim 1.
  • Such a device advantageously makes it possible to block, preferably axially, ie in a direction parallel to the shaft of the turbine, the vanes of the turbine when they are no longer retained in their respective cells by a few millimeters ie when they are are ready to be deposited.
  • a turbine blade to fall just before removal in itself (withdrawal of the blade of its alveolus).
  • the removal opening may be a notch made in the holding element.
  • the sizing of the dispensing aperture is related to the height of the portion of the blade taken in its cell to ensure its extraction from said cell.
  • the removal opening makes it possible to get rid of hazards specific to the environment where the removal of the blade of the horizontal type of the engine or module takes place, risk of contact between operators and therefore a fall of one or several blades, small shocks or repeated efforts to exit each dawn of his home, possible instability of the ground, shocks on the engine.
  • the holding element is preferably fixed to the hub / trunnion of the turbine.
  • an angular position of the holding member can be done by rotating the holding member manually around the turbine shaft due to the pivot connection.
  • the setting compared to the opening of deposit with the dawn to deposit allows an operator to access this blade which is not blocked by the blocking surface.
  • the other blades are maintained thanks to the blocking surface and are not likely to drop in the event of a jolt, mishandling or other accident.
  • the invention also relates to a system for depositing at least one blade of a turbine, said turbine comprising a set of N blades, said system comprising a dispensing device according to one of the previously described embodiments, a shaft of the turbine, the first ring being fixed to the shaft of the turbine so that it is integral in rotation with the shaft of the turbine and the holding member being free to rotate relative to the turbine shaft in the circular groove.
  • An operator to access the blades and extract them partially gradually, in ellipse of their respective cells can either help the opening of removal, and in this case rotate the holding element to put the aperture drop off each dawn little by little; either use the access opening, or the plurality of access openings.
  • the method according to the invention may have the following additional characteristic: the partial extraction step is carried out by a plurality of successive axial displacements of each of the blades of the set of vanes so as to position said vanes abutting against the blocking surface.
  • the partial extraction is done by dawn by rotating all along the turbine and by repeating this operation until the blade dimension, and more particularly the blade root, outside the corresponding cell is sufficient for the game between blades allows the removal of a blade. In this case, the blades are in abutment against the blocking surface.
  • the figure 1 illustrates a sectional view of an aircraft engine
  • the dispensing system comprises a dispensing device 1 and a turbine shaft Ar, here a journal.
  • the figure 3 illustrates the dispensing system in a vertical configuration of the turbine.
  • This type of configuration is generally adopted for the set of blades.
  • the vanes being deposited axially in their respective cells (cells not visible in the photo) along the axis X1, it is visible that in this so-called vertical configuration, no risk of falling in case of shock, shock is to be feared.
  • the blades are placed (and deposited) gradually, one after the other, elliptically millimeters by millimeters. In the vertical configuration, a blade whose foot is inserted only one or two millimeters into its cell will not fall.
  • the figure 4 illustrates the removal system of the figure 1 in a horizontal configuration of the turbine.
  • This configuration is generally used for in-situ blade removal.
  • a blade whose foot is inserted only one or two millimeters into its cell, just before removal (which is the total extraction of the blade of its cell along the axis X2) may fall without the removal device 1 whose operation will be explained in more detail with reference to the following figures.
  • the holding member is a ring.
  • the figure5A illustrates a first ring 121 attached to the shaft Ar of the turbine and thus secured in rotation with the shaft Ar of the turbine. It is fixed by means of a system 3 with screws and nuts to the shaft of the turbine Ar and more particularly to an apparent surface element 21 of the shaft Ar.
  • the first ring 121 has a shoulder 1212 on the outer surface 1211 of the first ring 121.
  • the Figure 5B is the first ring 121. It has holes 3 of the screw system and nuts for fixing the first ring to the turbine shaft. Also visible are passage holes 4 of a system for fixing a second ring to the first ring.
  • the first ring has a shoulder 1212 protruding on the outer surface 1211 of the first ring.
  • the outer surface 1211 is the surface which will be facing the locking surface of the holding member once the latter has been positioned relative to the first ring 121 and will be described with reference to the following figures.
  • the shoulder 1212 is circular and its diameter is smaller than the diameter of the first ring. Its function is to allow the positioning of the holding element and its centering.
  • the Figure 6A illustrates a holding member 11 positioned on the shoulder 1212 of the first ring 121, the first ring being fixed to the shaft Ar of the turbine.
  • the radial movements of the holding member 11 are blocked.
  • the axial movements towards the motor of the holding element 11 are blocked by the surface S of the first ring against which it bears.
  • the holding element comprises a blocking surface 111 whose function is to block the blades A in axial translation along their insertion axis in their respective cells in the direction of their removal, i.e. their extraction of the cells.
  • This axis is inclined relative to the shaft of the turbine Ar, which is the axis of rotation of the motor. This inclination has the function of allowing the maintenance of the blades during the high speed rotation of the turbine.
  • the Figure 6B is the holding member 11.
  • the locking surface 111 is constituted by the entire holding member except the dispensing opening 112, which is a notch in this embodiment.
  • the dimensions of the deposit opening 112, by which is deposited, ie totally extracted, the blade to be deposited, are a function of the geometry of the blade to be deposited.
  • the dispensing aperture 112 is here at the periphery of the holding element 11, so the dispensing opening 112 is also open towards the outside of the periphery of the holding element 11 and has this notch shape and can pass thus only the foot of dawn.
  • the holding element 11 of the Figure 6B comprises five access openings 113. These access openings 113 allow an operator to access, for example by means of his thumb, an area of the space 114 defined opposite the blocking surface (refer to FIG. the Figure 6A ) so as to catch the foot of the dawn in order to partially extract the dawn. This partial extraction can also be performed by means of the dispensing aperture 112, but in this case, it is necessary to rotate the holding element each time to put the dispensing opening 112 next to each blade, some after others.
  • the Figure 7A illustrates the removal system, once a second ring 122 attached to the first ring 121 by means of wing screws 4, chosen for their ease of tightening / loosening.
  • the superposition of the first ring 121 and the second ring 122 forms a circular groove 123 for holding and the rotational drive of the holding member 11 relative to the shaft of the turbine Ar.
  • the circular groove is formed by the shoulder 1212 of the first ring, the outer surface 1211 of the first ring facing the surface of the locking 111 of the holding member and the second ring 122.
  • the holding element 11 comprises a stop 1111 on the blocking surface 111.
  • This abutment makes it possible to adjust the axial retention of the blades and the dimensioning of this abutment is a function of the distance from which the vanes of their cells must be partially extracted before it can be deposited by the opening 112.
  • the first ring / second ring assembly forms the fastening means 12 of the holding element 11 on the shaft Ar of the turbine. Thanks to the circular groove formed by the superimposition of the first and second ring in which the holding element is located, a pivot connection is formed between the holding element and the shaft Ar of the turbine.
  • the Figure 7B illustrates the second ring 122 having passage holes 5 for thumb screws 4 for fixing the second ring to the first ring.
  • the operator rotates the holding member around the blade.
  • turbine shaft in order to bring the dispensing aperture opposite each vane to be deposited in order to extract it completely from its cell by passing it through the dispensing opening since it is no longer blocked by the surface of the locking of the holding element.
  • the holding element having several angular positions depending on the blade to be deposited.
  • the blocking surface ensures the maintenance of the blades not deposited safely.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP14747094.2A 2013-07-15 2014-07-10 Dispositif de dépose pour aubes et procédé de dépose correspondant Active EP3022405B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1356940A FR3008448B1 (fr) 2013-07-15 2013-07-15 Dispositif de depose pour aubes
PCT/FR2014/051774 WO2015007979A1 (fr) 2013-07-15 2014-07-10 Dispositif de dépose pour aubes et procédé de dépose correspondant

Publications (2)

Publication Number Publication Date
EP3022405A1 EP3022405A1 (fr) 2016-05-25
EP3022405B1 true EP3022405B1 (fr) 2019-11-13

Family

ID=49667308

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14747094.2A Active EP3022405B1 (fr) 2013-07-15 2014-07-10 Dispositif de dépose pour aubes et procédé de dépose correspondant

Country Status (5)

Country Link
US (1) US10533434B2 (zh)
EP (1) EP3022405B1 (zh)
CN (1) CN105452617B (zh)
FR (1) FR3008448B1 (zh)
WO (1) WO2015007979A1 (zh)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108005732B (zh) * 2017-12-20 2024-04-19 华瑞（江苏）燃机服务有限公司 一种燃气轮机透平静叶组件的拆卸机构
FR3082232B1 (fr) * 2018-06-12 2020-08-28 Safran Aircraft Engines Systeme de maintien pour le demontage d'une roue a aubes
CN109676562A (zh) * 2018-12-19 2019-04-26 中国航发沈阳发动机研究所 一种航空发动机低压涡轮导向叶片安装装置
CN113814697B (zh) * 2020-06-18 2022-10-28 中国航发商用航空发动机有限责任公司 低压涡轮轴的分解方法

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5131814A (en) * 1990-04-03 1992-07-21 General Electric Company Turbine blade inner end attachment structure
DE19520274A1 (de) * 1995-06-02 1996-12-05 Abb Management Ag Vorrichtung und Verfahren zur Montage von Laufschaufeln
US7048504B2 (en) * 2003-05-07 2006-05-23 Snecma Moteurs Machine stator and mounting and dismounting methods
US7648336B2 (en) * 2006-01-03 2010-01-19 General Electric Company Apparatus and method for assembling a gas turbine stator
US7971334B2 (en) * 2008-01-22 2011-07-05 United Technologies Corporation Bladed disk assembly method and roller device
US8046886B2 (en) * 2009-12-30 2011-11-01 General Electric Company Fixture for mounting articulated turbine buckets
US20120156045A1 (en) * 2010-12-17 2012-06-21 General Electric Company Methods, systems and apparatus relating to root and platform configurations for turbine rotor blades

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
WO2015007979A1 (fr) 2015-01-22
FR3008448A1 (fr) 2015-01-16
CN105452617A (zh) 2016-03-30
US10533434B2 (en) 2020-01-14
CN105452617B (zh) 2018-03-06
EP3022405A1 (fr) 2016-05-25
FR3008448B1 (fr) 2018-01-05
US20160169010A1 (en) 2016-06-16

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