EP3498980B1 - Stufenfalzdichtungsanordnung - Google Patents

Stufenfalzdichtungsanordnung 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
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English (en)
French (fr)
Other versions
EP3498980A1 (de
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.)
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Publication date
Application filed by Ansaldo Energia Switzerland AG filed Critical Ansaldo Energia Switzerland AG
Priority to EP17207850.3A priority Critical patent/EP3498980B1/de
Priority to CN201811531048.XA priority patent/CN110005476B/zh
Publication of EP3498980A1 publication Critical patent/EP3498980A1/de
Application granted granted Critical
Publication of EP3498980B1 publication Critical patent/EP3498980B1/de
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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. Stufenfalzanordnung für eine Gasturbine (1), die eine Achse (A) aufweist; wobei die Stufenfalzanordnung (24) Folgendes umfasst:
    - eine erste und eine zweite Schaufel (12), die in einer auf die Gasturbinenachse (A) zentrierten Umfangsrichtung (15) nebeneinander angeordnet sind; wobei jede Schaufel (12) in einer radialen Richtung (14) einen Fuß (16), der zum Koppeln der Schaufel (12) mit einem Rotor (7) konfiguriert ist, einen Schaftabschnitt (17), der mit einer stromabseitigen Abschlusswand (18) versehen ist, eine Plattform (19) und einen Flügel (20) umfasst; wobei zwischen den nebeneinander angeordneten Schaufeln (12) im Schaftabschnitt (17) ein Kühllufthohlraum (21) vorgesehen ist, der stromabwärts durch eine Stufenfalzkopplung (24) zwischen den benachbarten Schaftabschlusswänden (18) abgedichtet ist; wobei die Stufenfalzkopplung (24) einen vorstehenden Umfangsabschnitt (28) der Schaftabschlusswand (18) der ersten Schaufel (12) und einen entsprechenden Aufnahmevertiefungsabschnitt (29) in der benachbarten Schaftabschlusswand (18) umfasst;
    - eine radiale Dichtung (30), die entlang des Spalts zwischen dem vorstehenden Abschnitt (28) und den Vertiefungsabschnitt (29) der Stufenfalzkopplung (24) angeordnet ist;
    dadurch gekennzeichnet, dass die radiale Dichtung (30) auf einer Seite in einer ersten radialen Rille (31), die in dem vorstehenden Abschnitt (28) realisiert ist, und auf der anderen Seite in einer zweiten radialen Rille (32), die im Vertiefungsabschnitt (29) realisiert ist, aufgenommen ist, um eine Sperre dagegen, dass eine Verlustströmung durch die Stufenfalzkopplung hindurchtritt, bereitzustellen;
    und dass der Schaft durch eine axiale Dichtung (22), die entlang des Spalts zwischen den benachbarten Plattformen (19) angeordnet ist, nach außen abgedichtet ist.
  2. Anordnung nach Anspruch 1, dadurch gekennzeichnet, dass die Dichtung (30) steif und mit einem Zwischenraum in den Rillen (31, 32) aufgenommen ist, um eine pendelnde Lagerung der Dichtung (30) in den Rillen (31, 32) bereitzustellen.
  3. Anordnung nach Anspruch 2, dadurch gekennzeichnet, dass sich der Zwischenraum in der Umfangsrichtung und/oder in axialer Richtung befindet.
  4. Anordnung nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Dichtung (30) hakenförmig ist, wobei eine konvexe Seite (33), die gegen die Verlustströmung zeigt, und eine konkave Seite (34), die sich mit einem Vorsprung (35) entweder in der ersten oder in der zweiten Rille (31, 32) in Eingriff befindet, definiert werden, wobei die Verlustströmung die Dichtung (30) gegen den Vorsprung (35) drückt.
  5. Anordnung nach Anspruch 4, dadurch gekennzeichnet, dass die Dichtung (30) einen längeren Arm (36), der den Spalt zwischen dem vorstehenden Abschnitt (28) und dem Vertiefungsabschnitt (29) der Stufenfalzkopplung (24) kreuzt, und einen kürzeren Arm (37), der vom längeren Arm (36) vorsteht und zusammen mit dem Vorsprung (35) in der zweiten Rille (32) aufgenommen ist, umfasst, wobei die Verlustströmung den längeren Arm (36) gegen eine Innenfläche der ersten Rille (31) drückt.
  6. Anordnung nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Rille (31, 32) und die Dichtung (30) zwischen zwei Biegungen entlang des Spalts zwischen dem vorstehenden Abschnitt (28) und dem Vertiefungsabschnitt (29) der Stufenfalzkopplung (24) angeordnet sind.
  7. Anordnung nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Innenenden der Rillen (31, 32) offen sind, um eine gleitende Montage der Dichtung (30) zu ermöglichen.
  8. Anordnung nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Dichtung (30) an den Außenenden der Rillen (31, 32) in Position gehalten wird.
  9. Anordnung nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Dichtung (30) durch die axiale Dichtung (22), die nach der Dichtung (30) montiert wird, in Position gehalten wird.
  10. Gasturbine für ein Kraftwerk; wobei die Gasturbine (1) eine Achse (A) aufweist und Folgendes umfasst:
    - einen Kompressor (2) zum Komprimieren von Luft;
    - einen Brenner (3, 4) zum Mischen und Verbrennen der komprimierten Luft, die den Kompressor (2) verlässt, mit mindestens einem Brennstoff;
    - eine Turbine (3) zum Expandieren des Stroms des verbrannten heißen Gases, der den Brenner (3, 4) verlässt, und Verrichten von Arbeit an einem Rotor (7);
    wobei die Turbine (3) mindestens eine Stufenfalzanordnung nach einem der vorhergehenden Ansprüche umfasst.
EP17207850.3A 2017-12-15 2017-12-15 Stufenfalzdichtungsanordnung Active EP3498980B1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP17207850.3A EP3498980B1 (de) 2017-12-15 2017-12-15 Stufenfalzdichtungsanordnung
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 (de) 2017-12-15 2017-12-15 Stufenfalzdichtungsanordnung

Publications (2)

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

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP17207850.3A Active EP3498980B1 (de) 2017-12-15 2017-12-15 Stufenfalzdichtungsanordnung

Country Status (2)

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EP (1) EP3498980B1 (de)
CN (1) CN110005476B (de)

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 (de) * 2007-04-05 2008-10-16 Alstom Technology Ltd Shiplap-anordnung
DE502008000588D1 (de) * 2007-04-05 2010-06-10 Alstom Technology Ltd Spaltdichtung für Schaufeln einer Turbomaschine
US20120045337A1 (en) * 2010-08-20 2012-02-23 Michael James Fedor Turbine bucket assembly and methods for assembling same
JP5848439B2 (ja) * 2012-03-28 2016-01-27 三菱重工業株式会社 シール部材、タービン、及びガスタービン
EP2832952A1 (de) * 2013-07-31 2015-02-04 ALSTOM Technology Ltd Turbinenschaufel und Turbine mit verbesserter Abdichtung
EP2843197B1 (de) * 2013-08-29 2019-09-04 Ansaldo Energia Switzerland AG Schaufel einer rotierenden Strömungsmaschine, wobei die Schaufel eine spezifische Haltevorrichtung für eine radiale Streifendichtung aufweist
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
EP3498980A1 (de) 2019-06-19
CN110005476A (zh) 2019-07-12
CN110005476B (zh) 2022-11-08

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