EP3498980B1 - Agencement de joint à feuillure - Google Patents

Agencement de joint à feuillure Download PDF

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Publication number
EP3498980B1
EP3498980B1 EP17207850.3A EP17207850A EP3498980B1 EP 3498980 B1 EP3498980 B1 EP 3498980B1 EP 17207850 A EP17207850 A EP 17207850A EP 3498980 B1 EP3498980 B1 EP 3498980B1
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EP
European Patent Office
Prior art keywords
seal
shiplap
coupling
arrangement according
adjacent
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.)
Active
Application number
EP17207850.3A
Other languages
German (de)
English (en)
Other versions
EP3498980A1 (fr
Inventor
Philip CORSER
Sarah Heaven
Arthur Mateusz FAFLIK-BROOKS
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.)
Ansaldo Energia Switzerland AG
Original Assignee
Ansaldo Energia Switzerland 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 Ansaldo Energia Switzerland AG filed Critical Ansaldo Energia Switzerland AG
Priority to EP17207850.3A priority Critical patent/EP3498980B1/fr
Priority to CN201811531048.XA priority patent/CN110005476B/zh
Publication of EP3498980A1 publication Critical patent/EP3498980A1/fr
Application granted granted Critical
Publication of EP3498980B1 publication Critical patent/EP3498980B1/fr
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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
    • F01D11/005—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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • F05D2240/80—Platforms for stationary or moving blades

Definitions

  • the present invention relates to a shiplap arrangement for a gas turbine
  • sealing means for sealing interspaces such as rubber seals, polymer seals, adhesive means, or engaging of a projection in a slot, as are especially to be encountered in the case of the seal between two static elements, are generally known.
  • a wide variety of elements are cooled by means of a cooling air flow for avoiding heat damage. This cooling air flow is to be effected with the lowest losses possible in order to maximize the cooling potential.
  • Turbine blades in most cases have at least one platform element radially on the inside and/or radially on the outside, which, with the blade row installed, abut on the respectively adjacent platform element of the respectively adjacent blade element by the two sides of the platform element which point in the circumferential direction, forming in each case an essentially circumferential gap.
  • Such a turbine blade element on at least one axial edge, especially the trailing edge, on a first side which points in the circumferential direction, can have a projection which extends in the circumferential direction and projects into the platform element of the abutting blade element, and on a second side which points in the circumferential direction can have a recess which accommodates this projection.
  • Such a shiplap is an overlapping or engaging region, which is stepped in the flow direction of the operating gas, between the shroud element on an axial edge of a blade element and the shroud element on the same axial edge of the adjacent blade element.
  • This shiplap seals the radially extending gap between the contiguous circumferential sides of two turbine blades against the escape of cooling air from the secondary air circuit, i.e. against the leakage flow in the axial direction.
  • Such a shiplap comes into being as result of the covering of a recess on a first side, which points in the circumferential direction, of an adjacent blade element by means of a projection on the second side, which points in the circumferential direction, of a blade element, or by the engagement of the projection in the recess.
  • US2012045337 refers to a gas turbine engine comprising a plurality of circumferentially-spaced rotor blades provided with at least one sealing assembly.
  • US2008247867 relates to a gap seal for radial sealing of a gap which extends axially and radially between two blades of a turbomachine which are adjacent in the circumferential direction.
  • the invention is accordingly based on the object of providing an improved arrangement which has an improved sealing effect along the shiplap coupling that reduces the leakage flow from the cooling air cavity.
  • the present invention refers also to a gas turbine for power plant provided with such a sealed shiplap arrangement.
  • figure 1 is a schematic view of a flow diagram of an embodiment of a gas turbine for power plants.
  • Figure 1 discloses a gas turbine power plant 1 having an axis A and comprising in series along the main flow M:
  • the rotor 7 is single piece of a plurality of rotor wheels welded together and extends from the compressor 2 to the turbine 5.
  • the combustor section can be provided with an annular combustor or a plurality of can combustors.
  • the exhaust gases leaving the turbine can be used in a steam generator 8 and the rotor 7 can connected to load 9 that can be a stationary load such as an electrical generator in a power plant.
  • the compressor 2 and the turbine 5 comprises a plurality of stator vanes and a plurality of rotating blades. These rotating blades connected to the rotor 7 and arranged in parallel circumferential rows centered in the axis 7.
  • figures 2 and 3 are schematic views of adjacent blades of the gas turbine of fig. 1 , in particular figures 2 and 3 refer to adjacent turbine blades 12.
  • the turbine blades are in contact with the hot gas and therefore need to be cooled by cooling air, i.e. compressed air.
  • figure 2 discloses a legend of the main directions of the gas turbine filed.
  • the reference 13 refers to the axial direction that is parallel to the rotor 7, to the axis A and in general to the hot gas flow direction M.
  • the terms downstream and upstream refer to the axial direction 13 along the hot gas flow direction M.
  • the reference 14 refers to the radial direction centered in the axis A; the terms inner/inwardly and outer/outwardly refer to the distance from the axis A along the radial direction 14.
  • the reference 15 refers to the circumferential direction centered in the axis A.
  • this legend discloses this legend to allow the easy identification of the correct position of the represented gas turbine components.
  • FIG. 2 discloses an axial downstream view of two adjacent turbine blades 12 of a common row of blades. Blades 12 may be constructed of a metal, metal alloy, ceramic matrix composite (CMC), or other suitable material.
  • each blade 12 comprises a foot 16 configured to be coupled with the rotor 7, a shank portion 17 provided with downstream or closing wall 18, a platform 19, and an airfoil 20.
  • a cavity is present, in particular a cooling air cavity that is partially disclosed in the figures 8 and 9 with the reference 21. From the shank cavity, the cooling air can enter in cooling duct realized inside the airfoil 20 that in operation are in contact with the hot gas flow. This cavity is outwardly limited along the radial direction 14 by the adjacent edges of the platforms 19 and downstream along the axial direction 13 by the adjacent edges of the closing walls 18.
  • this cooling air cavity has to be sealed both in radial direction, i.e. to avoid leakages passing to the gap present between the adjacent platforms 19, and in axial direction, i.e. to avoid leakages passing to the gap present between the closing walls 18.
  • the sealing in the radial direction is performed by an axial seal in form preferably of an axial seal strip arranged in axial seats of the facing adjacent edges of the platforms 19.
  • Figure 2 and 3 disclose schematically this axial seal with the reference 22 and the figures 8 and 9 disclose the seats 23 of this axial seal 22 in the platforms 19.
  • the sealing in the axial direction is performed by the so called shiplap coupling represented in figure 2 and 3 by the reference 24.
  • the shiplap coupling 24 comprises a radial edge of the closing wall 19 that is projecting to the adjacent closing wall 19 and a recess configured for housing the projecting edge realized in such an adjacent closing wall 19.
  • each blade of the row, beside the last blade comprise a closing wall wherein a first radial edge in provided with the projecting portion along the circumferential direction 15 and on the opposite radial edge with a radial recess suitable for housing the projecting portion of the adjacent blade.
  • Figure 3 schematically shows a top view along the radial direction 14 of some adjacent blades in order to clarify the shiplap coupling.
  • the airfoil 20 comprises a leading edge 25 and a trailing edge 26.
  • Figure 3 discloses the radial gap 27 between two adjacent platforms 19 sealed by the axial seal 22 and the shiplap coupling 24 configure for closing the axial gap between two adjacent closing walls 19.
  • the projection portion of the shiplap coupling 24 has been represented by the reference 28 and the corresponding recess with the reference 29.
  • figure 4 is a schematic enlarged view of a shiplap portion of figure 3 .
  • figure 4 discloses a seal 30 arranged in the shiplap region 24 foregoing described.
  • This seal 30 is configured to provide a barrier against a leakage flow from the shank cavity passing through the gap present between the projection portion 28 and the recess portion 29.
  • figure 5 is a schematic enlarged view of the portion of figure 4 represented by reference V and showing a top view along the radial direction of the shiplap region 24 provided with the seal 30.
  • the seal 30 has axially extends from a first groove 31 realized in the projection portion 28 to a second groove 32 realized in the recessed portion 29.
  • the references C1 and C2 in figure 5 represent the cooling air flow passing between two adjacent closing walls, in particular passing through the gap present between the projection portion 28 and the recess portion 29.
  • C1 is the leakage flow along the axial direction and C2 the leakage flow along the circumferential direction.
  • the seal 30 allow to stop the flow C2.
  • Seal 30 is preferably a rigid seal housed with play or clearance the grooves 31 and 32.
  • the first 31 and the second groove 32 are substantially facing each other along the axial direction 13.
  • figure 6 and 7 are schematic views of the sealing arrangement of figure 5 respectively in a standard condition and in the worst case of tolerances.
  • seal 30 in the relative grooves 21 and 32 ensures that manufacturing tolerances are recovered and, at the same time, proper seal is obtained.
  • clearance is in a direction parallel to the leakage flow C2, i.e. along the circumferential direction 15, and/or in a direction transversal, preferably perpendicular, to the leakage flow C2, i.e. along the axial direction 13.
  • This provides a floating mount of the rigid seal 30 in seat 31 32.
  • the seal 30 has a hook shape defining a convex side 33 pointing against the leak flow C2 and a concave side 34 engaging a protrusion 35 within one the groove 32, in particular the groove 32 in the recess portion 29. Coupling between seal 30 and protrusion 35 is a floating coupling due to clearance of seal inside seat 31, 32. In use, leakage flow C2 presses seal 30 against protrusion 35 even if the centrifugal force is acting on the seal 30.
  • the seal 30 has a substantially 'L' cross section orthogonal to the radial direction 14 defining by a longer arm 36 crossing gap of the shiplap coupling and a shorter arm 37 housed in the groove 32 in the recess portion 29.
  • L shape is simple to manufacture, e.g. by bending. It is however possible to obtain a similar function with other profiles, such as a 'T' profile that can be manufactured e.g. by extrusion. In use, leakage flow presses longer arm 36 against an internal surface of groove 31 in the recess portion 28 even if the centrifugal force is acting on the seal 30.
  • figures 8 and 9 are schematic prospective views of the sealing arrangement of figure 5 along the axial direction showing respectively the seal arranged in a blade and in the adjacent blade.
  • figure 8 and 9 disclose two prospective axial view of the seal 30 respectively from the shank cavity from outside the shank cavity.
  • the seal 30 and the grooves 31 32 extend radially along substantially the entire radial length of the projecting 28 and recess 29.
  • the seal 30 outwardly extends up to the axial seal arranged between the adjacent blades in the seats 23.
  • the inner ends of the groove are open to allow a sliding assembly of the seal 30 that is held in position at the opposite outer ends of the grooves.
  • the seal 30 is held by the axial seal 22 that is assembled after the seal 30.

Landscapes

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

Claims (10)

  1. Agencement à clin d'une turbine à gaz (1) présentant un axe (A) ; l'agencement à clin (24) comprenant :
    - des première et deuxième aubes (12) adjacentes agencées le long d'une direction circonférentielle (15) centrées dans l'axe de la turbine à gaz (A) ; chaque aube (12) le long d'une direction radiale (14) comprenant un pied (16) configuré afin d'accoupler l'aube (12) à un rotor (7), une partie jambe (17) dotée d'une paroi de fermeture aval (18), une plate-forme (19) et un profil aérodynamique (20) ; entre les aubes adjacentes (12) dans la partie jambe (17), est prévue une cavité d'air de refroidissement (21) qui est scellée en aval par un accouplement à clin (24) entre les parois de fermeture de jambe adjacentes (18) ; l'accouplement à clin (24) comprenant une partie saillie circonférentielle (28) de la paroi de fermeture de jambe (18) de la première aube (12), et une partie renfoncement de réception correspondante (29) dans la paroi de fermeture de jambe adjacente (18) ;
    - un joint radial (30) agencé le long de l'intervalle entre la partie saillie (28) et la partie renfoncement (29) de l'accouplement à clin (24) ;
    caractérisé en ce que le joint radial (30) est logé au niveau d'un côté dans une première rainure radiale (31) réalisée dans la partie saillie (28), et au niveau de l'autre côté dans une deuxième rainure radiale (32) réalisée dans la partie renfoncement (29), afin de fournir une barrière contre un flux de fuite passant à travers l'accouplement à clin ;
    et en ce que la jambe est scellée extérieurement par un joint axial (22) agencé le long de l'intervalle entre les plates-formes adjacentes (19).
  2. Agencement selon la revendication 1, caractérisé en ce que le joint (30) est rigide, et logé avec un jeu dans les rainures (31, 32) afin de fournir un montage flottant du joint (30) dans les rainures (31, 32).
  3. Agencement selon la revendication 2, caractérisé en ce que le jeu se situe dans une direction circonférentielle et / ou axiale.
  4. Agencement selon l'une quelconque des revendications précédentes, caractérisé en ce que le joint (30) présente une forme de crochet qui définit un côté convexe (33) qui est dirigé contre l'écoulement de fuite, et un côté concave (34) qui vient en prise avec une saillie (35) à l'intérieur de l'une desdites première et deuxième rainures (31, 32), l'écoulement de fuite pressant le joint (30) contre la saillie (35).
  5. Agencement selon la revendication 4, caractérisé en ce que le joint (30) comprend un bras plus long (36) qui croise l'intervalle entre la partie saillie (28) et la partie renfoncement (29) de l'accouplement à clin (24), et un bras plus court (37) qui fait saillie hors du bras le plus long (36), et qui est logé dans la deuxième rainure (32) ainsi que la saillie (35), l'écoulement de fuite pressant le bras plus long (36) contre une surface intérieure de la première rainure (31).
  6. Agencement selon l'une quelconque des revendications précédentes, caractérisé en ce que la rainure (31, 32) et le joint (30) se situent entre deux courbures le long de l'intervalle entre la partie saillie (28) et la partie renfoncement (29) de l'accouplement à clin (24).
  7. Agencement selon l'une quelconque des revendications précédentes, caractérisé en ce que les extrémités intérieures des rainures (31, 32) sont ouvertes afin de permettre un assemblage coulissant du joint (30).
  8. Agencement selon l'une quelconque des revendications précédentes, caractérisé en ce que le joint (30) est maintenu en position au niveau des extrémités extérieures des rainures (31, 32).
  9. Agencement selon l'une quelconque des revendications précédentes, caractérisé en ce que le joint (30) est maintenu en position par le joint axial (22) qui est assemblé après le joint (30).
  10. Turbine à gaz d'une centrale électrique ; la turbine à gaz (1) présentant un axe (A) et comprenant :
    - un compresseur (2) destiné à comprimer l'air,
    - une chambre de combustion (3, 4) destinée à mélanger et à brûler l'air comprimé qui quitte le compresseur (2), avec au moins un combustible,
    - une turbine (3) destinée à expanser le flux des gaz chauds brûlés qui quittent la chambre de combustion (3, 4), et à produire un travail sur un rotor (7) ;
    où la turbine (3) comprend au moins un agencement à clin selon l'une quelconque des revendications précédentes.
EP17207850.3A 2017-12-15 2017-12-15 Agencement de joint à feuillure Active EP3498980B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP17207850.3A EP3498980B1 (fr) 2017-12-15 2017-12-15 Agencement de joint à feuillure
CN201811531048.XA CN110005476B (zh) 2017-12-15 2018-12-14 搭叠密封装置

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17207850.3A EP3498980B1 (fr) 2017-12-15 2017-12-15 Agencement de joint à feuillure

Publications (2)

Publication Number Publication Date
EP3498980A1 EP3498980A1 (fr) 2019-06-19
EP3498980B1 true EP3498980B1 (fr) 2021-02-17

Family

ID=60673741

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17207850.3A Active EP3498980B1 (fr) 2017-12-15 2017-12-15 Agencement de joint à feuillure

Country Status (2)

Country Link
EP (1) EP3498980B1 (fr)
CN (1) CN110005476B (fr)

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2002201913A (ja) * 2001-01-09 2002-07-19 Mitsubishi Heavy Ind Ltd ガスタービンの分割壁およびシュラウド
WO2008122507A1 (fr) * 2007-04-05 2008-10-16 Alstom Technology Ltd Agencement en feuillure
EP1995413B1 (fr) * 2007-04-05 2010-04-28 ALSTOM Technology Ltd Joint d'étanchéité pour le jeu d'aubes d'une turbomachine
US20120045337A1 (en) * 2010-08-20 2012-02-23 Michael James Fedor Turbine bucket assembly and methods for assembling same
US10167728B2 (en) * 2012-03-28 2019-01-01 Mitsubishi Heavy Industries, Ltd. Seal member, turbine, and gas turbine
EP2832952A1 (fr) * 2013-07-31 2015-02-04 ALSTOM Technology Ltd Aube de turbine et turbine à étanchéité améliorée
EP2843197B1 (fr) * 2013-08-29 2019-09-04 Ansaldo Energia Switzerland AG Aube de machine tournante, l'aube ayant des moyens de rétention spécifiques pour un joint radial d'étanchéité en bande
US10113438B2 (en) * 2016-02-18 2018-10-30 United Technologies Corporation Stator vane shiplap seal assembly

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
CN110005476B (zh) 2022-11-08
EP3498980A1 (fr) 2019-06-19
CN110005476A (zh) 2019-07-12

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