EP3788236A1 - Rotor pourvu d'une pièce disposée entre deux disques de rotor - Google Patents

Rotor pourvu d'une pièce disposée entre deux disques de rotor

Info

Publication number
EP3788236A1
EP3788236A1 EP19752935.7A EP19752935A EP3788236A1 EP 3788236 A1 EP3788236 A1 EP 3788236A1 EP 19752935 A EP19752935 A EP 19752935A EP 3788236 A1 EP3788236 A1 EP 3788236A1
Authority
EP
European Patent Office
Prior art keywords
rotor
disk
recesses
ring projection
radially
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
EP19752935.7A
Other languages
German (de)
English (en)
Other versions
EP3788236B1 (fr
Inventor
Peter Kury
Harald Hoell
Karsten Kolk
Vyacheslav Veitsman
Yulia Bagaeva
Christopher W. Ross
Peter Schröder
Andrew R. Waddell
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.)
Siemens Energy Global GmbH and Co KG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Publication of EP3788236A1 publication Critical patent/EP3788236A1/fr
Application granted granted Critical
Publication of EP3788236B1 publication Critical patent/EP3788236B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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
    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade 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
    • 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
    • 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
    • F05D2220/32—Application in turbines in gas 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking

Definitions

  • the invention relates to a rotor of a gas turbine, which has at least two interconnected rotor disks, between which an annular rotor component is arranged.
  • annular rotor component being arranged between the rotor disks for shielding the inner region of the rotor from the hot gas flowing through the gas turbine.
  • the two rotor disks each have a plurality of rotor blades distributed over the outer circumference. Between the two rows of blades, there is a row with guide vanes distributed around the circumference, each of which is attached to the stationary housing. Because of the rotation of the rotor, there is inevitably a gap between the guide vanes and the blades. This basically allowed hot gas to enter the area radially within the guide vane.
  • an annular rotor construction part is arranged in some gas turbines between the two adjacent rotor disks. For this purpose, this rotor component is supported on both sides of the rotor disk.
  • the basic purpose of the rotor component is to prevent the entry of hot gas. There is usually no other function.
  • the storage of the rotor component is kept simple in a usual manner, with only an annular, axially extending portion engaging in a corresponding annular groove.
  • An unwanted rotation of the rotor component relative to the rotor disks is generally prevented by a press fit between the rotor component and one of the rotor disks in the engagement of the ring-shaped shoulder in the annular groove being present at at least one point.
  • the object of the present invention is therefore to rule out the relative movement between the rotor component and the rotor disks at least to the extent that this does not limit the life of the rotor.
  • the generic rotor is initially used for a gas turbine. Irrespective of this, however, it is also possible to use the embodiment of the rotor in another turbomachine, for example in a steam turbine.
  • At least the rotor has a first rotor disk and a second rotor disk that is directly and firmly connected to the first rotor disk.
  • the rotor disks each have a plurality of the respective rotor disc in each case axially penetrating vane holding grooves.
  • the blade holding grooves are used to hold moving blades.
  • first rotor disk radially below the blade holding grooves has a circumferential first ring projection that extends axially toward the second rotor disk.
  • second rotor disk radially below the blade retaining grooves has a circumferential, second ring projection that extends axially toward the first rotor disk.
  • An annular rotor component is arranged between the two rotor disks in the area of the blade holding grooves and / or radially below the blade holding grooves. This encloses the rotor located in sections within the rotor component, or sections of the two rotor disks.
  • the rotor component has a circumferential support section at both of its axial ends.
  • the first support section is located on the side facing the rotor axis below the first ring projection and the second support section is located radially below the second ring projection. It can be provided that the respective support section rests with a press fit on the ring projection or leaves a slight gap - with Ge ensuring the centering - to the ring projection.
  • a coupling between the rotor component of the first rotor disk is produced radially outside the ring projection, which prevents a relative displacement in the circumferential direction.
  • the first rotor disk has at least two first recesses arranged distributed around the circumference.
  • the rotor component has complementary second engagement shoulders, each of which engages in a corresponding first recess.
  • the first rotor disk has at least two first engagement shoulders distributed around the circumference.
  • the rotor component has complementary second recesses, so that the first engagement sections engage in the second recesses.
  • the embodiment of the invention causes a reliable coupling between the rotor component and the rotor disks, so that a relative movement is prevented even if a press fit is lost. In this respect, there can be no friction between the components and negatively affect the service life.
  • the rotor component has at one axial end an axially opening first ring groove surrounding the first ring projection and opposite at the other axial end axially opening second ring groove surrounding the second ring projection.
  • the flanks of the respective annular groove located on the side facing the rotor axis are formed by the support sections.
  • the centering of the rotor component relative to the rotor disks ben under the various operating states can be improved if a radially outer flank of the first annular groove is present on the first annular projection or a radially outer flank of the second annular groove is present on the second annular projection.
  • the first recesses in the first rotor disk and / or the second recesses in the rotor component can be realized differently.
  • the first rotor disk or the rotor component has a circumferential ring shoulder. Accordingly, the recess interrupts the circumferential ring shoulder.
  • the recess is delimited on both sides by portions extending in the circumferential direction.
  • an engagement shoulder is arranged on both sides of a respective recess. In so far as mutually adjacent in the circumferential direction, a first engagement shoulder of the first rotor disk engages in a second recess of the rotor component and a second engagement shoulder of the rotor component engages in a first recess of the first rotor disk.
  • first engagement sections in the first rotor disk are each positioned centrally between two blade holding grooves. Accordingly, it is advantageous if the first recesses are each arranged in an extension of the blade-holding grooves.
  • these advantageously have a length in the circumferential direction less than the smallest distance between two blade retaining grooves.
  • connection is arranged immediately above the ring projection.
  • the first rotor disk has the first engagement shoulders on the radially outward-facing side of the ring projection.
  • the second recesses in the rotor component are required.
  • the rotor component advantageously has a first annular groove, in which the first annular projection engages. Consequently, the recess is to be arranged on the radially outer flank of the annular groove. Since the first engagement shoulder and thus the second recess is preferably to be spaced from the axially free end of the ring projection. An additional burden is thus avoided by the second recess in the area of the groove base of the first annular groove.
  • the intervention paragraphs can be realized in different ways. A reliable connection with the engagement paragraphs is created if they are integrally formed with the first rotor disk or integrally with the rotor component.
  • the rotor component also has at least one circumferential, radially extending disk section. This is arranged at an axial end and can cover sections of the rotor disk and the blade holding grooves.
  • An advantageous stabilization of the rotor component, in particular the disk section and an advantageous securing of the connection between the rotor component and the rotor disks, is achieved when the disk section has a second area with a first material thickness in the axial direction and radially outside the first area an increased and at least 2 times material strength.
  • a thickening is advantageously arranged on the immediately adjacent side to form the second region. This leads to a centrifugal force due to the uneven mass distribution between the first area and the second area slight bending moment of the free end of the disc section facing the immediately adjacent rotor disc.
  • the arrangement of the second recesses and / or the second engagement shoulders on the rotor component takes place here in a particularly advantageous manner in the second region of the disc section.
  • Fig. 1 sections of the rotor in longitudinal section in the loading
  • FIG. 2 shows the first rotor disk for the embodiment from FIG. 1;
  • FIG. 3 shows the rotor component for the embodiment from FIG. 1;
  • Fig. 4 sectionally the rotor in longitudinal section in the loading
  • FIG. 5 shows the rotor component for the embodiment from FIG. 4;
  • FIG. 6 shows the first rotor disk for the embodiment from FIG. 4;
  • a rotor is sketched in a first exemplary embodiment in longitudinal section only in the area of the ro door component 11.
  • the further design of the rotor can be selected on the basis of customary embodiments.
  • At least the rotor has a first rotor disk 01 and a second rotor disk 06.
  • a circumferential, axially extending ring projection 03, 08 is arranged on each of these 01, 06.
  • Between the rotor disks 01, 06 is the rotor construction part 11, which 11 for attachment to the rotor disks 01,
  • the rotor component 11 has a radially extending disk section 20 around it.
  • the coupling between the rotor component 11 and the first ro tor disc 01 is in this embodiment in the radially outer region.
  • first rotor disk 01 in a perspective view. You can see the circumferential ring projection 03 and radially outside the blade retaining grooves 02 penetrating axially through the first rotor disk 01. Between two blade retaining grooves 02 there is a first engagement shoulder 05. Between two engagement portions 05 there is a corresponding first recess.
  • Fig. 3 shows the complementary rotor component 11. Again, the circumferential annular grooves 12, 17 can be seen with which are arranged on the side facing the rotor axis th support sections 13, 18.
  • the axially adjacent to the first rotor disc 01 radially at one end he stretching disc section 20 is divided into a ra dial inner first region and a radially outer second region, the second region having a cover 19 and thereby achieving at least twice the material thickness of the first region.
  • this embodiment Example arranged on the rotor member 11 second engagement shoulders 15 and the intermediate second recesses 14 arranged opposite to the detection 19 in the radially outer region.
  • FIG. 4 shows a rotor in a two exemplary embodiment.
  • the rotor has a first rotor disk 21 and a second rotor disk 26.
  • a circumferential, axially extending ring projection 23, 28 is arranged on each of these 21, 26.
  • the rotor construction part 31 which 31 for attachment to the rotor disks 21,
  • the rotor component 31 has a radially extending disk section 40 around it.
  • the coupling between the rotor component 31 and the first rotor disk 21 is located immediately radially outside the first ring projection 23.
  • FIG. 5 shows the rotor component 31 in perspective view. Again, the circumferential first annular groove 32 can be seen with the support sections arranged on the side facing the rotor axis. The one at one axial end un directly adjacent to the second rotor disk 26 radially he extending disk section 40 is analogous as previously leads.
  • the rotor component has a circumferential ring shoulder 35 on the radially outer side of the flank of the first annular groove 32 on the side facing the rotor axis.
  • This 35 is interrupted several times by in each case arranged circumferentially arranged second recesses 34.
  • 6 shows the first rotor disk 21 in a perspective view. The circumferential ring projection 23 and the blade retaining grooves 02 can be seen.
  • the first rotor disk 21 on the radially outer side on the first ring projection 23 has the first engagement shoulders 25 complementary to the second recesses 34.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un rotor d'une turbine à gaz pourvu de deux disques (01, 06) voisins, lesquels présentent une pluralité de rainures de retenue d'aube (02) réparties à la périphérie et destinées à loger des aubes mobiles et, radialement au-dessous des rainures de retenue d'aube (02), une partie saillante annulaire (03, 08) périphérique s'étendant axialement. Une pièce (11) de rotor périphérique se trouve entre les disques (01, 06) de rotor, fixée sur les parties saillantes annulaires (03, 08). Aux fins de blocage périphérique, le disque (01) de rotor ou la pièce (11) de rotor présente au moins deux évidements (14) ménagés de manière répartie à la périphérie, dans lesquels s'insèrent respectivement des épaulements d'insertion (15) de la pièce (11) de rotor ou du disque (01) de rotor.
EP19752935.7A 2018-08-02 2019-07-24 Rotor pourvu d'une pièce disposée entre deux disques de rotor Active EP3788236B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201862713572P 2018-08-02 2018-08-02
PCT/EP2019/069866 WO2020025406A1 (fr) 2018-08-02 2019-07-24 Rotor pourvu d'une pièce disposée entre deux disques de rotor

Publications (2)

Publication Number Publication Date
EP3788236A1 true EP3788236A1 (fr) 2021-03-10
EP3788236B1 EP3788236B1 (fr) 2023-06-21

Family

ID=67620379

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19752935.7A Active EP3788236B1 (fr) 2018-08-02 2019-07-24 Rotor pourvu d'une pièce disposée entre deux disques de rotor

Country Status (6)

Country Link
US (1) US11339662B2 (fr)
EP (1) EP3788236B1 (fr)
JP (1) JP7092938B2 (fr)
KR (1) KR102537955B1 (fr)
CN (1) CN112534119B (fr)
WO (1) WO2020025406A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20240084708A1 (en) * 2016-02-05 2024-03-14 Siemens Energy Global GmbH & Co. KG Rotor comprising a rotor component arranged between two rotor discs

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Also Published As

Publication number Publication date
KR20210031984A (ko) 2021-03-23
KR102537955B1 (ko) 2023-05-31
CN112534119A (zh) 2021-03-19
EP3788236B1 (fr) 2023-06-21
WO2020025406A1 (fr) 2020-02-06
JP7092938B2 (ja) 2022-06-28
US20210310359A1 (en) 2021-10-07
US11339662B2 (en) 2022-05-24
JP2021533304A (ja) 2021-12-02
CN112534119B (zh) 2023-04-14

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