US20120308360A1 - Overlap seal for turbine nozzle assembly - Google Patents

Overlap seal for turbine nozzle assembly Download PDF

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Publication number
US20120308360A1
US20120308360A1 US13/118,686 US201113118686A US2012308360A1 US 20120308360 A1 US20120308360 A1 US 20120308360A1 US 201113118686 A US201113118686 A US 201113118686A US 2012308360 A1 US2012308360 A1 US 2012308360A1
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US
United States
Prior art keywords
turbine
axial
axial tooth
tip portion
radially extending
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.)
Abandoned
Application number
US13/118,686
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English (en)
Inventor
Fred Thomas Willett, JR.
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
Priority to US13/118,686 priority Critical patent/US20120308360A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: WILLETT, FRED THOMAS, JR.
Priority to FR1254744A priority patent/FR2976019A1/fr
Priority to DE102012104620A priority patent/DE102012104620A1/de
Priority to RU2012122108/06A priority patent/RU2012122108A/ru
Publication of US20120308360A1 publication Critical patent/US20120308360A1/en
Abandoned legal-status Critical Current

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    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E20/00—Combustion technologies with mitigation potential
    • Y02E20/16—Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]

Definitions

  • the subject matter disclosed herein relates to turbines and, more particularly, to overlap seals for a turbine drum rotor cooling circuit.
  • Some power plant systems for example certain nuclear, simple cycle and combined cycle power plant systems, employ turbines in their design and operation. Some of these turbines are driven by a flow of high temperature steam which is directed over the buckets/blades of the turbine. This high temperature steam can have detrimental effects on the condition and longevity of certain components in the turbine such as a drum rotor. Repeated exposure of the drum rotor to high temperature steam may result in inefficient operation, corrosion, system damage, and a need for rotor repairs and/or rotor replacement. Some systems attempt to adapt the drum rotor to tolerate contact with high temperature steam in order to avoid shortening the lifespan of the drum rotor.
  • the drum rotor design and build process includes specific, temperature-resistant materials which are intended to allow the rotor to operate in contact with high temperature steam without significant degradation.
  • these specific, temperature-resistant materials may be expensive, contributing to increased overall system cost. Further, use of these materials may complicate the design and build process.
  • a turbine nozzle assembly includes: an outer diaphragm ring; a vane physically connected to the outer diaphragm ring; and an inner diaphragm ring physically connected to the vane, the inner diaphragm ring including a first axial tooth configured to interact and substantially form a seal with a second axial tooth disposed on a bucket shank.
  • a first aspect of the disclosure provides a turbine nozzle assembly including: an outer diaphragm ring; a vane physically connected to the outer diaphragm ring; and an inner diaphragm ring physically connected to the vane, the inner diaphragm ring including a first axial tooth configured to interact and substantially form a seal with a second axial tooth disposed on a bucket shank.
  • a second aspect provides a turbine bucket including: a blade; and a bucket shank coupled to the blade, wherein the bucket shank includes a first axial tooth configured to extend toward a nozzle, substantially forming a seal with the nozzle.
  • a third aspect provides a turbine including: a stator; a working fluid passage substantially surrounded by the stator; a drum rotor configured radially inboard of the working fluid passage; a cooling circuit fluidly connected to the drum rotor; and an overlap seal disposed between a nozzle coupled to the stator and a turbine bucket coupled to the drum rotor, the overlap seal substantially fluidly separating the working fluid passage and the cooling circuit, the overlap seal including: a first axial tooth disposed upon the nozzle; and a second axial tooth disposed upon the turbine bucket, the second axial tooth being configured to interact and substantially form a seal with the first axial tooth.
  • FIG. 1 shows a partial cut-away schematic view of a turbine system according to an embodiment of the invention.
  • FIG. 2 shows a partial cut-away schematic view of a turbine system according to an embodiment of the invention.
  • FIG. 3 shows a partial cut-away schematic view of portions of a turbine system according to an embodiment of the invention.
  • FIG. 4 shows a three-dimensional perspective view of a turbine bucket according to an embodiment of the invention.
  • FIG. 5 shows a partial cut-away schematic view of portions of a turbine system according to an embodiment of the invention.
  • FIG. 6 shows a partial cut-away schematic view of a nozzle and turbine bucket according to an embodiment of the invention.
  • FIG. 7 shows a partial cut-away schematic view of an embodiment of a nozzle and turbine bucket in accordance with an aspect of the invention.
  • FIG. 8 shows a partial cut-away schematic view of an embodiment of a nozzle and turbine bucket in accordance with an aspect of the invention.
  • FIG. 9 shows a partial cut-away schematic view of an embodiment of a nozzle and turbine bucket in accordance with an aspect of the invention.
  • FIG. 10 shows a schematic block diagram illustrating portions of a combined cycle power plant system according to embodiments of the invention.
  • FIG. 11 shows a schematic block diagram illustrating portions of a single-shaft combined cycle power plant system according to embodiments of the invention.
  • Some turbines include static nozzle assemblies that direct flow of a working fluid into turbine buckets connected to a rotating drum rotor.
  • the turbine buckets include bucket shanks and blades (airfoils) and the nozzle assembly includes a plurality of nozzles, “vanes” or “airfoils” and is sometimes referred to as a “diaphragm” or “nozzle assembly stage.”
  • Steam turbine diaphragms include two rings, the outer diaphragm ring and the inner diaphragm ring. These two rings are separated by and coupled to one another via a plurality of vanes.
  • the nozzle assembly is typically comprised of two halves, one upper and one lower, each containing an inner ring, an outer ring, and a plurality of vanes. The upper and lower halves are assembled around the rotor.
  • aspects of the invention provide for systems and devices configured to thermally protect portions of a turbine from damage due to contact with a turbine working fluid (e.g., high temperature steam) by using overlap seals and a cooling circuit.
  • the cooling circuit supplies a cooling fluid (e.g., low temperature steam) to the drum rotor.
  • the low temperature steam travels through the drum rotor via the cooling circuit which is defined in part by axial passages through the turbine buckets, and overlap seals which are disposed between nozzles and turbine buckets in the turbine.
  • the overlap seals substantially blocking the axial gap between bucket platforms and nozzle root bands and restricting radially inward or outward flows.
  • turbines driven by high temperature steam are often employed as part of the system.
  • the high temperature steam is directed through multiple sets of turbine buckets, thereby rotating a drum rotor and converting thermal energy into mechanical energy.
  • the high temperature steam may have negative effects on certain components of the turbine such as the drum rotor.
  • the high temperature of the steam can cause material damage to the drum rotor, increasing the maintenance cost of the system and significantly reducing the lifespan of the drum rotor.
  • FIG. 1 a partial cross-sectional view of a turbine 100 is shown according to embodiments of the invention.
  • Turbine 100 may include a drum rotor 10 (partially shown in FIG.
  • Drum rotor 10 may include at least one substantially circumferential dovetail slot 40 along its outer circumference.
  • a turbine bucket 12 may be secured within at least one substantially circumferential dovetail slot 40 on drum rotor 10 .
  • Drum rotor 10 may include a plurality of substantially circumferential dovetail slots 40 and a plurality of turbine buckets 12 secured therein as is known in the art.
  • Stator 15 may include at least one nozzle 17 secured within a nozzle slot 19 .
  • stator 15 may include a plurality of nozzles 17 which define stages of the turbine and may be secured within nozzle slots 19 .
  • Nozzles 17 and turbine buckets 12 may radially extend respectively from stator 15 and drum rotor 10 , such that nozzles 17 and turbine buckets 12 are interspersed along an axial length of turbine 100 .
  • a working fluid, such as steam, may be directed to a downstream location 14 , along primary working fluid passage 5 through turbine buckets 12 and nozzles 17 to assist the rotation of drum rotor 10 .
  • FIG. 2 a schematic partial cut-away side-view of a turbine 200 including an overlap seal 207 is shown according to embodiments. It is understood that elements similarly numbered between FIG. 1 and FIG. 2 may be substantially similar as described with reference to FIG. 1 . Further, in embodiments shown and described with reference to FIGS. 2-11 , like numbering may represent like elements. Redundant explanation of these elements has been omitted for clarity. Finally, it is understood that the components of FIGS. 1-11 and their accompanying descriptions may be applied to any embodiment described herein.
  • turbine 200 may include a packing head 210 .
  • a cooling fluid may be introduced into turbine 200 through a cooling circuit 7 via a snout 202 in packing head 210 .
  • the fluid introduced through cooling circuit 7 may include steam or any other fluid as is known in the art.
  • Snout 202 may be configured to supply fluid to an annulus 206 via coolant delivery passages 204 .
  • packing head 210 may include a plurality of snouts 202 configured to introduce cooling fluid into turbine 200 via cooling circuit 7 .
  • packing head 210 may include a single coolant delivery passage 204 .
  • coolant delivery passages 204 may be configured as straight radially extending passages.
  • coolant delivery passages 204 may be configured as a tortuous set of passages.
  • cooling circuit 7 may direct a fluid to annulus 206 via snout 202 and coolant delivery passages 204 . From annulus 206 , cooling circuit 7 directs the fluid through drum rotor 10 . In drum rotor 10 , cooling circuit 7 is further defined by overlap seal 207 disposed between turbine bucket 12 and nozzle 17 . Overlap seal 207 is configured to shield drum rotor 10 from fluid and/or thermal contact with a working fluid passage 5 and to fluidly separate working fluid passage 5 and cooling circuit 7 .
  • FIG. 3 a partial cut-away of an embodiment of a turbine 300 is shown having cooling circuit 7 partially defined by a plurality of overlap seals 207 and a set of axial passages 302 (shown in phantom) formed through turbine bucket shanks 502 .
  • axial passages 302 may be fluidly connected to cooling circuit 7 , allowing fluid to pass from annulus 206 through multiple stages of turbine 300 via axial passages 302 .
  • the plurality of overlap seals 207 disposed on a turbine bucket shank 502 of turbine bucket 12 and an inner diaphragm ring 507 of nozzle 17 .
  • cooling circuit 7 may pass through a set of nozzle root seals 304 disposed between rotor 10 and nozzles 17 .
  • cooling circuit 7 may be pressurized such that a positive pressure differential is created relative to working fluid passage 5 .
  • working fluid passage 5 may be pressurized such that a positive pressure differential is created relative to cooling circuit 7 .
  • a fluid passing through cooling circuit 7 may be at a low temperature relative to a fluid passing through working fluid passage 5 .
  • cooling circuit 7 may exhaust the cooling fluid into working fluid passage 5 .
  • FIG. 4 a partial three-dimensional perspective of an environment 400 including an embodiment of a turbine bucket shank 502 is shown having a set of axial passages 302 there through.
  • Axial passages 302 enable the passing of a fluid through a plurality of stages in a turbine.
  • axial passages 302 may be machined into bucket shank 502 .
  • axial passages 302 may be formed in bucket shank 502 .
  • axial passages 302 may be fluidly connected to cooling circuit 7 .
  • FIG. 5 a partial cut-away of a portion of an embodiment of a turbine 500 is shown having axial teeth 508 disposed upon an inner diaphragm ring 507 of nozzle 17 and axial teeth 509 disposed upon a bucket shank 502 of turbine bucket 12 .
  • axial teeth 508 extend toward bucket shank 502 such that axial teeth 508 overlap and interact with axial teeth 509 which extend toward inner diaphragm ring 507 , thereby forming a plurality of overlap seals 207 .
  • Plurality of overlap seals 207 partially define cooling circuit 7 along with axial passage 302 (shown in phantom) and an axial passage 510 (shown in phantom).
  • turbine bucket 12 includes bucket shank 502 and a blade 504 .
  • Nozzle 17 includes an outer diaphragm ring 505 , inner diaphragm ring 507 and a nozzle vane 503 .
  • overlap seals 207 substantially fluidly separate working fluid passage 5 and cooling circuit 7 which is radially inboard of working fluid passage 5 and passes below axial teeth 508 and 509 , and through axial passages 302 and 510 .
  • cooling circuit 7 may be exhausted into working fluid passage 5 via axial passage 510 .
  • nozzle vane 503 may have a height between about 1 inch and about 2 inches, and a width between about 1 inch and about 2 inches.
  • nozzle vane 503 may have a height between about 2 inches and about 3 inches, and a width between about 2 inches and about 3 inches. In one embodiment, nozzle vanes 503 may be circumferentially spaced between about 0.2 inches and about 0.7 inches relative one another.
  • FIG. 6 a partial cut-away view of an embodiment of a nozzle 17 and set of turbine buckets 12 is shown having a plurality of axial teeth 508 and 509 .
  • two axial teeth 508 disposed on inner diaphragm ring 507 may be configured between two axial teeth 509 disposed on bucket shank 502 so as to interact and form overlap seals 207 .
  • overlap seal 207 may be comprised of any number of axial teeth 508 and 509 .
  • Overlap seal 207 with axial passages 302 partially defining cooling circuit 7 which may flow through nozzle root seals 304 .
  • FIG. 7 a partial cut-away of an embodiment of a nozzle 17 and set of turbine buckets 12 is shown having axial teeth 508 configured relative to axial teeth 509 so as to form overlap seals 207 .
  • axial teeth 508 disposed on inner diaphragm ring 507 include a radially extending tip portion 808 .
  • Radially extending tip portion 808 further reducing a clearance between axial teeth 508 and 509 , and substantially forming a seal there between.
  • FIG. 8 a partial cut-away view of an embodiment of a nozzle 17 and set of turbine buckets 12 is shown having axial teeth 508 configured relative to axial teeth 509 so as to form overlap seals 207 .
  • axial teeth 509 disposed on bucket shanks 502 include a radially extending tip portion 809 . Radially extending tip portion 809 further reducing a clearance between axial teeth 508 and 509 , and substantially forming a seal there between.
  • FIG. 9 a partial cut-away view of an embodiment of a nozzle 17 and set of turbine buckets 12 is shown having axial teeth 508 configured relative to axial teeth 509 so as to form overlap seals 207 .
  • axial teeth 508 include a radially extending tip portion 808 and axial teeth 509 include a radially extending tip portion 809 . Radially extending tip portions 808 and 809 further reducing a clearance between axial teeth 508 and 509 , and substantially forming a seal there between.
  • Combined cycle power plant 900 may include, for example, a gas turbine 902 operably connected to a generator 908 .
  • Generator 908 and gas turbine 902 may be mechanically coupled by a shaft 907 , which may transfer energy between a drive shaft (not shown) of gas turbine 902 and generator 908 .
  • a heat exchanger 904 operably connected to gas turbine 902 and a steam turbine 906 .
  • Heat exchanger 904 may be fluidly connected to both gas turbine 902 and a steam turbine 906 via conventional conduits (numbering omitted).
  • Gas turbine 902 and/or steam turbine 906 may be fluidly connected to cooling circuit 7 of FIG. 3 or other embodiments described herein.
  • Heat exchanger 904 may be a conventional heat recovery steam generator (HRSG), such as those used in conventional combined cycle power systems. As is known in the art of power generation, HRSG 904 may use hot exhaust from gas turbine 902 , combined with a water supply, to create steam which is fed to steam turbine 906 .
  • Steam turbine 906 may optionally be coupled to a second generator system 908 (via a second shaft 907 ). It is understood that generators 908 and shafts 907 may be of any size or type known in the art and may differ depending upon their application or the system to which they are connected.
  • cooling circuit 7 may receive a fluid from HRSG 904 .
  • cooling circuit 7 may receive a fluid from steam turbine 906 .
  • cooling circuit 7 receives a fluid from a fluid source 909 .
  • Fluid source 909 may be a compressor, pressurized gas source or other fluid source as is known in the art.
  • cooling circuit 7 may receive a fluid in the form of compressed air generated from the operation of gas turbine 902 .
  • steam turbine 906 may be fluidly integrated with cooling circuit 7 .
  • a single shaft combined cycle power plant 990 may include a single generator 908 coupled to both gas turbine 902 and steam turbine 906 via a single shaft 907 .
  • Steam turbine 906 and/or gas turbine 902 may be fluidly connected to cooling circuit 7 of FIG. 3 or other embodiments 200 , 400 , 500 , 600 , 700 , 800 or 900 described herein.
  • the overlap seals and cooling circuit of the present disclosure are not limited to any one particular turbine, power generation system or other system, and may be used with other power generation systems and/or systems (e.g., combined cycle, simple cycle, nuclear reactor, etc.). Additionally, the overlap seals and cooling circuit of the present invention may be used with other systems not described herein that may benefit from the thermal protection of the cooling circuit described herein.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US13/118,686 2011-05-31 2011-05-31 Overlap seal for turbine nozzle assembly Abandoned US20120308360A1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US13/118,686 US20120308360A1 (en) 2011-05-31 2011-05-31 Overlap seal for turbine nozzle assembly
FR1254744A FR2976019A1 (fr) 2011-05-31 2012-05-24 Distributeur de turbine
DE102012104620A DE102012104620A1 (de) 2011-05-31 2012-05-29 Überlappungsdichtung für eine Turbinenleitdüsenbaugruppe
RU2012122108/06A RU2012122108A (ru) 2011-05-31 2012-05-30 Сопловой аппарат турбины, турбинная лопатка и турбина

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/118,686 US20120308360A1 (en) 2011-05-31 2011-05-31 Overlap seal for turbine nozzle assembly

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US20120308360A1 true US20120308360A1 (en) 2012-12-06

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US13/118,686 Abandoned US20120308360A1 (en) 2011-05-31 2011-05-31 Overlap seal for turbine nozzle assembly

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US (1) US20120308360A1 (de)
DE (1) DE102012104620A1 (de)
FR (1) FR2976019A1 (de)
RU (1) RU2012122108A (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20180371917A1 (en) * 2015-12-24 2018-12-27 Mitsubishi Hitachi Power Systems, Ltd. Steam turbine

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1819864A (en) * 1930-03-24 1931-08-18 Gen Electric Elastic fluid turbine
US2552239A (en) * 1946-10-29 1951-05-08 Gen Electric Turbine rotor cooling arrangement
US4882902A (en) * 1986-04-30 1989-11-28 General Electric Company Turbine cooling air transferring apparatus
US6506016B1 (en) * 2001-11-15 2003-01-14 General Electric Company Angel wing seals for blades of a gas turbine and methods for determining angel wing seal profiles
US6916151B2 (en) * 2003-02-06 2005-07-12 Snecma Moteurs Ventilation device for a high pressure turbine rotor of a turbomachine
US7186074B2 (en) * 2003-05-13 2007-03-06 Alstom Technology, Ltd. Axial flow stream turbines
US20070224035A1 (en) * 2005-09-16 2007-09-27 General Electric Company Angel wing seals for turbine blades and methods for selecting stator, rotor and wing seal profiles
US7488153B2 (en) * 2002-07-01 2009-02-10 Alstom Technology Ltd. Steam turbine
US20100008760A1 (en) * 2008-07-10 2010-01-14 Honeywell International Inc. Gas turbine engine assemblies with recirculated hot gas ingestion

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1819864A (en) * 1930-03-24 1931-08-18 Gen Electric Elastic fluid turbine
US2552239A (en) * 1946-10-29 1951-05-08 Gen Electric Turbine rotor cooling arrangement
US4882902A (en) * 1986-04-30 1989-11-28 General Electric Company Turbine cooling air transferring apparatus
US6506016B1 (en) * 2001-11-15 2003-01-14 General Electric Company Angel wing seals for blades of a gas turbine and methods for determining angel wing seal profiles
US7488153B2 (en) * 2002-07-01 2009-02-10 Alstom Technology Ltd. Steam turbine
US6916151B2 (en) * 2003-02-06 2005-07-12 Snecma Moteurs Ventilation device for a high pressure turbine rotor of a turbomachine
US7186074B2 (en) * 2003-05-13 2007-03-06 Alstom Technology, Ltd. Axial flow stream turbines
US20070224035A1 (en) * 2005-09-16 2007-09-27 General Electric Company Angel wing seals for turbine blades and methods for selecting stator, rotor and wing seal profiles
US20100008760A1 (en) * 2008-07-10 2010-01-14 Honeywell International Inc. Gas turbine engine assemblies with recirculated hot gas ingestion

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20180371917A1 (en) * 2015-12-24 2018-12-27 Mitsubishi Hitachi Power Systems, Ltd. Steam turbine
US10876408B2 (en) * 2015-12-24 2020-12-29 Mitsubishi Power, Ltd. Steam turbine

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Publication number Publication date
FR2976019A1 (fr) 2012-12-07
RU2012122108A (ru) 2013-12-10
DE102012104620A1 (de) 2012-12-06

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AS Assignment

Owner name: GENERAL ELECTRIC COMPANY, NEW YORK

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:WILLETT, FRED THOMAS, JR.;REEL/FRAME:026453/0100

Effective date: 20110527

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION