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WO2016118138A1 - Système d'étanchéité pour segments annulaires radialement vers l'extérieur d'un ensemble turbine dans un moteur à turbine - Google Patents

Système d'étanchéité pour segments annulaires radialement vers l'extérieur d'un ensemble turbine dans un moteur à turbine Download PDF

Info

Publication number
WO2016118138A1
WO2016118138A1 PCT/US2015/012372 US2015012372W WO2016118138A1 WO 2016118138 A1 WO2016118138 A1 WO 2016118138A1 US 2015012372 W US2015012372 W US 2015012372W WO 2016118138 A1 WO2016118138 A1 WO 2016118138A1
Authority
WO
WIPO (PCT)
Prior art keywords
seal plate
receiver
ring segment
retention device
seal
Prior art date
Application number
PCT/US2015/012372
Other languages
English (en)
Inventor
Runzhong CHEN
Original Assignee
Siemens Aktiengesellschaft
Siemens Energy, Inc.
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 Aktiengesellschaft, Siemens Energy, Inc. filed Critical Siemens Aktiengesellschaft
Priority to PCT/US2015/012372 priority Critical patent/WO2016118138A1/fr
Publication of WO2016118138A1 publication Critical patent/WO2016118138A1/fr

Links

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
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding

Definitions

  • This invention is directed generally to turbine engines, and more particularly to seal systems for turbine ring segment assemblies for turbine engines.
  • a plurality of ring segments are typically assembled to form a ring radially outward of the tips of turbine blade forming a portion of a stage within a turbine assembly in a gas turbine engine.
  • the ring segments are typically sealed together with seals to limit hot gas from escaping the hot gas pathway.
  • the seals have been formed from plates that are welded in place. During use, these plates can work free and become dislocated. The dislocated plates are often swept into the hot gas path and flow downstream causing significant damage to downstream turbine
  • the seal system may include a seal plate retention device that retains a seal plate between adjacent ring segments positioned radially outward of a circumferential row of turbine blades.
  • the seal plate retention device may retain the seal plate in position without welds.
  • the seal plate retention device may retain the seal plate at least partially within a first seal plate receiver in a first ring segment and a second seal plate receiver in a second ring segment.
  • the seal plate retention device may include one or more arms extending from the seal plate to provide a robust seal with reduced likelihood of becoming dislodged and flowing downstream where the seal plate would likely damage downstream components.
  • the gas turbine engine may include a turbine assembly formed from a rotor assembly having one or more turbine blades formed from a generally elongated airfoil having a leading edge, a trailing edge, a pressure side, a suction side, a tip at a first end and a platform coupled to a second end of the generally elongated airfoil opposite to the first end.
  • First and second ring segments may be positioned radially outward from the tip of the turbine blade. The first and second ring segments may be aligned in a circumferentially extending row and form at least a portion of a ring around a travel path of the turbine blade.
  • the first and second ring segments may each include an inner surface forming a portion of a hot gas path within the turbine assembly.
  • One or more seal plates may have one or more seal plate retention devices.
  • the seal plate may extend from an upstream edge of the first ring segment to a downstream end of the first ring segment.
  • One or more first seal plate receivers may be positioned in a first side surface of the first ring segment.
  • the first seal plate receiver may receive at least a portion of the seal plate.
  • One or more second seal plate receivers may be positioned in a second side surface of the second ring segment.
  • the first side surface of the first ring segment and the second side surface of the second ring segment may face each other.
  • the second seal plate receiver may receive at least a portion of the seal plate.
  • the seal plate retention device may be configured to prevent the seal plate from being released from being partially positioned within the first seal plate receiver and the one second seal plate receiver.
  • the seal plate retention device may enable the seal plate to be retained within the first seal plate receiver and the second seal plate receiver without a weld.
  • the seal plate retention device may include one or more first arms extending laterally from a first side of the seal plate.
  • the first seal plate receiver may include one or more retention device receivers receiving the first arm.
  • the seal plate retention device may include one or more second arms extending laterally from a second side of the seal plate.
  • the first arm may be positioned at an upstream edge of the seal plate.
  • the retention device receiver in the first seal plate receiver may be positioned at an upstream edge of the first ring segment.
  • the first seal plate receiver may include an opening in the upstream edge of the first ring segment.
  • the retention device receiver in the first seal plate receiver may include an opening in the upstream edge of the first ring segment.
  • the second seal plate receiver may include one or more retention device receivers receiving the second arm.
  • the second arm may be positioned at an upstream edge of the seal plate.
  • the retention device receiver in the second seal plate receiver may be positioned at an upstream edge of the second ring segment.
  • the second seal plate receiver may include an opening in the upstream edge of the second ring segment.
  • the retention device receiver in the second seal plate receiver may include an opening in the upstream edge of the second ring segment.
  • first and second ring segments have been described with respect to first and second ring segments.
  • the seal system is not limited to only being used between two rings segments; rather, the seal system may be used with a turbine ring segment assembly formed from a plurality of ring segments forming a ring radially outward of the turbine blades.
  • the plurality of ring segments may number more than two ring segments.
  • the first and second ring segments may be a plurality of first and second ring segments forming a ring around a travel path of the turbine blade such that each of the first and second ring segments are joined together via seal plates having at least one seal plate retention device.
  • Each first ring segment may include one or more first seal plate receivers receiving at least a portion of the seal plate
  • each second ring segment may include one or more second seal plate receivers receiving at least a portion of the seal plate. This pattern may be repeated as many times as necessary, depending on the number of ring segments, to form a ring.
  • seal plate retention device reduces the likelihood of damage to downstream turbine components by providing a robust seal with reduced likelihood of becoming.
  • seal plate retention device enables the seal plate to be retained within the first seal plate receiver and the second seal plate receiver without a weld.
  • seal system is not susceptible to failure due to failure of a weld.
  • Figure 1 is a cross-sectional, perspective view of a gas turbine engine with the seal system positioned between adjacent ring segments radially outward of turbine blades of the turbine assembly.
  • Figure 2 is a detail, cross-sectional view of with the seal system positioned between adjacent ring segments radially outward of turbine blades of the turbine assembly taken at detail 2-2 in Figure 1 .
  • Figure 3 is a perspective view looking radially inward on two adjacent ring segments coupled together with the seal system.
  • Figure 4 is a seal plate of the seal system.
  • Figure 5 is a perspective view of the second ring segment.
  • Figure 6 is a detail view of the retention device receiver positioned within the second seal plate receiver in the second ring segment.
  • the seal system 12 may include a seal plate retention device 16 that retains a seal plate 18 between adjacent ring segments 20, 22 positioned radially outward of a circumferential row 24 of turbine blades 26.
  • the seal plate retention device 16 may retain the seal plate 18 in position without welds.
  • the seal plate retention device 16 may retain the seal plate 18 at least partially within a first seal plate receiver 28 in a first ring segment 20 and a second seal plate receiver 30 in a second ring segment 22.
  • the seal plate retention device 16 may include one or more arms 32 extending from the seal plate 18 to provide a robust seal with reduced likelihood of becoming dislodged and flowing downstream where the seal plate 18 would likely damage downstream components.
  • the gas turbine engine 10 may include a turbine assembly 34 formed from a rotor assembly 36 having one or more turbine blades 26 formed from a generally elongated airfoil 38, as shown in Figure 2, having a leading edge 40, a trailing edge 42, a pressure side 44, a suction side 46, a tip 48 at a first end 49 and a platform 51 coupled to a second end 53 of the generally elongated airfoil 38 opposite to the first end 50.
  • the turbine blades 26 may have any appropriate configuration and is not limited to a particular design already in existence.
  • the turbine ring segment assembly 14, as shown in Figure 1 may be formed from first and second ring segments 20, 22, as shown in Figure 3, positioned radially outward from the tip 48 of the turbine blade 26.
  • the first and second ring segments 20, 22 may be aligned in a circumferentially extending row 24, as shown in Figure 2, and form at least a portion of a ring around a travel path 50 of the turbine blade 26.
  • the first and second ring segments 20, 22 may each include an inner surface 52 forming a portion of a hot gas path 54 within the turbine assembly 34.
  • the first and second ring segments 20, 22 may have any appropriate configuration and may be coupled to a turbine vane carrier or other support structure in an appropriate manner.
  • the seal system 12 may include one or more seal plates 18 having one or more seal plate retention devices 16, as shown in Figure 4.
  • the seal plate 18 may be formed from a generally elongated body 56 with a length that is substantially longer than a width of the body 56. In at least one embodiment, the length of the generally elongated body 56 may be greater than a width of the body 56, and the width of the body may be greater than a thickness of the body 56. In at least one embodiment, the seal plate 18 may extend from an upstream edge 74 of the first ring segment 20 to downstream end 94 of the first ring segment 20. The seal plate 18 may also extend from an upstream edge 88 of the second ring segment 22 to a downstream end 94 of the second ring segment 22.
  • the seal plate 18 may have a shorter length than a distance from the upstream edge 74 of the first ring segment 20 to downstream end 94 of the first ring segment 20 or the upstream edge 72 of the second ring segment 22 to the downstream end 94 of the second ring segment 22.
  • One or more first seal plate receivers 28 may be positioned in a first side surface 58 of the first ring segment 20, as shown in Figure 3.
  • the first seal plate receiver 28 may be configured to receive at least a portion of the seal plate 18.
  • the first seal plate receiver 28 may include an opening 60 in the first side surface 58 of the first ring segment 20.
  • the opening 60 may be sized to receive the seal plate 18.
  • the opening 60 may be sized in a radially extending direction to be greater than a thickness of the seal plate 18, thereby enabling the seal plate 18 to be received within the opening 60 and the first seal plate receiver 28.
  • One or more second seal plate receivers 30 may be positioned in a second side surface 62 of the second ring segment 22, as shown in Figures 3, 5 and 6.
  • the first side surface 58 of the first ring segment 20 and the second side surface 62 of the second ring segment 22 may face each other.
  • the first side surface 58 of the first ring segment 20 and the second side surface 62 of the second ring segment 22 may be parallel or may be positioned nonparallel and nonorthogonal to each other.
  • the second seal plate receiver 30 may be configured to receive at least a portion of the seal plate 18.
  • the second seal plate receiver 30 may include an opening 64 in the second side surface 60 of the second ring segment 22.
  • the opening 64 may be sized to receive the seal plate 18.
  • the opening 64 may be sized in a radially extending direction to be greater than a thickness of the seal plate 18, thereby enabling the seal plate 18 to be received within the opening 64 and the first seal plate receiver 28.
  • the seal plate retention device 16 may be configured to prevent the seal plate 18 from being released from being partially positioned within the first seal plate receiver 28 and the second seal plate receiver 30.
  • the seal plate retention device 16 may enable the seal plate 18 to be retained within the first seal plate receiver 28 and the second seal plate receiver 30 without a weld.
  • the seal plate retention device 16 may include one or more first arms 66 extending laterally from a first side 68 of the seal plate 18.
  • the first seal plate receiver 28 may include one or more retention device receivers 70 receiving the first arm 66.
  • the first arm 66 may be positioned at an upstream edge 72 of the seal plate 18.
  • the retention device receiver 70 in the first seal plate receiver 28 may be positioned at an upstream edge 74 of the first ring segment 20.
  • the first seal plate receiver 28 may include an opening 76 in the upstream edge 74 of the first ring segment 20.
  • the retention device receiver 70 in the first seal plate receiver 28 may include an opening 78 in the upstream edge 74 of the first ring segment 20.
  • the first arm 66 may extend generally orthogonal to the seal plate 18. In another embodiment, the first arm 66 may extend nonorthogonally and nonparallel to the seal plate 18. A downstream edge 102 of the first arm 66 may be orthogonal to the seal plate 18. Alternatively, the downstream edge 102 of the first arm 66 may be nonorthogonal to the seal plate 18, such that the downstream edge 102 of the first arm 66 may extend at an angle relative to the seal plate 18.
  • the seal plate retention device 16 may include one or more second arms 80 extending laterally from a second side 82 of the seal plate 18.
  • the second seal plate receiver 30 may include one or more retention device receivers 84 receiving the second arm 80.
  • the second arm 80 may be positioned at an upstream edge 72 of the seal plate 18.
  • the retention device receiver 84 in the second seal plate receiver 30 may be positioned at an upstream edge 88 of the second ring segment 22.
  • the second seal plate receiver 30 may include an opening 90 in the upstream edge 72 of the second ring segment 22.
  • the retention device receiver 84 in the second seal plate receiver 30 may include an opening 92 in the upstream edge 72 of the second ring segment 22.
  • the second arm 80 may extend generally orthogonal to the seal plate 18.
  • the second arm 80 may extend nonorthogonally and nonparallel to the seal plate 18.
  • a downstream edge 104 of the second arm 80 may be orthogonal to the seal plate 18.
  • the downstream edge 104 of the second arm 80 may be nonorthogonal to the seal plate 18, such that the downstream edge 104 of the second arm 80 may extend at an angle relative to the seal plate 18.
  • the seal system 12 has been described with respect to first and second ring segments 22. However, the seal system 12 is not limited to only being used between two rings segments 20, 22; rather, the seal system 12 may be used with a turbine ring segment assembly 14 formed from a plurality of ring segments 20, 22 forming a ring radially outward of the turbine blades 26.
  • the plurality of ring segments 20, 22 may number more than two ring segments.
  • the first and second ring segments 20, 22 may be a plurality of first and second ring segments 20, 22 forming a ring around a travel path 50 of the turbine blade 26 such that each of the first and second ring segments 20, 22 are joined together via seal plates 18 having at least one seal plate retention device 16.
  • Each first ring segment 20 may include one or more first seal plate receivers 28 receiving at least a portion of the seal plate 18, and each second ring segment 22 may include one or more second seal plate receivers 30 receiving at least a portion of the seal plate 18. This pattern may be repeated as many times as necessary, depending on the number of ring segments, to form a ring.
  • the seal plate 16 of the ring segments 20, 22 may be prevented from moving axially by a vane hook 96.
  • the vane hook 96 may be held in position via an iso ring 98.
  • the vane hook 96 prevents the first and second arms 66, 80 from becoming dislodged from residing within the retention device receiver 70 of the first seal plate receiver 28 and the retention device receiver 84 of the second seal plate receiver 30.
  • the vane hook 96 does this by preventing the first and second arms 66, 80 and the seal plate 16 from moving axially upstream.
  • the first and second arms 66, 80 remain positioned within the retention device receiver 70 of the first seal plate receiver 28 and the retention device receiver 84 of the second seal plate receiver 30, preventing damage from occurring to downstream turbine components.

Landscapes

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

Abstract

Moteur à turbine à gaz (10) doté d'un système d'étanchéité (12) pour un ensemble segment annulaire de turbine. Le système d'étanchéité (12) peut comprendre un dispositif de retenue (16) de plaque d'étanchéité qui retient une plaque d'étanchéité (18) entre des segments annulaires adjacents positionnés radialement vers l'extérieur d'une rangée circonférentielle (24) d'aubes (26) de turbine. Le dispositif de retenue (16) de plaque d'étanchéité peut retenir la plaque d'étanchéité (18) en position sans soudures. En particulier, le dispositif de retenue (16) de plaque d'étanchéité peut retenir la plaque d'étanchéité (18) au moins partiellement dans un premier récepteur (28) de plaque d'étanchéité dans un premier segment annulaire (20) et un seconde récepteur (30) de plaque d'étanchéité dans un second segment annulaire (22). Selon au moins un mode de réalisation, le dispositif de retenue (16) de plaque d'étanchéité peut comprendre un ou plusieurs bras (32) qui s'étendent depuis la plaque d'étanchéité (18) pour fournir une étanchéité solide avec un risque réduit de détachement et d'écoulement en aval où la plaque d'étanchéité (18) risquerait d'endommager les composants en aval.
PCT/US2015/012372 2015-01-22 2015-01-22 Système d'étanchéité pour segments annulaires radialement vers l'extérieur d'un ensemble turbine dans un moteur à turbine WO2016118138A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/US2015/012372 WO2016118138A1 (fr) 2015-01-22 2015-01-22 Système d'étanchéité pour segments annulaires radialement vers l'extérieur d'un ensemble turbine dans un moteur à turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2015/012372 WO2016118138A1 (fr) 2015-01-22 2015-01-22 Système d'étanchéité pour segments annulaires radialement vers l'extérieur d'un ensemble turbine dans un moteur à turbine

Publications (1)

Publication Number Publication Date
WO2016118138A1 true WO2016118138A1 (fr) 2016-07-28

Family

ID=52444667

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2015/012372 WO2016118138A1 (fr) 2015-01-22 2015-01-22 Système d'étanchéité pour segments annulaires radialement vers l'extérieur d'un ensemble turbine dans un moteur à turbine

Country Status (1)

Country Link
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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003014529A1 (fr) * 2001-08-03 2003-02-20 Hitachi, Ltd. Aube mobile de turbine
WO2004074640A1 (fr) * 2003-02-19 2004-09-02 Alstom Technology Ltd Systeme de joint notamment destine a des segments d'ailettes de turbines a gaz
US8105039B1 (en) * 2011-04-01 2012-01-31 United Technologies Corp. Airfoil tip shroud damper

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003014529A1 (fr) * 2001-08-03 2003-02-20 Hitachi, Ltd. Aube mobile de turbine
WO2004074640A1 (fr) * 2003-02-19 2004-09-02 Alstom Technology Ltd Systeme de joint notamment destine a des segments d'ailettes de turbines a gaz
US8105039B1 (en) * 2011-04-01 2012-01-31 United Technologies Corp. Airfoil tip shroud damper

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