EP4102029A1 - Procédé de fabrication d'un rotor pour une turbomachine - Google Patents

Procédé de fabrication d'un rotor pour une turbomachine Download PDF

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Publication number
EP4102029A1
EP4102029A1 EP22173175.5A EP22173175A EP4102029A1 EP 4102029 A1 EP4102029 A1 EP 4102029A1 EP 22173175 A EP22173175 A EP 22173175A EP 4102029 A1 EP4102029 A1 EP 4102029A1
Authority
EP
European Patent Office
Prior art keywords
rotor part
intermediate piece
rotor
bore
face
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.)
Pending
Application number
EP22173175.5A
Other languages
German (de)
English (en)
Inventor
Stauff Ulrich
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.)
Atlas Copco Energas GmbH
Original Assignee
Atlas Copco Energas GmbH
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 Atlas Copco Energas GmbH filed Critical Atlas Copco Energas GmbH
Publication of EP4102029A1 publication Critical patent/EP4102029A1/fr
Pending 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/025—Fixing blade carrying members on 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins

Definitions

  • the present invention relates to a method for producing a rotor for a turbomachine, comprising a first rotor part and a second rotor part.
  • Hirth coupling which provides a toothed profile on the end faces of the two rotor parts. These toothed profiles are pushed together in a form-fitting manner in the axial direction and held together by axial bracing.
  • the production of such a coupling regularly generates a great deal of work and places particularly high demands on the manufacturing tolerances so that no imbalances or misalignments occur.
  • a so-called “pinning” is sometimes used.
  • axially running bores are made in the end faces, into which one or more pins are inserted or screwed.
  • the pins protrude from an end face of one of the two rotor parts in such a way that they can engage in a corresponding opening in the second rotor part. This provides a positive rotary connection.
  • the invention is based on the object of specifying an improved torsionally rigid axial connection (shaft-hub connection) which is higher both in terms of calculation and in practice Allowed loads with a lower cost of materials and a simple production.
  • the invention is based on the fact that the first rotor part is formed around a first longitudinal axis and has a first end face running perpendicularly to the first longitudinal axis.
  • the second rotor part is formed around a second longitudinal axis and has a second end face running perpendicular to the second longitudinal axis.
  • an intermediate piece which has a first contact surface and a second contact surface. This intermediate piece is brought into contact with the first contact surface on the first face—first position. In this first position, at least one first bore is introduced through the intermediate piece and the first end face into the first rotor part.
  • the relative position of the intermediate piece and the first rotor part corresponds to the relative orientation and positioning in the connected end state provided later.
  • the intermediate piece is brought into contact with the second contact surface on the second end face—second position.
  • at least one second bore is introduced through the intermediate piece and the second end face into the second rotor part.
  • the relative orientation and positioning of the intermediate piece and the second rotor part correspond to the position in the final state.
  • a first pin is arranged in the first bore, which pin extends both into the first rotor part and into the intermediate piece.
  • a second pin arranged, which extends into the intermediate piece and into the second rotor part.
  • the intermediate piece is brought into contact with the first contact surface on the first end face and with the second contact surface on the second end face, with the first axis of longitudinal extent and the second axis of longitudinal extent being arranged in alignment.
  • the first rotor part and the second rotor part are tensioned against one another in the direction of the first longitudinal axis and the second longitudinal axis (axial direction).
  • the torsionally rigid connection of the two rotor parts produced in this way is on the one hand easy to produce and on the other hand extremely stable and dimensionally accurate due to the freedom from play. Due to the tensile stress in the axial direction, the pinning can on the one hand be well secured and the two rotor parts can also be firmly connected to one another—and also released again—with very little effort.
  • the first rotor part is designed as a rotor shaft and the second rotor part is designed as a turbo impeller.
  • the rotor shaft is intended in particular to be attached to the housing of a turbomachine in To be supported by bearings in the axial and radial direction and also to provide the power transmission of the turbo impeller to a drive and / or an output.
  • the turbo impeller is used for the fluidic conversion of flow energy into rotary energy (turbine) or rotary energy into flow energy (turbo pump, turbo compressor).
  • the turbo impeller contains flow guide devices, in particular rotor blades or ducts, and can be designed as a radial or axial turbo impeller without restricting the invention.
  • the attachment of the two rotor parts with the aid of longitudinal bracing also makes it particularly easy to assemble and disassemble the turbo impeller, particularly from the side facing away from the rotor shaft.
  • the first bore and the second bore are preferably aligned parallel to the first axis of longitudinal extent and parallel to the second axis of longitudinal extent.
  • the axial positioning and tolerance of the pins in the bores are independent of one another, independently of the axial position of the first rotor part, the second rotor part and the intermediate piece. In particular, this enables a subsequent change in the thickness of the intermediate piece in the axial direction—for example, by material removal and/or compression.
  • the first pin is guided without play in the first bore and the second pin is guided without play in the second bore.
  • the total play of the rotor system is reduced due to the play-free guidance.
  • the pins can take on loads directly in both directions of rotation, without this having to be done first by rotating the two rotor parts relative to one another - against the inhibition of the tensile stress on the end faces.
  • a so-called press fit is to be regarded as "free of play”.
  • the maximum dimension within the manufacturing tolerances of the (first or second) bore smaller than the smallest size within the manufacturing tolerances of the (first or second) pin. To connect, the pins must be pressed into the respective assigned bores.
  • a plurality of first bores are inserted through the intermediate piece into the first rotor part, in which first pins are later inserted, and a plurality of second bores of the intermediate piece are inserted into the second rotor part, into which a plurality of second pins are later inserted.
  • the plurality of first and second bores are particularly preferably arranged equidistantly with the same pitch in the circumferential direction.
  • the large number of first and second bores improves the transmission of torque and at the same time ensures that the first rotor part and the second rotor part are centered relative to the intermediate piece.
  • the same number of first bores and second bores are provided, which are positioned alternately in the circumferential direction.
  • the first pin-or the first pins- is screwed into the first rotor part or the intermediate piece and/or the second pin-or the second pins-is screwed into the second rotor part or into the intermediate piece.
  • the pins are not only held captively on the respective rotor component (intermediate piece or rotor part), but are also reliably held against slipping in the axial direction.
  • a larger contact surface between the rotor component and the pin is also provided with a screw connection by means of a screw thread, on which additional forces can be transmitted by frictional engagement.
  • the respective pin can also be screwed into the associated rotor component with a press fit.
  • first bore is delimited by the end face of the second rotor part and the interior of a second bore is delimited by the first end face of the first rotor part.
  • the length of the pins is dimensioned in such a way that they are longer than the respective penetration depth into the intermediate piece or into the first or second rotor part. This ensures that even an axially displaceable pin is always in contact with the respective rotor part and the intermediate piece and can transmit forces there.
  • the pin always fills at least 75% of the interior of the first bore or the second bore.
  • the pin is particularly preferably slightly shorter than the axial extent of the associated bores, so that a subsequent length adjustment can take place by compressing or removing the intermediate piece.
  • the material of the intermediate piece has a lower thermal conductivity than the material of the first rotor part and than the material of the second rotor part.
  • those materials that form the first end face and the second end face are particularly relevant.
  • the intermediate piece is shortened to adjust the distance between the first rotor part and the second rotor part in the direction of the longitudinal axis, preferably after the introduction of the first bore and the penetration of the second bore and particularly preferably by grinding or machining.
  • This enables an exact axial positioning of the two rotor parts relative to one another. For example, it is conceivable to measure the dimensions of a turbomachine rotor exactly after it has been assembled using the method according to the invention described above. This is particularly necessary when individual rotor parts are manufactured separately from one another. If deviations are found in the longitudinal direction (axial direction), these can be remedied by subsequent grinding in of the spacer.
  • a corresponding correction is also possible later - for example after final assembly in the turbomachine or even as part of periodic maintenance work. Only the two rotor parts have to be relaxed and separated from each other. After removing the intermediate piece, it can be shortened accordingly to correct a length error. After reassembly, the first rotor part and the second rotor part are tightly clamped together at a smaller distance due to the reduced thickness—measured in the axial direction—of the intermediate piece.
  • the invention also relates to a rotor for a turbomachine, obtainable in particular by a method according to claims 1 to 8.
  • the rotor comprises a first rotor part, a second rotor part, an intermediate piece arranged between the first rotor part and the second rotor part, and at least one clamping means for axial bracing of the first rotor part with the second rotor part.
  • at least one first pin is in a first bore, which extends through the intermediate piece and into the first Rotor part extends into it without play.
  • a second pin which extends through the adapter and into the second rotor part, is accommodated in a second bore without play.
  • a rotor 1 according to the invention for a turbomachine is shown, which was produced according to the method according to the invention.
  • the rotor 1 is mounted on a housing 2, which is only indicated, and is sealed off from it by at least one shaft seal 2a.
  • the rotor 1 comprises a first rotor part 3 in the form of a rotor shaft rotatably mounted on the housing 2 and a second rotor part 4, which in the exemplary embodiment is designed as a radial turbo impeller with flow channels 4b arranged therein.
  • an intermediate piece 5 is arranged between the first rotor part 3 and the second rotor part 4 .
  • a clamping means 6 is provided in the form of a clamping bolt, by means of which the first rotor part 3 and the second rotor part 4 can be clamped in the axial direction—ie along the axis of rotation x of the rotor 1 with the intermediate piece 5 arranged in between.
  • the first rotor part 3 is formed around a first longitudinal axis a, which is in the 1 illustrated assembled state with the axis of rotation x of the rotor 1 coincides.
  • a first end face 3a is formed on the first rotor part 3 perpendicular to the first longitudinal axis a.
  • the first end face is formed within a stepped recess of the first rotor part 3 and is in contact with an annular first contact surface 5a of the intermediate piece 5.
  • the intermediate piece 5 also bears radially inward on a first stepped surface 3b of the first rotor part.
  • a first bore 8a is formed in the intermediate piece 5 and the first rotor part 3, in which a first pin 9a is accommodated without play.
  • the first bore is aligned parallel to the first longitudinal axis a or the axis of rotation x of the rotor 1 .
  • the cavity formed by the first bore 8a is delimited in the axial direction by a second end face 4a of the second rotor part 4 and is almost completely filled by the first pin 9a.
  • the second rotor part extends around a second longitudinal direction b, which also coincides with the axis of rotation x of the rotor 1 in the assembled state.
  • the second end face 4a is also aligned perpendicularly to the second direction of longitudinal extent b and is in planar contact with a second contact surface 5b of the intermediate piece 5.
  • a second bore 8b is formed in the intermediate piece 5 and the second rotor part 4, in which a second pin 9b is accommodated without play is.
  • the second bore 8b is delimited in the axial direction by the first end face 3a and almost completely filled by the second pin 9b.
  • the intermediate piece 5 is designed as a circular ring disk, rotationally symmetrical about the axis of rotation x, with an inner radius r and an outer radius R.
  • the intermediate piece 5 has a thickness d in the axial direction x. This can be reduced in particular by removing material to adjust the distance between the first rotor part 3 and the second rotor part 4 .
  • the inventive method is based on the Figures 2A and 2 B explained. It is essential that the intermediate piece 5 is in a first position ( Figure 2A ) with the first rotor part 3 and in a second position ( Figure 2B ) is brought into contact with the second rotor part 4. In the first position, the first bore 8a is introduced into the first rotor part 3 through the intermediate piece, the first contact surface 5a and the first end face 3a.
  • the intermediate piece 5 of the first rotor part 3 is particularly preferably braced in this first position and expediently a plurality of first bores 8a distributed in the circumferential direction are produced.
  • a second position ( Figure 2B ) the intermediate piece 5 is brought into contact with the second contact surface 5b on the second end face 4a so that the axis of symmetry of the intermediate piece 5 is aligned with the second longitudinal axis b of the second rotor part 4 .
  • one or more second bores 8b can then be introduced into the second rotor part 4 through the intermediate piece 5, the second contact surface 5b, and the second end face 4a.
  • several first bores 8a and second bores 8b should be introduced without the intermediate piece and the respective rotor part 3, 4 being moved in the meantime.
  • the holes can be made simultaneously by a multiple drill.
  • the first rotor part 3 and the second rotor part 4 are both supported simultaneously on the intermediate piece 5 without touching each other.
  • the intermediate piece 5 has a reduced specific thermal conductivity compared to the material of the first rotor part 3 and the material of the second rotor part 4 . As a result, a heat transfer between the rotor shaft 3 and the turbo impeller 4 can be reduced.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP22173175.5A 2021-06-07 2022-05-13 Procédé de fabrication d'un rotor pour une turbomachine Pending EP4102029A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102021114576.7A DE102021114576A1 (de) 2021-06-07 2021-06-07 Verfahren zur Herstellung eines Rotors für eine Turbomaschine

Publications (1)

Publication Number Publication Date
EP4102029A1 true EP4102029A1 (fr) 2022-12-14

Family

ID=81653510

Family Applications (1)

Application Number Title Priority Date Filing Date
EP22173175.5A Pending EP4102029A1 (fr) 2021-06-07 2022-05-13 Procédé de fabrication d'un rotor pour une turbomachine

Country Status (2)

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EP (1) EP4102029A1 (fr)
DE (1) DE102021114576A1 (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2366870A2 (fr) * 2010-03-16 2011-09-21 Bosch Mahle Turbo Systems GmbH & Co. KG Rotor d'un turbochargeur
WO2013110922A1 (fr) * 2012-01-24 2013-08-01 Napier Turbochargers Limited Système de connexion, rotor et turbocompresseur correspondants
DE102012205042A1 (de) * 2012-03-29 2013-10-02 Continental Automotive Gmbh Turbinenläufer für eine Abgasturbine sowie ein Verfahren zur Herstellung des Turbinenläufers
CN112049687A (zh) * 2020-07-28 2020-12-08 北京控制工程研究所 用于空间热电转换的耐高温涡轮发电机转子及其装配方法

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2933513A1 (fr) 2014-04-15 2015-10-21 Siemens Aktiengesellschaft Dispositif d'accouplement destiné à relier un embrayage à un ensemble de turbine
DE102015205042A1 (de) 2015-03-19 2016-09-22 Continental Automotive Gmbh Verfahren zur Steuerung einer Audiosignalausgabe für ein Fahrzeug

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2366870A2 (fr) * 2010-03-16 2011-09-21 Bosch Mahle Turbo Systems GmbH & Co. KG Rotor d'un turbochargeur
WO2013110922A1 (fr) * 2012-01-24 2013-08-01 Napier Turbochargers Limited Système de connexion, rotor et turbocompresseur correspondants
DE102012205042A1 (de) * 2012-03-29 2013-10-02 Continental Automotive Gmbh Turbinenläufer für eine Abgasturbine sowie ein Verfahren zur Herstellung des Turbinenläufers
CN112049687A (zh) * 2020-07-28 2020-12-08 北京控制工程研究所 用于空间热电转换的耐高温涡轮发电机转子及其装配方法

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DE102021114576A1 (de) 2022-12-08

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