EP3318724A1 - Segment d'étanchéité d'un rotor et rotor - Google Patents

Segment d'étanchéité d'un rotor et rotor Download PDF

Info

Publication number
EP3318724A1
EP3318724A1 EP16197271.6A EP16197271A EP3318724A1 EP 3318724 A1 EP3318724 A1 EP 3318724A1 EP 16197271 A EP16197271 A EP 16197271A EP 3318724 A1 EP3318724 A1 EP 3318724A1
Authority
EP
European Patent Office
Prior art keywords
sealing
rotor
segment
support
profile
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Withdrawn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
EP16197271.6A
Other languages
German (de)
English (en)
Inventor
Peter Kury
Ivan Lbov
Peter Schröder
Vyacheslav Veitsman
Karsten Kolk
Kevin KAMPKA
Yulia Bagaeva
Marc Lange
Alexander Romanov
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 EP16197271.6A priority Critical patent/EP3318724A1/fr
Priority to PCT/EP2017/076344 priority patent/WO2018082907A1/fr
Publication of EP3318724A1 publication Critical patent/EP3318724A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
    • 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 sealing segment for forming a sealing ring in a rotor, in particular for use in a gas turbine, wherein the sealing segment is fixed with a T-shaped configuration with a central portion on the rotor.
  • the sealing ring is not formed as a closed ring body but from a plurality of circumferentially distributed sealing segments. Their attachment in turn can be done in different ways, in a known embodiment, the sealing segments have a T-shape. These are releasably secured in the rotor with a centrally arranged section. The arms of the T-shaped sealing segment extend in this case on both sides in a straight line from the center to the rotor disks or to the rotor blades attached to the rotor blades.
  • Object of the present invention is therefore to provide an improvement of the T-shaped sealing segments to the effect that they preserve the operation of the rotor, if possible, the desired shape with less weight.
  • the generic sealing segment serves to form a sealing ring of a rotor.
  • a plurality of sealing segments in the circumference are arranged distributed in the rotor.
  • Which type of rotor is involved here is irrelevant in this case, with the use of the sealing segment being particularly suitable for a gas turbine.
  • the sealing segment has a T-shaped configuration with a central circumferentially and radially extending anchoring portion. It is not mandatory that the anchoring portion has a constant thickness in the axial direction. This depends rather on the required strength or on the type of connection.
  • At least the anchoring section has a fastening profile on the side facing the rotor axis, by means of which the sealing segment can be fastened to the rotor.
  • a segment center In the mounting profile opposite radially outwardly facing Side is located at the anchorage a segment center.
  • a first sealing section or a second sealing section extends axially on both sides.
  • the sealing portions thus extend substantially in the circumferential direction and in the axial direction.
  • At the ends pointing in the axial direction of the sealing portions are each support portions. That is, at the end of the first sealing portion is a first support portion and at the axially opposite end of the sealing segment at the end of the second sealing portion is the second support portion.
  • the stability of the sealing sections is now improved by having, at least in sections, a curved shape relative to the rotor axis between the segment center and the supporting section. Due to the deviation from a rectilinear shape, a significantly improved stability of the sealing sections is achieved with the centrifugal forces occurring during operation of the rotor. As a result, a lower material thickness than usual can be used and the weight can be reduced.
  • the sealing portions each correspond to a portion of a rotating body. This favors furthermore in a particularly advantageous manner to avoid imbalance in the sealing ring by the multiple arrangement of the sealing segments in the scope.
  • the anchoring section is also particularly preferably formed as a section of a rotational body.
  • the end of the sealing portions in the circumferential direction, at least neglecting the support portions, and the end of the anchoring portion, at least neglecting the fastening profile, in a longitudinal plane through the rotor and the rotor axis is particularly advantageous if the end of the sealing portions in the circumferential direction, at least neglecting the support portions, and the end of the anchoring portion, at least neglecting the fastening profile, in a longitudinal plane through the rotor and the rotor axis.
  • the concrete shape of the sealing portions is initially irrelevant, provided that the stability of the sealing portions is improved in the centrifugal forces occurring by the curved shape. It is particularly advantageous if the shape of the sealing portions is selected such that the centrifugal forces within the sealing portion substantially lead to compressive stresses in the direction of the respective support portion. Depending on the shape, it may furthermore be advantageous if the stresses are distributed in the sealing section and guided on the one hand to the support sections as compressive stresses and on the other hand lead to compressive stresses towards the center of the segment.
  • At least one curved to the rotor axis harmonic shape is particularly preferable.
  • bending stresses in the sealing portions can be at least reduced in an advantageous manner, be avoided with a particularly advantageous shape as far as possible.
  • a deformation of the sealing sections during rotation of the rotor is advantageously minimized or prevented.
  • the respective sealing section starting from the middle of the segment, first approaches the rotor axis axially in the direction of the support sections and then the distance to the rotor axis increases again up to the support sections.
  • a harmonic profile is selected over both sealing sections. It is advantageous if the distance of the sealing sections to the rotor axis, starting from the middle of the segment increases continuously on both sides up to the support sections.
  • sealing segments on the rotor for the realization of a sealing ring is usually radially outside the sealing ring, a stationary stator, with a flow of hot gas in the area between the stator and rotating seal should also be minimized as far as possible. Therefore, it is also advantageous if on the outwardly facing side of the sealing portions sealing ribs for forming, for example, a labyrinth seal are arranged.
  • the fastening profile extends in the circumferential direction. This opens up greater possibilities with regard to the attachment of the fastening profile to the rotor. Furthermore, this considerably simplifies the production of the sealing segment as part of a rotor body. It is particularly advantageous if a sealing segment has at least two mutually spaced circumferentially, each as a part of a rotational body similar, mounting profiles with intermediate space.
  • a Christmas tree or a dovetail profile can be selected. This allows insertion into a corresponding complementarily shaped groove, with the radial undercut a load transfer in centrifugal force is possible.
  • a comparable embodiment of a fastening profile is also possible if a radial undercut is present and slipping out of the fastening profile is prevented during rotation of the rotor. That the fastening profile also requires no symmetry with respect to a transverse plane perpendicular to the rotor axis.
  • the fastening profile opposite, wherein the Christmas tree profile or dovetail profile is formed as a receiving profile on the rotor and the mounting profile C-shaped engages over the corresponding receiving profile on the rotor.
  • a fir tree groove or a dovetail groove or the like which opens radially towards the rotor axis is present in the fastening profile.
  • this may be a sealing groove that opens to the rotor axis.
  • a radially extending to the rotor axis sealing ridge is arranged on the mounting profile, which may be integrally formed on the mounting profile in a simple embodiment.
  • a radially extending sealing web is used, which in this case is inserted in the radially opening sealing groove.
  • the sealing measure is advantageous in the case of a Christmas tree or dovetail profile to be arranged on at its rotor axis facing bottom.
  • the sealing measure is advantageous to arrange in the middle of the interior of the sealing profile facing the rotor axis.
  • the support section in a first variant on a radially outwardly facing support surface and transverse to an axially pointing from the middle of the segment centering.
  • the support section has a curved support surface.
  • This radially outwardly and axially arcuately curved support surface also permits radial and axial support and thus advantageous load transfer from the support section into the rotor disc and / or the blade, i. in particular the compressive stresses acting on the sealing sections.
  • the support section has an inclined support surface.
  • the inclination may be chosen here such that, when the sealing segment is used as intended in the operation of the rotor, the forces occurring in this case, i.e., in the direction of rotation of the rotor are eliminated.
  • the pressure forces acting on the sealing sections as well as the centrifugal forces in the support section are transmitted essentially as pure compressive stresses via the support surface and, as far as possible, lateral forces are largely avoided in the support surface.
  • the support section Depending on the selected type of mounting of the sealing segment on the rotor, it is necessary to perform the support section variously. It is particularly advantageous if the support section divided at least with the support surface in the circumferential direction in at least two parts. In this case, there is a recess between the parts of the support surface of the support portion, which advantageously allows mounting on the rotor.
  • an advantageous seal between the radially outwardly located region and the region below the sealing sections is further favored if a radially extending sealing strip is present in the support section.
  • the sealing strip in the use of the sealing segment can rest on, for example, a rotor blade attached to the rotor disk, so that a further sealing from the sealing segment to the rotor blade is improved.
  • a receiving groove opening in the circumferential direction and extending radially outwards is provided in the supporting section.
  • the receiving groove on the top of the support portion, i. on the radially outward-facing side be aligned axially within the support portion perpendicular to the rotor axis.
  • the pitch of the sealing segments coincides with the pitch of the adjacent moving blades, at least on one rotor disk, preferably the upstream rotor disk.
  • the flow seal to a - in contrast to the rotor - stationary stator ring is improved when a sealing wing is arranged on the support portion, which is axially spaced in the middle of the segment from the support surface and in this case extends in the circumferential direction and radially.
  • a rotor according to the invention is possible, which is used in particular in a gas turbine, wherein the rotor has at least two rotor disks.
  • the rotor disks each have a plurality of blade retaining grooves distributed in the circumference.
  • Between the rotor discs is a plurality of sealing rings forming a sealing segments, wherein for attachment of the sealing segments with the mounting profile on the rotor, an annular receiving profile is present.
  • sealing segments according to the previous description are used in this case.
  • sealing segments and the rotor disks or the rotor is shaped such that form two separate annular spaces on both sides of the anchoring portion.
  • the fastening profile Depending on the installation of the fastening profile on the receiving profile, a more or less complete separation of the first annular space from the second annular space can be achieved. If the fastening profile has an interruption or other clearances are present, in particular for easier assembly, then it is particularly advantageous to provide further sealing measures in the connection between the fastening profile and the receiving profile.
  • a circumferentially and radially outwardly extending sealing web can be provided, which is formed, for example, integrally with the receiving profile.
  • a radially outwardly opening sealing groove is provided in the receiving profile. It is particularly advantageous in a third variant both in the fastening profile and to provide a sealing groove in the receiving profile, wherein a circumferentially and radially extending sealing ring dips into both opposing grooves.
  • sealing ring only in the sealing groove in the receiving profile, which migrates due to the centrifugal force during operation of the rotor at least minimally radially outwards and sealingly comes to rest on the mounting profile.
  • the rotor in each case on the blade retaining grooves with blade roots mounted blades, which each have a circumferentially and axially extending blade platform.
  • To support the sealing segments further comprises a rotor disk or both rotor disks each between the blade retaining grooves on an axially réelleckenden mounting projection.
  • the support sections come into abutment with the support surfaces at least during the rotation of the rotor on the attachment projection and thus are supported directly on the respective rotor disk.
  • the rotor blades have a collar extending from the blade platform and projecting beyond the rotor disk in the area of the blade retaining grooves. This collar can connect with minimal sealing gap to the support section.
  • the sealing strip in the support section applies at least during rotation of the rotor on the collar, so that an optimal seal between the sealing segment and blade is achieved.
  • the arrangement of the receiving profile for attachment of the sealing segments with the fastening profile can be carried out in many ways be. In this respect, it is possible, for example, to provide an encircling receiving profile or a plurality of axially running circumferentially arranged receiving profiles on an intermediate ring between the two rotor discs.
  • At least one rotor disk has a connecting flange on the side facing the other rotor disk.
  • both adjacent rotor disks each have a mutually facing connecting flange, wherein its size and shape can be chosen differently.
  • the receiving profile is arranged on the connecting flange or on a connecting flange of one of the rotor disks.
  • the receiving profile in such a way that the two adjacent rotor disks, each with half facing each other, realize half of the receiving profile with one profile half, ie. that the two profile halves of the two adjacent connecting flanges together form the receiving profile, and thus allow the attachment of the sealing segments with the fastening profile.
  • the receiving profile For attachment of the sealing segments on the receiving profile, it is also particularly advantageous, in particular when the receiving profile in the circumferential direction, if at least one mounting space is available in the receiving profile. In which direction the mounting space extends, i. E. opens, is initially irrelevant, provided that the corresponding insertion of the sealing segment with the fastening profile in the mounting space and is subsequently made possible in the receiving profile on the rotor.
  • the mounting space starting from the receiving profile in a radially outward-facing direction and / or extend in an axial direction. It is provided that the fastening profile is initially positioned in the radial direction at a radial opening of the mounting space or in the axial direction with a corresponding axial opening of the mounting space in corresponding radially and axially correct position with respect to the receiving profile, then by subsequent rotation, ie a shift in the circumferential direction, the sealing segment is inserted relative to the rotor disks, an insertion of the fastening profile in the receiving profile.
  • this mounting tool is for use in a sealing segment, which has a respective support portion at the axial opposite ends.
  • the respective support section it is necessary for the respective support section to have a mounting recess which opens to the opposite support section. Accordingly, the support section with the mounting recess is radially undercut.
  • the assembly tool in this case has a first lever and a hingedly connected second lever.
  • the first lever extends in the direction of a support portion, wherein at the end of the first lever, a first contact element is arranged. This engages in the corresponding mounting recess of the associated support section.
  • the connected via a second lever extends in the direction of the other support portion and also has at its end a second contact element. Analog engages the second contact element in the associated mounting recess of the corresponding support portion. This represents the mounting position of the mounting tool.
  • FIG. 1 a first embodiment of a rotor according to the invention and a sealing segment according to the invention in a perspective view in half section is shown.
  • blades can be fixed with a corresponding blade root in a known manner.
  • the connection between the two rotor disks 01 is shown simplified without a separation.
  • the two rotor disks 01 are manufactured separately and connected to each other via a mechanical connection.
  • a connecting flange 05 is arranged between the rotor disks 01, which extends radially outward from a section connecting the rotor disks 01.
  • a plurality of sealing segments 11 are distributed in the circumference. Furthermore, the sealing segments 11 adjoin the rotor disks 01 and the rotor blades to be mounted on both sides.
  • the closed annular spaces 08, 09 favor an advantageous cooling air flow in the rotor.
  • FIG. 2 shows again the FIG. 2 the view FIG. 1 omitting the front rotor disk 01.
  • the connecting flange 05 know a circumferential mounting profile 06.
  • a mounting space 07 is provided on the connecting flange 05, which interrupts the receiving profile 06.
  • the sealing segment 11 can be mounted in a bayonet.
  • FIG. 3 an exemplary embodiment of a sealing segment 11 is sketched in perspective view.
  • the sealing portions 15 are here arcuate, so that when centrifugal forces occurring an advantageous stress distribution in the sealing segment 11 is achieved.
  • At the middle of the segment 12 opposite end of the respective sealing portions 15 is located on both sides of the sealing segment 11 each have a support portion 17.
  • the support portion 17 has a radially outwardly facing support surface 21 and an axially to the respective rotor disk 01 facing centering surface 23.
  • the support surface 21 and the centering surface 23 are arranged in an L-shape.
  • the support surface 21 is interrupted over the length of the sealing segment 11 in the circumferential direction. Therefore, the support portions 17 in this embodiment each have two recesses 18, which correspond at least to the length of the mounting projections 04 in the circumferential direction. This also allows the bayonet-like mounting of the sealing segment 11 between the rotor disks 01. Furthermore, it can be seen in this embodiment, that the support portions 17 further comprise a spaced from the centering surface 13 in the direction of 12 center segment 12 sealing wings. This 19 favors the further seal to a stationary stator ring, which surrounds the sealing ring formed from sealing segments 11.
  • the sealing segment 11 has a plurality of radially outwardly extending sealing ribs 16, which also favor 16 an advantageous seal against the stator ring.
  • the support sections 17 each have a receiving groove 20 extending in the circumferential direction. It is provided that in the receiving groove 20, a sealing strip is inserted, which comes at least under centrifugal force under a collar of the respective blades to the plant and allows an advantageous seal to the blades.
  • the T-shaped sealing segment furthermore has an anchoring section 13 extending radially inwards from the middle of the segment 11.
  • the attachment profile 14 is designed in this embodiment as a broadening of the anchoring portion 13, so that this 14 can be secured in a T-shaped receiving groove of the receiving profile 06 at its end opposite to the segment center 12. It is obvious that for this purpose the mounting space 07 at the receiving profile 06 of the connecting flange 05 must be made sufficiently large, so that the fastening profile 14 can be mounted in a bayonet.
  • FIG. 4 is again for presentation FIG. 1 the arrangement of two adjacent rotor disks 01 sketched with intermediate sealing segment 11 in section.
  • the rotor disks 01 can be seen with the connecting web 05 and the sealing segment 11 located therebetween.
  • the sealing segment 11 is mounted here with the fastening profile 14 in the receiving profile 06 on the connecting flange 05.
  • the receiving profile 06 at the appropriate place a mounting space 07, so that the mounting profile 14 can be inserted from above first into the mounting space 07 and then into the receiving profile 06.
  • the rotor disks 01 further have at their radially outer end on the mutually facing sides in each case a fastening projection 04, on which the T-shaped sealing segment 11 also comes to rest.
  • FIG. 5 This is shown in a detail view in FIG. 5 the support portion 17 of the sealing segment 11 outlined. To recognize is in turn the end of the sealing portion 15 to which the support portion 17 connects.
  • the support portion 17 in this case has radially outwardly facing a support surface 21 for support on the mounting projection 04. Furthermore, the support portion 17, the centering surface 23 also to rest on the mounting projection 04. Spaced to the centering surface 23 is located on the support portion 17, a sealing wing 19 and immediately adjacent to the centering surface 23 a receiving groove 20th
  • FIG. 6 is an alternative embodiment of a sealing segment 41 and the embodiment of the rotor disks 31 analogous to the representation in FIG. 4 sketched on average.
  • the adjacent arrangement of the rotor disks 31 can be seen with a connecting flange 35 lying between them.
  • the connecting flange 35 is divided in the middle and thus formed by two halves 35a and 35b respectively belonging to one of the two rotor disks 31 .
  • the receiving profile 36 At the end of the connecting flange 35 closes analogous previous Execution, the receiving profile 36, wherein in this embodiment, the receiving profile 36 is formed according to the separation of the rotor discs 31 of two halves 36 a and 36 b and in this case represents a T-shaped configuration with the anchoring portion 35.
  • the receiving profile 36 is formed according to the separation of the rotor discs 31 of two halves 36 a and 36 b and in this case represents a T-shaped configuration with the anchoring portion 35.
  • the radially outer end of the rotor disks 31 are analogous to the mounting projections 34.
  • FIG. 8 Another embodiment is analogous to the representation FIG. 4 outlined.
  • a sealing strip 27 is arranged between the mounting profile 74 and the connecting flange 65.
  • the receiving profile 66 on the connecting flange 55 has a radially outwardly facing sealing groove 67 into which the annular sealing strip 27 is inserted. This 27 may be performed circumferentially.
  • the fastening profile 74 analogously has a sealing groove 84 in the sealing strip 27 engages.
  • FIG. 9 Two other design options for the design of the support sections 77, 78 outlined. Accordingly, no longer separate support and centering surfaces are provided, but rather a support surface 81, 82, 81, 82 can support both radially and axially on the correspondingly executed fastening projection 64,68.
  • a first solution provides in this case that the support surface 81 of the support portion 77 is curved.
  • the shape of the support surface 81 corresponds in section to a circular section in an advantageous manner, a planar contact of the support section 77 on the fastening projection 64 is ensured even in the case of deformations of the sealing section 15.
  • a second solution for this purpose discloses a support portion 78 with a support surface 82 inclined and correspondingly designed Befest Whilesvorsprung 68.
  • the inclination of the support surface 82 is in this case selected such that during normal operation of the rotor with the centrifugal forces occurring taking into account the axial and radial forces essentially only compressive forces on the inclined support surface 82 are transferred to the mounting projection 68.
  • FIG. 10 an exemplary mounting tool 101 is shown schematically in a mounting position on the sealing segment 11.
  • the support portions 17 at the end of the sealing portions 15 each have a facing the opposite support portion 17 mounting recess, which is radially undercut.
  • the assembly tool 101 comprises a first lever 103, which extends substantially axially to one of the support sections 17 and at the end of which a first receiving element 104 is located. This 104 engages in the mounting recess on the corresponding support portion 17.
  • a hinge 107 Opposite at the end of the first lever 103 is a hinge 107 to which a second lever 105 is pivotally mounted. This 105 extends analogously in the opposite direction to the other support portion 17.
  • the assembly tool 101 can be removed from the sealing segment 11 by pivoting the second lever 105 relative to the first lever 103.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP16197271.6A 2016-11-04 2016-11-04 Segment d'étanchéité d'un rotor et rotor Withdrawn EP3318724A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP16197271.6A EP3318724A1 (fr) 2016-11-04 2016-11-04 Segment d'étanchéité d'un rotor et rotor
PCT/EP2017/076344 WO2018082907A1 (fr) 2016-11-04 2017-10-16 Segment étanche d'un rotor et rotor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16197271.6A EP3318724A1 (fr) 2016-11-04 2016-11-04 Segment d'étanchéité d'un rotor et rotor

Publications (1)

Publication Number Publication Date
EP3318724A1 true EP3318724A1 (fr) 2018-05-09

Family

ID=57226884

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16197271.6A Withdrawn EP3318724A1 (fr) 2016-11-04 2016-11-04 Segment d'étanchéité d'un rotor et rotor

Country Status (2)

Country Link
EP (1) EP3318724A1 (fr)
WO (1) WO2018082907A1 (fr)

Cited By (1)

* 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

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5236302A (en) * 1991-10-30 1993-08-17 General Electric Company Turbine disk interstage seal system
US5320488A (en) * 1993-01-21 1994-06-14 General Electric Company Turbine disk interstage seal anti-rotation system
US5338154A (en) * 1993-03-17 1994-08-16 General Electric Company Turbine disk interstage seal axial retaining ring
EP1079070A2 (fr) * 1999-08-26 2001-02-28 Asea Brown Boveri Ag Bouclier thermique pour un rotor de turbine
EP1898054A1 (fr) * 2006-08-25 2008-03-12 ALSTOM Technology Ltd Turbine à gaz
EP2208860A2 (fr) * 2009-01-14 2010-07-21 General Electric Company Joint entre étages de turbine à gaz et turbine à gaz associée
US20120051917A1 (en) * 2010-08-31 2012-03-01 Daniel Edward Wines Tapered collet connection of rotor components
US20130315708A1 (en) * 2012-05-25 2013-11-28 Jacob Romeo Rendon Nozzle with Extended Tab
FR3009336B1 (fr) * 2013-08-05 2015-09-04 Snecma Ensemble rotatif de turbomachine muni d'une virole labyrinthe cmc

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5236302A (en) * 1991-10-30 1993-08-17 General Electric Company Turbine disk interstage seal system
US5320488A (en) * 1993-01-21 1994-06-14 General Electric Company Turbine disk interstage seal anti-rotation system
US5338154A (en) * 1993-03-17 1994-08-16 General Electric Company Turbine disk interstage seal axial retaining ring
EP1079070A2 (fr) * 1999-08-26 2001-02-28 Asea Brown Boveri Ag Bouclier thermique pour un rotor de turbine
EP1898054A1 (fr) * 2006-08-25 2008-03-12 ALSTOM Technology Ltd Turbine à gaz
EP2208860A2 (fr) * 2009-01-14 2010-07-21 General Electric Company Joint entre étages de turbine à gaz et turbine à gaz associée
US20120051917A1 (en) * 2010-08-31 2012-03-01 Daniel Edward Wines Tapered collet connection of rotor components
US20130315708A1 (en) * 2012-05-25 2013-11-28 Jacob Romeo Rendon Nozzle with Extended Tab
FR3009336B1 (fr) * 2013-08-05 2015-09-04 Snecma Ensemble rotatif de turbomachine muni d'une virole labyrinthe cmc

Cited By (2)

* 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
US11339662B2 (en) 2018-08-02 2022-05-24 Siemens Energy Global GmbH & Co. KG Rotor comprising a rotor component arranged between two rotor disks

Also Published As

Publication number Publication date
WO2018082907A1 (fr) 2018-05-11

Similar Documents

Publication Publication Date Title
DE3210892C2 (de) Turbomaschinen-Laufrad
DE2908242C2 (de) Rindförmiger Flansch für den Läufer einer axial durchströmten Strömungsmaschine zum Zusammenwirken mit einer Stirnfläche eines Radkranzes oder dergleichen
DE102010060284B4 (de) Sicherungs-Abstandshalteranordnung für ein Schaufelblattbefestigungssystem zur Einführung in Umfangsrichtung und Rotoranordnung mit derartiger Sicherungs-Abstandshalteranordnung
DE3006099C2 (de) Dichtungsanordnung zwischen zwei umlaufenden scheibenförmigen Maschinenteilen
DE19507673A1 (de) Leitrad für Turbomaschinen
DE102015116935A1 (de) Sicherungsvorrichtung zur axialen Sicherung einer Laufschaufel und Rotorvorrichtung mit einer derartigen Sicherungsvorrichtung
EP2394028B1 (fr) Dispositif d'étanchéité sur l'arbre à aubes d'un étage de rotor d'une turbomachine axiale et son utilisation
EP3227532A1 (fr) Ensemble disque de roue à montage simplifié des tôles d'étanchéité
EP3318724A1 (fr) Segment d'étanchéité d'un rotor et rotor
EP3194725B1 (fr) Rotor, compresseur axial, procédé de montage
EP3109520B1 (fr) Support d'étanchéité, stator et turbomachine
EP2860350A1 (fr) Aube de turbine et turbine à gaz
EP3695100B1 (fr) Rotor pourvu d'élément d'étanchéité et de bague d'étanchéité
EP3318723B1 (fr) Anneau d'étanchéité d'un rotor et rotor
EP3885535B1 (fr) Bague d'étanchéité pour un rotor et rotor doté d'une telle bague d'étanchéité
DE102017220336A1 (de) Dichtsegment eines Rotors sowie Rotor
EP3724456B1 (fr) Rotor à surfaces de contact optimisées au niveau de forces centrifuges
EP3287595A1 (fr) Rotor dote d'un anneau d'etancheite segmente
DE102016205921B4 (de) Rotorscheibenanordnung mit zweiteiliger Dichtung
DE102017214065A1 (de) Rotor mit mittels Dichtelementen fixierten Laufschaufeln
DE10217390A1 (de) Turbinenschaufel
DE102017214062A1 (de) Rotor mit mittels Dichtelemente axial fixierten Laufschaufeln
DE3101250A1 (de) "rotor fuer stroemungsmaschinen, insbesondere axialverdichterrotor fuer gasturbinentriebwerke"
EP3561234B1 (fr) Rotor pourvu de dispositif d'étanchéité
EP3348786A1 (fr) Rotor comprenant une couverture de conduite et plaques d'étanchéité

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20181110