EP2584151A2 - Agencement d'étanchéité pour une aube rotorique de turbine et moteur à turbine à gaz associé - Google Patents

Agencement d'étanchéité pour une aube rotorique de turbine et moteur à turbine à gaz associé Download PDF

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Publication number
EP2584151A2
EP2584151A2 EP12188728.5A EP12188728A EP2584151A2 EP 2584151 A2 EP2584151 A2 EP 2584151A2 EP 12188728 A EP12188728 A EP 12188728A EP 2584151 A2 EP2584151 A2 EP 2584151A2
Authority
EP
European Patent Office
Prior art keywords
seal
turbine
slot
shank
inches
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Withdrawn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
EP12188728.5A
Other languages
German (de)
English (en)
Inventor
Sergio Daniel Marques Amaral
Gary Michael Itzel
Xiuzhang James Zhang
Kenneth Dale Moore
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP2584151A2 publication Critical patent/EP2584151A2/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor

Definitions

  • the present invention relates to seals for air-ingesting turbomachines, and more particularly to a seal for the shank region of a rotating component of the turbomachine.
  • Conventional turbomachines includes compressor and turbine sections that each has a plurality of rotating components (compressor blades, turbine components, etc.) attached about a circumference of a turbine rotor. Each rotating component is located at a distance away from an adjacent rotating component to allow movement and expansion during operation.
  • Each rotatable component includes: a shank that attaches to the rotor, a platform, and an airfoil that extends radially outwardly from the platform.
  • the area between the adjacent rotating components is considered the shank pocket.
  • the cavities between the rotating components and adjacent stationary components forward and aft of the shank pocket are at different operating pressures. Fluid naturally flows from the higher pressure cavity to the lower pressure cavity through gaps; which allow for movement and expansion, between adjacent rotating components. In addition, fluid flowing over the platform can leak into the shank pocket. These sources of "cross-shank” leakage are detrimental to the performance of the turbomachine. The severity of the leakage depends, in part, on the size of the shank.
  • the system should provide a simple seal design that may be applied to a turbine bucket and/or a compressor blade.
  • a system comprising: a rotatable component comprising: an airfoil portion comprising a first end, an opposite second end, and suction and pressure surfaces located between the first end and the opposite second end; a shank portion comprising a mount and a slot, wherein the slot is positioned near a wall and is adjacent a downstream edge of the airfoil portion; a platform portion that connects the airfoil portion to the shank portion; a seal comprising: an arm portion; and a hook portion; wherein the arm and hook portions are shaped to mate with the slot such that the slot restrains the movement of the seal; wherein the seal is sized to substantially prevent a cooling flow from leaking through a shank pocket.
  • a system comprising: a gas turbine comprising: a compressor section and a turbine section; a turbine bucket installed in the turbine section, wherein the turbine bucket comprises: an airfoil comprising a tip, a base, and suction and pressure surfaces that connected the tip and the base; a shank comprising a mount and a slot, wherein the slot is positioned near a surface that is adjacent an edge of the airfoil, and an end of the slot is adjacent to a top portion of the mount; a platform portion that connects the airfoil to the shank; a seal comprising: an arm; and a hook; wherein the arm and hook are sized to allow insertion into the slot such that the slot secures the movement of the seal; wherein the seal has a width that substantially prevents a cooling flow from leaking through a shank pocket, which is formed between the shank portion of the rotatable component and an another shank portion of an adjacent rotatable component.
  • first, second, primary, secondary, etc. may be used herein to describe various elements, these elements should not be limited by these terms. These terms are only used to distinguish one element from another. For example, but not limiting to, a first element could be termed a second element, and, similarly, a second element could be termed a first element, without departing from the scope of example embodiments.
  • the term "and/or" includes any, and all, combinations of one or more of the associated listed items.
  • the present invention may be applied to the variety of turbomachines that produce an exhaust fluid, such as, but not limiting of, a heavy-duty gas turbine; an aero-derivative gas turbine; or the like.
  • An embodiment of the present invention may be applied to either a single turbomachine or a plurality of turbomachines.
  • An embodiment of the present invention may be applied to a turbomachine operating in a simple cycle or a combined cycle configuration.
  • An embodiment of the present invention takes the form of a seal that may substantially reduce cross-shank leakage.
  • the elements of the present invention may be fabricated of any material that can withstand the operating environment under which embodiments of the present invention may operate.
  • Embodiments of the seal may be connected to a wide variety of rotatable components including, but not limited to, compressor blades, turbine buckets, or the like.
  • FIG 1 is a schematic view, in cross-section, of a gas turbine 100, illustrating the environment in which an embodiment of the present invention operates.
  • FIG 1 illustrates a known configuration of a gas turbine 100 that includes: a compressor section 105; a combustion section 130; and a turbine section 150.
  • the compressor section 105 includes a plurality of rotating blades 110 and stationary vanes 115 structured to compress a fluid.
  • the compressor section 105 may also include a compressor discharge casing 125.
  • the combustion section 130 includes a plurality of combustion cans 135, a plurality of fuel nozzles 140, and a plurality of transition sections 145.
  • compressed air is received from the compressor section 105 and mixed with fuel received from a fuel source.
  • the mixture is ignited and creates a working fluid.
  • the working fluid generally flows downstream from the aft end of the plurality of fuel nozzles 140, downstream through the transition section 145, and into the turbine section 150.
  • the turbine section 150 includes a plurality of rotating components 155, and a plurality of stationary components 160.
  • the turbine section 150 converts the energy of the working fluid to a mechanical torque.
  • FIG 2 is a schematic illustrating a close-up elevation view of the turbine section 150 illustrated in FIG 1 .
  • the plurality of rotatable component 155 (hereinafter “turbine bucket”) are commonly arranged in a plurality of stages.
  • FIGS 1 and 2 illustrate an arrangement of three stages of turbine buckets 155.
  • FIGS 3A and 3B collectively FIG 3 , illustrate side and isometric views of the turbine buckets 155 of FIGS 1 and 2 .
  • Each of the turbine buckets 155 may comprise: an airfoil 165, a platform 167, and a shank 170.
  • the airfoil 165 may generally comprise a first end (or tip); an opposite second end (or base); and suction and pressure surfaces located between the first end and the opposite second end.
  • the shank 170 may comprise a mount 173, a slot 175, and a shank pocket 177.
  • An embodiment of the mount 173 may comprise any mating shape that allows the turbine bucket 155 to mate with a turbine wheel slot 405 on a turbine wheel 400, as illustrated in FIG 4 .
  • the slot 175 functions to secure a seal 180.
  • the shape of the slot 175 corresponds to that of the seal 180, which allows mating to occur, as illustrated in FIG 6 .
  • An embodiment of the slot 175 may be vertically positioned near a side wall that is substantially aligned with a downstream edge of the airfoil 165, as illustrated in FIGS 3 and 5 .
  • an end of the slot 175 is adjacent to a top portion of the mount 173.
  • an overall height of the slot 175 may extend from around the top portion of the mount 173 to a bottom portion of the platform 167; as illustrated in FIG 5 .
  • other embodiments may comprise a shorter height.
  • the platform 167 provides the structure that connects the bottom of the airfoil 165 to the top of the shank 170.
  • FIG 4 is a schematic illustrating an arrangement, facing downstream, of multiple rotating components 155 mounted on a turbine wheel 400.
  • the mount 173 is illustrated in a dovetail shape; however other forms of axially insertable mounts 173 may be used with embodiments of the present invention.
  • the mounts 173 are inserted into the turbine wheel slots 405, located along the outer periphery of the turbine wheel 400. This allows each turbine bucket 155 to be attached to the turbine wheel 400.
  • FIG 4 also provides an overview of the flow path of the working fluid and the cooling circuits; and how both of which impact the turbine bucket 155.
  • One cooling circuit utilizes the collective shank pockets 177 formed by shanks 170 and platforms 167 of adjacent turbine buckets 155. This design may extract air from a cooling purge 200 and uses that air to pressurize the shank pockets 177.
  • the shank pocket 177 can also be pressurized using coolant flows from other circuits. Once pressurized, the shank pockets 177 may supply cooling air to other locations on the platform 167. Impingement cooling is often incorporated in this type of cooling circuit to enhance heat transfer.
  • the cooling air may exit the shank pockets 177 through film cooling holes in the platform 167 or through axial cooling holes which direct the air out of the shank pocket 177.
  • Embodiments of the present invention provide a seal 180 that may prevent leakage of the working fluid out of those shank pockets 177.
  • the seal 180 may be very beneficial to the reducing cross-shank leakage.
  • FIG 6 is a partial-isometric view of a turbine bucket 155 and an embodiment of the seal 180, in accordance with an embodiment of the present invention.
  • the seal 180 is designed to take advantage of two deterministic that are naturally acting on the turbine buckets 155, as the gas turbine 105 operates. First, a centrifugal force that may regularly apply tension. Second, is a force due to the pressure difference between the shank pocket 177 and an aft cooling purge 600 that may constantly force the seal 180 into the slot 175. This second force may help to maintain a relatively tight clearance.
  • An embodiment of the seal 180 may comprise the form of a strip of metal that is inserted between adjacent turbine buckets 155 and attached near the dovetail region associated with the mount 173.
  • the seal 180 may comprise an arm 185 with a hook 190 at an end.
  • the hook 190 may be located at the portion of the seal 180 that is located near the mount 173. The hook 190 helps to position the seal 180 within the mating slot 175.
  • the seal 180 may prevent coolant flow from leaking through the shank pocket 177.
  • the location of the seal 180 may be critical. As the turbine bucket 155 begins to rotate, the seal 180 may be in tension instead of compression. Here, compression may damage the seal 180. Operationally, a large pressure difference typically exists between the shank pocket 177 and the aft cooling purge 600. Here, the force exerted on the seal 180 may prevent leakage, as discussed.
  • FIG 7 illustrates another partial-isometric view of a rotating component 155 and a seal 180, in accordance with an embodiment of the present invention.
  • An embodiment of the seal 180 may be manufactured of a relatively thin sheet of metal that is generally flexible to conform to the surfaces of the mating slot 175, and provide a desired seal against the intrusion of the working fluid.
  • the material utilized for the seal 180 should be selected to withstand the pressures and temperatures associated with a specific application and to allow for some plastic deformation.
  • the seal 180 may plastically deform in response to the thermal and centrifugal loads to conform and fit the contours of the slot 175. The plastic deformation may provide a desired seal against the intrusion of the working fluid and may minimize leakage of cooling/ purge flow.
  • FIG 7 illustrates reference locations for the following dimensional ranges, in accordance with embodiments of the present invention.
  • a width ("W") of the seal 180 may comprise a range of from about 0.2 inches to about 1.0 inch.
  • a length ("L") of the seal 180 may comprise a range of from about 2.0 inches to about 10.0 inches.
  • a thickness ("T") of the seal 180 may comprise a range of from about 0.1 inches to about 0.5 inches.
  • the shape of the hook 190 may include an arc portion, a polygon or combinations thereof.
  • a diameter ("D") of the arc of the hook 190 may comprise a range of from about 0.2 inches to about 1.0 inch.
  • embodiments of the present invention may allow continued use or turbine buckets 155 having relatively larger shanks 170, while minimizing cross-shack leakage with a simple seal 180.
  • Embodiments of the seal 180 may improve the overall performance and efficiency of the gas turbine 105.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP12188728.5A 2011-10-17 2012-10-16 Agencement d'étanchéité pour une aube rotorique de turbine et moteur à turbine à gaz associé Withdrawn EP2584151A2 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/274,950 US20130094969A1 (en) 2011-10-17 2011-10-17 System for sealing a shaft

Publications (1)

Publication Number Publication Date
EP2584151A2 true EP2584151A2 (fr) 2013-04-24

Family

ID=47115376

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12188728.5A Withdrawn EP2584151A2 (fr) 2011-10-17 2012-10-16 Agencement d'étanchéité pour une aube rotorique de turbine et moteur à turbine à gaz associé

Country Status (3)

Country Link
US (1) US20130094969A1 (fr)
EP (1) EP2584151A2 (fr)
CN (1) CN103047015A (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2843197A2 (fr) 2013-08-29 2015-03-04 Alstom Technology Ltd Aube de machine à flux rotatif avec joint d'étanchéité en bande
DE102013220467A1 (de) * 2013-10-10 2015-05-07 MTU Aero Engines AG Rotor mit einem Rotorgrundkörper und einer Mehrzahl daran angebrachter Laufschaufeln
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11156110B1 (en) * 2020-08-04 2021-10-26 General Electric Company Rotor assembly for a turbine section of a gas turbine engine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2912223A (en) * 1955-03-17 1959-11-10 Gen Electric Turbine bucket vibration dampener and sealing assembly
US6579065B2 (en) * 2001-09-13 2003-06-17 General Electric Co. Methods and apparatus for limiting fluid flow between adjacent rotor blades
GB2401658B (en) * 2003-05-16 2006-07-26 Rolls Royce Plc Sealing arrangement
US7575416B2 (en) * 2006-05-18 2009-08-18 United Technologies Corporation Rotor assembly for a rotary machine
US20100232939A1 (en) * 2009-03-12 2010-09-16 General Electric Company Machine Seal Assembly
US20110255958A1 (en) * 2010-04-16 2011-10-20 General Electric Company Seal member for hot gas path component
US8657574B2 (en) * 2010-11-04 2014-02-25 General Electric Company System and method for cooling a turbine bucket

Non-Patent Citations (1)

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

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2843197A2 (fr) 2013-08-29 2015-03-04 Alstom Technology Ltd Aube de machine à flux rotatif avec joint d'étanchéité en bande
EP2843197A3 (fr) * 2013-08-29 2015-07-22 Alstom Technology Ltd Aube de machine à flux rotatif avec joint d'étanchéité en bande
US9890651B2 (en) 2013-08-29 2018-02-13 Ansaldo Energia Switzerland AG Blade of a rotary flow machine with a radial strip seal
US10233766B2 (en) 2013-08-29 2019-03-19 Ansaldo Energia Switzerland AG Blade of a rotary flow machine with a radial strip seal
DE102013220467A1 (de) * 2013-10-10 2015-05-07 MTU Aero Engines AG Rotor mit einem Rotorgrundkörper und einer Mehrzahl daran angebrachter Laufschaufeln
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same

Also Published As

Publication number Publication date
CN103047015A (zh) 2013-04-17
US20130094969A1 (en) 2013-04-18

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