EP3287595A1 - Rotor dote d'un anneau d'etancheite segmente - Google Patents

Rotor dote d'un anneau d'etancheite segmente Download PDF

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Publication number
EP3287595A1
EP3287595A1 EP16185591.1A EP16185591A EP3287595A1 EP 3287595 A1 EP3287595 A1 EP 3287595A1 EP 16185591 A EP16185591 A EP 16185591A EP 3287595 A1 EP3287595 A1 EP 3287595A1
Authority
EP
European Patent Office
Prior art keywords
rotor
sealing
support surface
rotor according
rotor disk
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.)
Withdrawn
Application number
EP16185591.1A
Other languages
German (de)
English (en)
Inventor
Peter Schröder
Fathi Ahmad
Karsten Kolk
Peter Kury
Mirko Milazar
Volker Vosberg
Vyacheslav Veitsman
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 AG
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
Priority to EP16185591.1A priority Critical patent/EP3287595A1/fr
Priority to PCT/EP2017/070153 priority patent/WO2018036818A1/fr
Publication of EP3287595A1 publication Critical patent/EP3287595A1/fr
Withdrawn legal-status Critical Current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
    • 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
    • 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

Definitions

  • the invention relates to a rotor of a gas turbine, wherein between the rotor blades of a first rotor disk and the rotor blades of a second rotor disk, a plurality of sealing segments are arranged distributed in the circumference.
  • sealing ring is formed by a plurality of individual distributed circumferentially arranged segments.
  • An exemplary embodiment is for this purpose in the EP 2 535 523 A2 specified.
  • sealing segments are used, which are supported on both sides in a region lying radially below the rotor blades on a circumferential annular surface on the rotor disk.
  • the annular surface on the rotor disk is in this case aligned facing the rotor axis, so that the centrifugal force leads to the sealing segment to a support on the annular surface of the rotor disk.
  • an axially opening receiving groove is present in an outer circumferential region of the sealing segment, into which a shoulder attached to the blade engages. This allows mounting of the sealing segment with its positioning in its final position and subsequent approach leading the adjacent blade with engagement of the paragraph in the receiving groove.
  • Object of the present invention is therefore to realize a seal between two rotor disks, both the seal from the fully assembled rotor should be removed and also when removing blades no disassembly or securing the sealing elements is required.
  • a rotor according to the invention is used in particular for use in a gas turbine. Nevertheless, the solution according to the invention can be applied to a rotor of a steam turbine or other turbomachine. At least it requires a first rotor disk and a second rotor disk. It is provided that a plurality of first rotor blades are distributed in the circumference of the first rotor disk. Likewise, the second rotor disk likewise has a plurality of second rotor blades distributed in the circumference. How the assembly of the blades takes place on the respective rotor disk, initially irrelevant.
  • the rotor comprises a sealing ring formed from sealing segments, which extends between the first rotor disk and the second rotor disk.
  • the first rotor disk has a rotor axis facing first support surface and the second rotor disk analogous to the rotor axis facing second support surface.
  • the invention provides that the first rotor disk has an outwardly facing first bearing surface on which a first resting surface of the respective sealing segment comes into abutment.
  • the shaping of contact and resting surface is initially insignificant, as long as it is ensured that with a radially inwardly pointing force on the sealing segment - for example, when the rotor with horizontal rotor axis due to its gravity at a position above the rotor axis - a support of the sealing segment over whose resting surface takes place on the bearing surface.
  • a displacement of the sealing segment in the radial direction can be prevented directly by the rotor disk.
  • a second Resting surface is arranged, wherein analogous to the investment of the first resting surface on the first bearing surface by abutment of the second resting surface on the second bearing surface is supported on both sides a support of the sealing segment, so that a radial displacement can be prevented.
  • blade receiving grooves are advantageously present for receiving the rotor blades, which extend in a particularly advantageous manner (parallel or inclined or arcuate) along the rotor axis on both sides to an end face of the respective rotor disk.
  • the shape of the support surface taking into account the inclusion of the centrifugal forces and the support surface is initially arbitrary, it is advantageous if the support surfaces and / or the support surfaces are designed as a rotation surface. This may be both a continuous surface of revolution as it is also permissible if the support surface and / or the support surface of spaced apart surfaces of a surface of revolution are formed. Particularly preferred as a surface of revolution, a cylindrical surface or a conical surface is selected with an angle to the rotor axis of less than 15 °.
  • the support surfaces of the first rotor disk and the second rotor disk are either designed as a closed surface of revolution or have radially symmetrical partial surfaces.
  • the bearing surfaces are also arranged radiärsymmetrisch with common consideration of all sealing segments advantageous.
  • a defined position of the sealing segments in the axial direction can be realized in different ways.
  • the support surfaces and the complementary thereto load surfaces sufficiently conical, so that a self-centering between the opposite load surfaces of the first rotor disk and the second rotor disk takes place.
  • the first rotor disk has a first end face extending approximately transversely to the rotor axis and the second rotor disk has a second end face extending approximately transversely to the rotor disk, the first end face being in a particularly advantageous manner located opposite the second end face.
  • the sealing segment has a first collar surface which essentially comes to rest on the first end face and a second collar face which essentially comes to rest on the second end face.
  • the shape of the end face and the collar surface is irrelevant, provided that an axial centering of the sealing segment.
  • the end face can be formed, for example, by bead-like, axially extending elevations.
  • the survey can be performed both annular and also a plurality of radially extending surveys can be used.
  • the opposite end faces are made similar, as it is also not necessary that the sealing segment axially opposite collar surfaces are made similar.
  • a minimum clearance is provided between the end faces and the collar surfaces, so that an unproblematic mounting of the sealing segment between the end faces is possible, without causing a jamming during assembly.
  • the arrangement of the support surface can be done in different positions. Particularly advantageous in this case is the arrangement of the support surface on an approximately (corresponding to the shape of the support surface) axially to the opposite rotor disc extending mounting projection. Consequently forms an edge of the fastening projection facing the rotor axis, the support surface.
  • the opposite end of the rotor disk facing the support surface forms a free end of the mounting projection.
  • the free end of the fastening projection is arranged on an end face of the rotor disk forming the end of the blade retaining grooves. In a particularly advantageous manner, the fastening projection extends beyond the front side.
  • the bearing surface can be formed by an edge of a mounting projection extending to the opposite rotor disk.
  • the support surface and the support surface may be the same fastening projection with an edge facing the rotor axis as a support surface and a radially outwardly facing edge of the rotor axis as a support surface as well as the arrangement of two separate mounting projections is possible.
  • a first fastening projection of the first rotor disk to form the first supporting surface is closed in a ring shape.
  • a bearing of the load surface of the sealing segments on the support surface of the rotor disc is made possible regardless of the position of the sealing segments in the circumferential direction.
  • the annular first fastening projection has interruptions (for example required clearances for other functions) which have no influence on the position of the sealing segments in the circumferential direction with an engagement of the load surface on the supporting surface.
  • a second attachment projection on the second rotor disk for forming the second support surface has at least two mutually spaced projection portions.
  • the second fastening projection has at least two interruptions which separate the projection sections from each other. The interruptions allow an advantageous installation of the sealing segments. It can be provided that a projection portion has an extension in the circumferential direction, which is smaller than the length of the sealing segment in the circumferential direction, in contrast, the second projection portion are guided over the substantially remaining circumference of the fastening projection.
  • the projection sections are each located between two blade retaining grooves.
  • the first attachment projection may also have a plurality of projection portions as an alternative to the annular embodiment as well.
  • the first load surface can be formed in a particularly advantageous manner by a first attachment paragraph, which extends over at least 75% of the length of the sealing segment in the circumferential direction. It is initially irrelevant whether the first attachment paragraph is carried out continuously or whether the first load surface is continuously present or whether the first load surface in this case has interruptions, provided that its partial surfaces together correspond to at least 75% of the length of the sealing segment.
  • the second load surface is likewise advantageously formed by a second fastening shoulder which, contrary to the advantageous embodiment of the first fastening shoulder, extends over a length of at least 75% of the length of the sealing segment in the circumferential direction.
  • the length of the second attachment paragraph with the second load surface is at least 25% of the length of the sealing segment in the circumferential direction.
  • the second attachment paragraph extends continuously with the second load surface.
  • the second attachment paragraph divides on at least two spaced apart paragraph sections.
  • the interruption of the second attachment paragraph allows in a particularly advantageous manner, the assembly of the sealing segment on the rotor disk at the same time interrupted second mounting projection.
  • the particularly advantageous embodiment of the rotor disks and the sealing segments leads to a possible mounting of the sealing segments with an obliquely axial radial insertion of the Sealing segments on the first rotor disc, so that the first load surface on the first support surface comes into abutment, wherein subsequently pivoting about the first load surface or first support surface, so that the paragraph sections can pass the sealing segment through the interruptions in the mounting projection, with subsequent rotation of the sealing segments in the circumferential direction relative to the second rotor disk joining the heel portions under the projection portions.
  • At least one blade is provided in a particularly advantageous manner with a blocking element which engages between two shoulder portions on the sealing segment.
  • a particularly advantageous embodiment of the sealing segments is given if they have on their radially outwardly facing side a sealing surface which extends substantially between the respective outer periphery of the rotor discs.
  • the shape of the sealing surface is initially irrelevant, and it is further advantageous if the sealing surface is shaped such that the flow through the gas turbine substantially through the blades and vanes takes place and a deviating flow along the sealing surface is prevented as far as possible.
  • the sealing surface may have a plurality of radial elevations.
  • sealing segment at one end in the circumferential direction radially from an outer Peripheral surface, that is, the sealing surface, set back inner paragraph.
  • an inner shoulder covering outer shoulder is arranged on the adjacent sealing element.
  • the sealing segments have the inner shoulder at one end in the direction of contact and the outer shoulder in the circumferential direction at the other end.
  • a first sealing segment which has at both opposite ends an inner recessed from the outer peripheral surface paragraph, while a second sealing element on both sides opposite in the circumferential direction has an outer shoulder.
  • a sealing strip extending in the axial direction over the width of the sealing segment is used. It can be provided on the one hand, that the sealing strip extends axially and in the circumferential direction and engages in opposite end faces.
  • a radially outwardly opening sealing receptacle in which an axially and radially extending sealing strip is arranged.
  • the sealing strip rests against an underside facing the rotor axis of the outer shoulder.
  • sealing strips are arranged between the blades and the sealing segments. It can be provided both that the sealing strip is annular, ie in the manner of a piston ring, executed across all sealing segments away. In order not to hinder the assembly is advantageously the Each sealing strip is designed in the length of the individual sealing segments. It is provided that the sealing strips engage in receiving grooves in the sealing element and come to rest on the blade.
  • a respective collar is arranged on the moving blade, which overlaps an axially extending shoulder on the sealing segment.
  • the sealing strip is placed between the shoulder of the sealing segment and the collar on the blade.
  • the sealing segment can be designed differently in a longitudinal section considered, wherein in a first advantageous embodiment, the sealing segment is designed substantially beam-shaped. This is considered a rectangle, which surrounds the sealing segment in longitudinal section. The rectangle is aligned parallel to a connecting line between the load surfaces.
  • the circumscribing rectangle has a height of at most 50% in relation to the width of the rectangle. Particularly advantageous is an aspect ratio with a height of at most 30% in relation to the width. As a result, a large clearance is created below the sealing segment or only a very small radial height required.
  • the first support surface is positioned on the first rotor disk and the second support surface on the second rotor disk with the same distance as possible to the rotor axis and with the same radial distance as possible to the outer periphery of the respective rotor disk. That is, with the same diameter of the rotor disks, the second support surface (possibly mirrored and) is positioned offset axially relative to the first support surface.
  • the first fastening projection on the first rotor disk and the second fastening projection on the second rotor disk are advantageously formed in each case by individual projection sections, which are each arranged between the blade retaining grooves on the rotor disks.
  • the sealing segment is viewed in a longitudinal section through the rotor axis substantially L-shaped.
  • the sealing segment has a short leg extending approximately in the axial direction and a short leg extending radially to the rotor axis transversely to the long leg.
  • first support surface on the first rotor disk below the blade retaining grooves, so that a radially encircling first fastening projection can be realized.
  • second fastening projection is in turn arranged analogous to previous embodiments near the outer periphery of the second rotor disk.
  • FIG. 1 a first embodiment of a rotor according to the invention is schematically sketched. Shown here is only essential for the invention range with the sealing segment 31 in arrangement between a first rotor disk 01 and a second rotor disk 02. On the first rotor disk 01 are distributed in the periphery a plurality of first blades 21 and on the second rotor disk 02 a plurality of second blades 22 are distributed distributed around the circumference.
  • FIG. 2 This outlines the FIG. 2 the execution FIG. 1 as an exploded view.
  • a blade retaining groove 03 and a retaining profile 23 of the first rotor blade 21 arranged in the blade retaining groove 03 can be seen.
  • the blade retaining groove 03 and the retaining profile 23 extend parallel to the rotor axis.
  • the rotor disk 01 has on the outer circumference an axially extending fastening projection 07, which 07 is interrupted by the individual blade retaining grooves 03.
  • a plurality of projection portions for realizing the fastening projection 07 are distributed in the circumference.
  • the fastening projection 07 on the one hand forms the support surface 11 facing the rotor axis.
  • the end face 17 facing the second rotor disk 02 serves to realize a contact of the sealing segment 31 in the axial direction.
  • the first rotor disk 01 has a support ring 13, which 13 also extends axially facing the second rotor disk 02.
  • this 13 serves with a radially outwardly facing support surface 15 for supporting the sealing segment 31, in particular when the rotor is at rest.
  • the second rotor disk 02 also has a blade retaining groove 04, in which the retaining profile 24 of the rotor blade 22 is received.
  • this embodiment of the second rotor disk 02 has a fastening projection 08 extending axially to the first rotor disk 01 adjacent to the outer circumference.
  • this attachment projection 08 analogously realizes a support surface 12 on the side pointing toward the rotor axis, and furthermore the attachment projection 08 on the side pointing radially outwards forms a bearing surface 16 for supporting the sealing segment 31.
  • the sealing segment 31 is designed substantially in the manner of a beam and has a sealing surface 32 on the side pointing radially outwards. Although in this illustration, the sealing surface 32 is shown in a straight line, so this is to be provided in reality for optimal flow seal with surveys.
  • this 31 has a fastening shoulder 37, 38 on the two axially opposite sides. These 37, 38 each form a load surface 41 or 42 with a radially outwardly pointing flank.
  • the sealing segment 31 is supported on the respective support surfaces 11, 12 via the load surface 41, 42.
  • a resting surface 45 which is formed by a flank facing the rotor axis of the first attachment paragraph 37 of the sealing segment 31, on the supporting surface 15 formed by the first rotor disk 01.
  • a support web 44 is arranged, which also has a resting surface 47 on the side facing the rotor axis 44, which in turn comes to rest on the bearing surface 16 of the second rotor disk 02.
  • a fixing in the axial direction is achieved by a first collar surface 47 of the sealing segment 31 comes to rest on the first end face 17 of the first rotor disk 01 and opposite a second collar surface 48 of the sealing segment 31 comes to rest on a second end face 18 of the second rotor disk 02.
  • the sealing with respect to the rotor blades 21, 22 is advantageously realized by arranging on the rotor blades 21, 22 in each case a collar 25, 26 extending in sections over the sealing segment 31.
  • the sealing strip 35, 36 can slightly protrude from the receiving groove in the sealing segment 31, whereby a contact is made on the respective collar 25, 26 of the moving blade 21, 22.
  • the first attachment shoulder 37 has at least one interruption, wherein the remaining shoulder portions of the attachment shoulder 37 correspond to the width of the blade retention grooves 03 between the respective projection portions of the attachment projection 07.
  • the second attachment paragraph 38 is performed analogously to the first attachment paragraph 37 with at least one interruption, so that the sealing segment 31 can be mounted in a bayonet.
  • the sealing segment 31 is positioned such that the heel portions of the first attachment paragraph 37 and the heel portions of the second attachment paragraph 38 between the projection portions of the first attachment projection 07 and the second attachment projection 08 can be passed through until an investment of the rest surfaces 35 and 36 on the Support surfaces 15 and 16 is given.
  • the first attachment paragraph 37 is carried out essentially continuously, so that at least no bayonet-type mounting is possible on this side.
  • the sealing segment 31 is inserted in an inclined orientation initially with the first attachment paragraph 37 between the attachment projection 07 and the support ring 13.
  • the position of the sealing segments 31 in the circumferential direction is secured by a blocking element 28 arranged on at least one moving blade 22, which element 28 dips in between two shoulder portions of the second fastening shoulder 38.
  • FIG. 3 an alternative embodiment for a seal according to the invention in a rotor is schematically sketched.
  • the second rotor disk 02 with the second blades 22 is designed in accordance with the first embodiment and to that extent is omitted description.
  • the first rotor disk 51 in turn has blade retaining grooves 53, in which 53 the respective retaining profile 73 of the respective blade 71 is arranged.
  • the blade 71 has a collar 75 extending in sections over the sealing segment 81.
  • a receiving ring groove 59 which opens axially relative to the second rotor disk 02, is introduced into the first rotor disk 51 below the blade retaining groove 53, on which the first fastening projection 57 is located radially outward.
  • This 57 forms the supporting surface 61 facing the rotor axis.
  • the free end of the fastening projection 57 forms an end face 67 for bearing the sealing segment 81 in the axial direction.
  • the receiving ring groove 59 further forms with a flank the bearing surface 65 pointing away from the rotor axis.
  • the sealing segment 81 used for this purpose is L-shaped and has an axially extending leg and a radially extending to the rotor axis leg. At the radially lower end of the second leg is in turn the axially extending mounting shoulder 87, on whose 87 radially outwardly facing side, the load surface 91 is arranged. An edge of the first fastening shoulder 87 facing the rotor axis analogously forms the resting surface 95. Above the first fastening shoulder 87 there is a collar surface 97 for engagement with the end face 67.
  • the first fastening shoulder 87 is implemented continuously over the length of the sealing segment 81.
  • the receiving ring groove 59 and the fastening projection 57 are executed circumferentially. This allows a particularly stable connection of the sealing segment 81 to the first rotor disk 51.
  • the sealing segment 81 is pivoted in, as in the first exemplary embodiment in the second variant.
  • the sealing segment 81 is slid inclined with the first attachment paragraph 87 in the receiving groove 59.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP16185591.1A 2016-08-25 2016-08-25 Rotor dote d'un anneau d'etancheite segmente Withdrawn EP3287595A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP16185591.1A EP3287595A1 (fr) 2016-08-25 2016-08-25 Rotor dote d'un anneau d'etancheite segmente
PCT/EP2017/070153 WO2018036818A1 (fr) 2016-08-25 2017-08-09 Rotor muni d'une bague d'étanchéité segmentée

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16185591.1A EP3287595A1 (fr) 2016-08-25 2016-08-25 Rotor dote d'un anneau d'etancheite segmente

Publications (1)

Publication Number Publication Date
EP3287595A1 true EP3287595A1 (fr) 2018-02-28

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ID=56800210

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16185591.1A Withdrawn EP3287595A1 (fr) 2016-08-25 2016-08-25 Rotor dote d'un anneau d'etancheite segmente

Country Status (2)

Country Link
EP (1) EP3287595A1 (fr)
WO (1) WO2018036818A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020025406A1 (fr) * 2018-08-02 2020-02-06 Siemens Aktiengesellschaft Rotor pourvu d'une pièce disposée entre deux disques de rotor
CN114599859A (zh) * 2019-10-18 2022-06-07 西门子能源全球有限两合公司 具有设置在两个转子盘之间的转子构件的转子
US12037926B2 (en) 2020-06-18 2024-07-16 Siemens Energy Global GmbH & Co. KG Rotor comprising a rotor component arranged between two rotor discs

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2256300A2 (fr) * 2009-05-15 2010-12-01 United Technologies Corporation Ensemble de joint à léchettes et étage rotorique associé
EP2535523A2 (fr) 2011-06-17 2012-12-19 General Electric Company Système d'étanchéité de turbine et procédé de son assemblage
DE102014115197A1 (de) * 2013-10-28 2015-04-30 General Electric Company Dichtungsbauteil zur Reduktion von sekundärer Luftströmung in einem Turbinensystem
CA2921257A1 (fr) * 2015-02-20 2016-08-20 General Electric Company Joint d'etancheite inter etage de turbine multi etage a auget et methode d'assemblage

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2256300A2 (fr) * 2009-05-15 2010-12-01 United Technologies Corporation Ensemble de joint à léchettes et étage rotorique associé
EP2535523A2 (fr) 2011-06-17 2012-12-19 General Electric Company Système d'étanchéité de turbine et procédé de son assemblage
DE102014115197A1 (de) * 2013-10-28 2015-04-30 General Electric Company Dichtungsbauteil zur Reduktion von sekundärer Luftströmung in einem Turbinensystem
CA2921257A1 (fr) * 2015-02-20 2016-08-20 General Electric Company Joint d'etancheite inter etage de turbine multi etage a auget et methode d'assemblage

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020025406A1 (fr) * 2018-08-02 2020-02-06 Siemens Aktiengesellschaft Rotor pourvu d'une pièce disposée entre deux disques de rotor
CN112534119A (zh) * 2018-08-02 2021-03-19 西门子能源全球有限两合公司 具有设置在两个转子盘之间的转子构件的转子
US11339662B2 (en) 2018-08-02 2022-05-24 Siemens Energy Global GmbH & Co. KG Rotor comprising a rotor component arranged between two rotor disks
CN114599859A (zh) * 2019-10-18 2022-06-07 西门子能源全球有限两合公司 具有设置在两个转子盘之间的转子构件的转子
JP2022552170A (ja) * 2019-10-18 2022-12-15 シーメンス エナジー グローバル ゲゼルシャフト ミット ベシュレンクテル ハフツング ウント コンパニー コマンディートゲゼルシャフト ２つのロータディスクの間に配置されたロータコンポーネントを有するロータ
CN114599859B (zh) * 2019-10-18 2023-11-17 西门子能源全球有限两合公司 具有设置在两个转子盘之间的转子构件的转子
US12037926B2 (en) 2020-06-18 2024-07-16 Siemens Energy Global GmbH & Co. KG Rotor comprising a rotor component arranged between two rotor discs

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