EP3521561A1 - Rotor pourvu d'élément d'étanchéité et de bague d'étanchéité - Google Patents

Rotor pourvu d'élément d'étanchéité et de bague d'étanchéité Download PDF

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Publication number
EP3521561A1
EP3521561A1 EP18154881.9A EP18154881A EP3521561A1 EP 3521561 A1 EP3521561 A1 EP 3521561A1 EP 18154881 A EP18154881 A EP 18154881A EP 3521561 A1 EP3521561 A1 EP 3521561A1
Authority
EP
European Patent Office
Prior art keywords
rotor
sealing
inner edge
edge portion
facing
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Withdrawn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
EP18154881.9A
Other languages
German (de)
English (en)
Inventor
Peter Schröder
Dirk Springborn
Karsten Kolk
Peter Kury
Yulia Bagaeva
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 EP18154881.9A priority Critical patent/EP3521561A1/fr
Priority to CN201980011393.7A priority patent/CN111670292B/zh
Priority to KR1020207024898A priority patent/KR102455245B1/ko
Priority to JP2020541886A priority patent/JP7026809B2/ja
Priority to EP19701772.6A priority patent/EP3695100B1/fr
Priority to PCT/EP2019/050247 priority patent/WO2019149474A1/fr
Priority to US16/957,223 priority patent/US11319823B2/en
Publication of EP3521561A1 publication Critical patent/EP3521561A1/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Withdrawn legal-status Critical Current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
    • 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
    • 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
    • F01D5/025—Fixing blade carrying members on shafts
    • 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
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/24—Rotors for 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • 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
    • F05D2240/55—Seals
    • F05D2240/58—Piston ring seals
    • 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 rotor having a rotor disk on which a plurality of rotor blades can be mounted distributed over the circumference and a plurality of sealing elements arranged on one end side, by means of which a covering of the blade retaining grooves required for receiving the rotor blades takes place.
  • rotors are known from the prior art, which have a rotor disk with blades and sealing plates.
  • the rotor disk on the outer circumference distributed Schaufelhaltenuten, in each of which a blade is attached with a blade root.
  • the blades have radially outside the rotor disk on a paddle platform, which extends in the circumferential direction in each case to the subsequent blade platform.
  • On one or both end sides of the rotor disk there are sealing sheets for covering the blade holding grooves, which in particular are intended to effect a separation between a hot gas flowing along the rotor and a cooling air flowing in the interior of the rotor blades.
  • the sealing plates are mounted in a known manner in an inner annular groove on the rotor disk and in an outer annular groove formed by the rotor blade.
  • the object of the bearing of the sealing plate in the annular groove is in particular the sealing of the area between the sealing plate and the rotor disk to the opposite region of the sealing plate.
  • sealing plates are further fastened by means of a hooking on the rotor disk.
  • the rotor disk between the blade retaining grooves and the sealing plates corresponding to each other complementary interlocking means. This improves the axial fixation of the sealing plates on the rotor disk.
  • Object of the present invention is therefore to allow axial fixation of the sealing plates, without the arrangement of an annular groove in the rotor disk is necessary.
  • the generic rotor is used in particular for use in a gas turbine. Independently of this, the embodiment can likewise be used for other types of rotors, for example for a steam turbine.
  • At least the rotor comprises a rotor disk, which has distributed on the outer circumference arranged a plurality of blade retaining grooves.
  • the blade retaining grooves extend in the axial direction parallel to the rotor axis or in a direction inclined thereto or has an arcuate course mainly in the axial direction.
  • the blade retaining grooves are each intended for receiving blades.
  • the rotor disc has a plurality of circumferentially distributed mounting projections, which extend axially from an end face of the rotor disk.
  • the fastening projections are arranged between adjacent blade retaining grooves.
  • the rotor comprises a rotor component adjacent to the rotor disk.
  • the rotor component can be a rotor disk provided with rotor blades or another rotor disk without rotor blades or a rotor component that surrounds the rotor axis in an annular manner, which can be embodied in one piece or in a segmented manner.
  • At least the rotor component is mounted immediately adjacent to the rotor disk.
  • the rotor component in this case has a circumferential sealing portion, which is arranged on the rotor disc facing side and on the radially outwardly facing side.
  • the generic embodiment of the rotor comprises a plurality of circumferentially distributed sealing elements, which cover the blade holding grooves at least in sections in front of an end face of the rotor disk.
  • the sealing elements For fastening the sealing elements to the rotor disk in at least the axial direction, it is provided that the sealing elements have holding projections extending axially to the end face. It is provided that the retaining projections are attached to the mounting projections, so that at least one axial fixation takes place.
  • the sealing element adjoins the sealing section with an inner edge section, wherein a sealing gap is formed between the inner edge section and the sealing section.
  • a receiving space for the arrangement of a sealing ring is now formed for sealing between the inner edge portion and the sealing portion.
  • the receiving space is limited on the radially outwardly facing side of the inner edge portion and on the rotor axis facing side of the sealing portion.
  • a one-piece or multi-part sealing ring is arranged, which causes a seal of the sealing gap between the two components in contact with at least one boundary of the receiving space by the sealing portion and a boundary by the inner edge portion.
  • An advantageous rotor further comprises a plurality of blades, which are arranged distributed in the circumference on the rotor disk.
  • the blades are each secured with a blade root in the corresponding Schaufelhaltenuten.
  • the rotor blades have a blade platform adjoining the blade root, which covers the rotor disk in sections and in this case extends beyond one end face of the rotor disk.
  • An airfoil is located radially outwardly of the blade platform.
  • a ring segment groove opening toward the rotor axis is arranged in a section projecting beyond the end face.
  • the sealing element is received in the Ringsegmentnut with an outer, radially outwardly facing edge portion.
  • a limited axial displacement in this regard is understood to mean a path which, with respect to the order of magnitude, corresponds to approximately half the thickness of the inner edge portion.
  • the fastening shoulder is displaceable relative to the fastening projection by a distance which corresponds at least to 0.2 times the thickness of the inner edge section. Furthermore, it is advantageous if a relative displacement of at most 0.5 times the thickness of the inner edge section is to be expected as intended, wherein at the same time the rotor component is displaceable relative to the rotor disk by the corresponding path. In this case, it is particularly advantageous if the axial displaceability of the rotor component relative to the rotor disk corresponds to the maximum permissible displacement of the sealing portion relative to the inner edge portion while maintaining the sealing function.
  • the sealing ring is particularly advantageous if it is designed in the manner of a piston ring. In order to enable assembly of the rotor, in particular to carry out a replacement of the sealing ring during maintenance can also be provided to perform the sealing ring in two parts.
  • the sealing portion is provided with an inner step shoulder.
  • the sealing portion has a radially outwardly extending sealing flank, which causes the axial boundary of the receiving space, wherein the sealing ring is arranged in the inner stepped shoulder.
  • the arrangement of the sealing flank takes place here in a particularly advantageous manner on the side facing away from the rotor disk and, accordingly, the inner stepped shoulder is located on the side facing the rotor disk.
  • the sealing portion wherein the sealing ring rests on the cone and thus is limited axially in one direction in the movement.
  • the cone is designed such that when the distance between the sealing portion is smaller relative to the rotor axis, an approach to the rotor disk.
  • the boundary of the receiving space can be realized by the inner edge portion on the opposite axial side in different ways.
  • the inner edge portion is provided with an outer stepped shoulder.
  • the inner edge portion has a pointing to the rotor axis extending edge edge, which causes the axial boundary of the receiving space, wherein in the outer stepped shoulder of the sealing ring is arranged.
  • the arrangement of the edge flank takes place in a particularly advantageous manner on the side facing the rotor disk and, accordingly, the outer stepped shoulder is located on the side facing away from the rotor disk side.
  • the cone is designed such that when the distance between the sealing portion is smaller relative to the rotor axis, an approach to the rotor disk.
  • the execution of the sealing ring depends on the design of the inner edge portion and the sealing portion with an inner and / or outer stepped shoulder or with its conical design.
  • it is particularly advantageous in conical sealing portion when the sealing ring is designed to be complementary conical on the side facing the rotor axis.
  • the sealing ring is at a conical inner edge portion. Accordingly, it is particularly advantageous if the sealing ring is carried out on the radially outwardly facing side complementary conical. Alternatively, it is also possible in the sealing ring on the radially outwardly facing side to perform crowned.
  • the reliable position of the sealing ring in the receiving space is ensured if the sealing ring can reliably support the inner edge section when centrifugal forces occur. If the cross section is considered by the sealing ring, then the center of gravity is in each intended state of the rotor radially below the inner edge portion, so that the centrifugal force of the sealing ring is supported directly on the inner edge portion without additional bending moments and shear forces occur in the sealing ring.
  • fastening projection in the form of a radially outwardly extending hook and the retaining projection in the form of a hook extending to the rotor axis are formed.
  • the interlocking hook of fastening projection and retaining projection axial fixation is achieved.
  • This embodiment favors a particularly simple assembly of the sealing plate with an insertion onto the rotor axis zu josd in the receiving groove on the rotor disk and at the same time of the retaining projection in the fastening projection.
  • fastening projection in the form of a hook extending to the rotor axis and analogously to the retaining projection in the form of a radially outwardly extending hook.
  • retaining projection in the form of a radially outwardly extending hook.
  • both embodiments can be combined by the retaining projection or the fastening projection has a T-shaped profile, which is clasped by a C-shaped fastening projection or retaining projection.
  • an embodiment in the manner of a dovetail connection can be selected.
  • the receiving space in conjunction with the dimensions of the sealing ring allows a radial clearance
  • a sufficient clearance is provided in addition to the sealing portion, so that first the sealing element is arranged with the inner edge portion in the free space and then with a radially outwardly facing movement with simultaneous pivoting of the sealing element about the retaining projection a joint of the retaining projection on the fastening projection and advantageously a conditioning of the outer edge portion takes place on the blade platform.
  • the necessary space for pivoting the inner edge portion can be created by a radial clearance of the sealing ring in the receiving space.
  • a radial fixation of the sealing plate can be done in different ways, wherein in a first simple and advantageous embodiment, an abutment of the outer edge portion with a radially outwardly facing end face on the blade platform, i. at the groove bottom of the ring segment, is provided. In this respect, centrifugal forces are first transferred from the sealing plate to the blade platform.
  • the stable attachment of the sealing element to the rotor disk, in particular in the connection of the retaining projection on the fastening projection, is favored if the two edges of the sealing element are located in the circumferential direction in the region between two blade retaining grooves. This allows the retaining projection to be hooked to two adjacent fastening projections spaced apart by a blade retaining groove. Likewise, it is possible in this case to provide on a sealing element two circumferentially spaced retaining projections.
  • the sealing element is also secured in the radial direction. If this is not already given by the opposite support of the inner edge portion on the sealing ring and the sealing ring on the sealing portion and the outer edge portion in the Ringsegmentnut or by the engagement of the retaining projection on the mounting projection, it is advantageous if a securing element is used, which prevents a radial displacement of the sealing element, in particular pointing towards the rotor axis.
  • the securing element by means of the securing element, the fuse in the radial direction and at the same time in the circumferential direction. Embodiments thereof are known to those skilled in the art and can be suitably applied.
  • the invention relates to a sealing element which is intended for use with a previously described rotor and is carried out as described above.
  • a first embodiment of a rotor according to the invention is outlined.
  • a rotor disk 01 which has 01 circumferentially arranged blade holding grooves 02.
  • the rotor disk 01 has a fastening projection 05 which is embodied in the form of a hook pointing radially outwards.
  • a rotor component 11 Adjacent to the rotor disk 01 there is a rotor component 11 fastened to the rotor disk 01, a gap 07 being located between the components 01, 11.
  • the two components 01, 11 can shift relative to one another by a small distance. This serves, in particular, to compensate for different thermal expansions in the rotor with the rotor disk 01 and the rotor component 11.
  • the sealing elements 21 which are distributed in the circumference in front of the blade retaining grooves 02 on the rotor disk 01, can be seen.
  • the sealing elements 21 in this embodiment a holding projection 25, which 25 is designed in the form of a radially pointing to the rotor axis hook.
  • fastening projection 05 and retaining projection 25 By the engagement of fastening projection 05 and retaining projection 25, the axial fixation of the sealing elements 21 is effected.
  • the seal between the sealing plates 21 and the rotor member 11 is shown in detail.
  • the rotor disk 01 with the adjacently arranged rotor component 11 can be seen again.
  • the sealing element 21 is located in front of an end face of the rotor disk 01.
  • the sealing element 21 adjoins a sealing portion 13 of the rotor component 11 with an inner edge portion 23.
  • a sealing ring 31 is inserted for sealing between the two components 11, 21, a sealing ring 31 is inserted.
  • the sealing portion 13 on an inner shoulder 14.
  • the inner shoulder 14 is delimited on the side facing away from the rotor disk 01 by a sealing flank 15.
  • the inner edge section 23 of the sealing element 21 has a conical sealing surface 24.
  • the conical sealing surface 24 is in this case aligned such that the distance from the rotor axis of the sealing edge 15 decreases technological.
  • a limited receiving space 16 is formed for the arrangement of the sealing ring 31, wherein the receiving space 16 is limited on the rotor axis facing side and on the side facing away from the rotor disk 01 side of the sealing portion 13 and on the radially outwardly facing side and in the direction of the rotor disk 01st pointing away from the inner edge portion 23 is limited.
  • sealing ring 31 can move within the receiving space 16 limited, however, a contact of the sealing ring 31 on the conical sealing surface 24 and on the sealing edge 15 takes place upon rotation of the rotor and thus a seal between the sealing element 21 and Rotor component 11 is effected.
  • Fig. 3 is a further embodiment for sealing between the sealing elements 61 and a rotor member 51 analogous to the illustration Fig. 2 outlined.
  • the rotor disk 01 with the adjacent rotor component 51 can be seen in turn.
  • the sealing elements 61 are in turn located in front of the end face of the rotor disk 01.
  • the rotor component 51 has a sealing section 53 on the side facing the sealing element 61, with a conical section 53 Sealing surface 54 is provided.
  • the sealing element 61 has an outer shoulder 64 delimited at the inner edge section 63 by a peripheral edge 65 arranged on the side facing the rotor disk 01.
  • a receiving space 56 delimited by the sealing section 53 and the inner edge section 63 is again formed.
  • the sealing ring 71 is arranged. Likewise, the sealing ring 71 can move limited in the receiving space 56, wherein a seal is effected during operation. On the one hand, this is effected as before by the rotation of the rotor, whereby a secure contact of the sealing ring 71 takes place on the outer shoulder 64.
  • the space between the rotor disk 01 and the sealing element 61 flows through cooling air at a higher pressure than on the opposite side of the sealing element 61. This increased pressure of the cooling air furthermore causes a reliable contact of the sealing ring 71 on the conical sealing surface 54.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Sealing Devices (AREA)
EP18154881.9A 2018-02-02 2018-02-02 Rotor pourvu d'élément d'étanchéité et de bague d'étanchéité Withdrawn EP3521561A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP18154881.9A EP3521561A1 (fr) 2018-02-02 2018-02-02 Rotor pourvu d'élément d'étanchéité et de bague d'étanchéité
CN201980011393.7A CN111670292B (zh) 2018-02-02 2019-01-07 具有密封元件和密封环的转子
KR1020207024898A KR102455245B1 (ko) 2018-02-02 2019-01-07 밀봉 요소 및 밀봉 링을 갖는 회전자
JP2020541886A JP7026809B2 (ja) 2018-02-02 2019-01-07 シール要素及びシールリングを具備するロータ
EP19701772.6A EP3695100B1 (fr) 2018-02-02 2019-01-07 Rotor pourvu d'élément d'étanchéité et de bague d'étanchéité
PCT/EP2019/050247 WO2019149474A1 (fr) 2018-02-02 2019-01-07 Rotor comprenant un élément d'étanchéité et une bague d'étanchéité
US16/957,223 US11319823B2 (en) 2018-02-02 2019-01-07 Rotor with sealing element and ring seal

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP18154881.9A EP3521561A1 (fr) 2018-02-02 2018-02-02 Rotor pourvu d'élément d'étanchéité et de bague d'étanchéité

Publications (1)

Publication Number Publication Date
EP3521561A1 true EP3521561A1 (fr) 2019-08-07

Family

ID=61157083

Family Applications (2)

Application Number Title Priority Date Filing Date
EP18154881.9A Withdrawn EP3521561A1 (fr) 2018-02-02 2018-02-02 Rotor pourvu d'élément d'étanchéité et de bague d'étanchéité
EP19701772.6A Active EP3695100B1 (fr) 2018-02-02 2019-01-07 Rotor pourvu d'élément d'étanchéité et de bague d'étanchéité

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP19701772.6A Active EP3695100B1 (fr) 2018-02-02 2019-01-07 Rotor pourvu d'élément d'étanchéité et de bague d'étanchéité

Country Status (6)

Country Link
US (1) US11319823B2 (fr)
EP (2) EP3521561A1 (fr)
JP (1) JP7026809B2 (fr)
KR (1) KR102455245B1 (fr)
CN (1) CN111670292B (fr)
WO (1) WO2019149474A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11542819B2 (en) * 2021-02-17 2023-01-03 Pratt & Whitney Canada Corp. Split ring seal for gas turbine engine rotor

Citations (5)

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Publication number Priority date Publication date Assignee Title
US4507052A (en) * 1983-03-31 1985-03-26 General Motors Corporation End seal for turbine blade bases
WO2007028703A1 (fr) * 2005-09-07 2007-03-15 Siemens Aktiengesellschaft Systeme de retenue axiale de d'aubes mobiles dans un rotor et utilisation dudit systeme
EP2453150A1 (fr) * 2010-11-10 2012-05-16 United Technologies Corporation Dispositf d'étanchéité
EP2653660A1 (fr) * 2012-04-16 2013-10-23 General Electric Company Système et procédé permettant de recouvrir une zone de montage d'aubes de turbine
EP3061916A1 (fr) * 2015-02-24 2016-08-31 Siemens Aktiengesellschaft Agencement de disque de rotor et procédé de montage d'un agencement de disque de rotor

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NL295165A (fr) * 1962-07-11
GB2001708A (en) * 1977-07-22 1979-02-07 Rolls Royce Bladed rotor for a gas turbine engine
GB2095763A (en) * 1980-12-29 1982-10-06 Rolls Royce Enhancing turbine blade coolant seal force
US4767276A (en) * 1986-12-19 1988-08-30 General Electric Company Retainer ring
FR2666623B1 (fr) * 1990-09-11 1993-05-07 Turbomeca Roue de turbomachine a pales rapportees.
US5211407A (en) * 1992-04-30 1993-05-18 General Electric Company Compressor rotor cross shank leak seal for axial dovetails
GB9925261D0 (en) * 1999-10-27 1999-12-29 Rolls Royce Plc Locking devices
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JP7026809B2 (ja) 2022-02-28
CN111670292A (zh) 2020-09-15
EP3695100B1 (fr) 2021-10-06
US20200392857A1 (en) 2020-12-17
CN111670292B (zh) 2022-11-08
KR102455245B1 (ko) 2022-10-17
US11319823B2 (en) 2022-05-03
JP2021512250A (ja) 2021-05-13
EP3695100A1 (fr) 2020-08-19
KR20200111790A (ko) 2020-09-29

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