EP1898053A2 - Singlet welded nozzle hybrid design for a turbine - Google Patents

Singlet welded nozzle hybrid design for a turbine Download PDF

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Publication number
EP1898053A2
EP1898053A2 EP07114373A EP07114373A EP1898053A2 EP 1898053 A2 EP1898053 A2 EP 1898053A2 EP 07114373 A EP07114373 A EP 07114373A EP 07114373 A EP07114373 A EP 07114373A EP 1898053 A2 EP1898053 A2 EP 1898053A2
Authority
EP
European Patent Office
Prior art keywords
turbine
nozzle
sidewall
ring
welded
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Withdrawn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
EP07114373A
Other languages
German (de)
English (en)
French (fr)
Inventor
Steven Sebastian Burdgick
Thomas William Crall
Larry Duclos
Thomas Patrick Russo
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 EP1898053A2 publication Critical patent/EP1898053A2/en
Withdrawn legal-status Critical Current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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • 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
    • F05D2240/55—Seals
    • F05D2240/56—Brush seals

Definitions

  • Typical diaphragm stages are constructed using one of two methods.
  • the first method is a "band/ring" method that uses an assembly comprised of a plurality of airfoils contained in inner and outer bands and then that banded airfoil assembly is welded into inner (web) and outer rings.
  • the second method involves welding airfoils directly to inner and outer rings using a fillet weld at the interface.
  • the second method is typically used for larger airfoils, where access for creating the weld is possible.
  • the invention provides a singlet welded nozzle hybrid design which inter alia addresses the distortion problem noted above. More particularly, in an example embodiment of the invention a construction is provided wherein a singlet (single airfoil with sidewalls) is seated directly in a radial and circumferential groove of an outer carrier or welded to an outer ring and seated with in a groove of an outer carrier.
  • the inner connection is effected with a unique inner sidewall construction.
  • the inner sidewalls are mechanically fit and welded to a circumferentially extending ring, or to one another via a small radial weld between inner sidewall endfaces (slashfaces).
  • the invention may be embodied in a turbine comprising: a turbine nozzle segment having at least one stator airfoil, an inner sidewall at a radially inner end of the stator airfoil, and an outer sidewall structure at the radially outer end of said stator airfoil, a radially inner surface of the inner sidewall having a circumferential groove defined therein, and a complimentary ring component having a key portion for being received in said circumferential groove, said ring component extending at least part circumferentially of an axis of the turbine to engage an inner sidewall of at least two respectively adjacent nozzle inner sidewalls, wherein the ring component is mechanically secured to the nozzle inner sidewalls.
  • the invention may also be embodied in a turbine comprising: a turbine nozzle segment having at least one stator airfoil and including an inner sidewall at a radially inner end of the stator airfoil and an outer sidewall structure at the radially outer end of said stator airfoil; and an outer ring carrier having a radially inwardly open groove; wherein said outer sidewall is configured to slideably engage said groove in a radial direction while being restricted from moving in an axial direction with respect thereto, and the inner sidewall is mechanically coupled to circumferentally adjacent turbine nozzle segments.
  • the invention may also be embodied in a turbine comprising: a turbine nozzle segment having at least one stator airfoil and including an inner sidewall at a radially inner end of the stator airfoil and an outer sidewall structure at the radially outer end of said stator airfoil, wherein respectively adjacent nozzle inner sidewall endfaces are welded or braised together.
  • FIGURE 1 shows the traditional construction of an impulse type turbine stage that uses partition, bands and rings welded into an assembly. More specifically, this traditional construction uses a diaphragm assembly 10 comprised of a plurality of airfoils 12 contained in inner and outer bands 14, 16 that is welded as at 18, 20, 22, 24 into an inner ring (web) 26 and an outer ring 28.
  • Various aspects of the present invention improve the steam path flow path of the stator nozzle (diaphragm) components. This is done with a simplified, determinant, low heat input singlet welded assembly using novel approaches at the inner sidewall connection such as, for example, welded endwalls, low heat input seal welds with mechanical lock, or small ring key welded to inner sidewalls, as described hereinbelow.
  • the invention also improves the production cost and cycle by adding features that assist in assembly procedures and that assist in machining fixturing. Further, the invention adds features that reduce the risk of unintended turbine shut down due to hardware weld failure.
  • the singlet welded nozzle hybrid design createds a construction that includes a singlet, that is, a single airfoil with respective inner and outer sidewall components.
  • the outer sidewall component mechanically fit and then welded to an outer ring carrier.
  • connection of the inner sidewall can be achieved in several ways.
  • the inner sidewalls of the singlets of the diaphragm can be mechanically fit and welded to either a seal carrier or a small ring, or a small radial weld may be provided between the sidewall endfaces (slashfaces) of circumferentially adjacent singlets.
  • This construction is suited primarily to nozzle constructions that are considered reaction-type turbines or "drum” construction turbine sections, characterized by much smaller axial spacing of the stages and a typically increased number of stages.
  • FIGURE 2 illustrates an example embodiment of the invention wherein a singlet nozzle is slid into a carrier.
  • the singlet is comprised of an airfoil 30 and inner and outer sidewalls 32, 34.
  • an outer ring carrier 40 configured to slideably engage and radially and axially mechanically lock to outer sidewall 34.
  • the outer sidewall 34 is formed to extend radially for being received in a circumferentially extending groove 42 of the outer ring carrier 40.
  • the axial end faces of the outer sidewall 34 define first and second grooves 44, 46 that extend in a circumferential direction for receiving corresponding axial protrusions 48, 50 in the ring carrier groove 42.
  • the radially inner sidewalls 32 of circumferentially adjacent singlets are coupled.
  • an inner ring 52 may be keyed and welded 54, 56 to the construction.
  • the keyed inner ring may define a seal carrier.
  • the singlet inner sidewalls 32 are welded to each other at their abutting endfaces. Examples the above mentioned assemblies are described in greater detail below with reference to FIGURES 3-6 and 9. These example embodiments are described using some of the same reference numbers (used with reference to FIGURE 2) and with some corresponding reference numbers, but incremented by multiples of 100, as appropriate.
  • FIGURE 3 shows an example inner ring 152 disposed to extend at least part circumferentially of the rotor, thereby to couple circumferentially adjacent singlets.
  • the inner ring 152 includes a keyed protrusion 158 to engage a corresponding cutout 160 of the inner sidewall 132. More specifically, the singlets are retained axially by the inner ring interfacing with the keyed cutout 160 of the inner sidewall.
  • a low heat ring weld (seal weld) 154, 156 is provided between [each] nozzle inner sidewall and the seal carrier.
  • This weld is not necessarily meant to be a significant structural weld as the mechanical interlock at the radially outer end (FIGURE 2) will hold the nozzle ends from moving downstream.
  • a mechanical design as described allows welds that are very low heat input to cause minimal distortion of the airfoil and steampath surfaces.
  • the inner ring 152 is configured to also comprise a seal carrier.
  • the seal carrier is very small in design such that it can fit in the small axial and radial spacing typical of drum construction turbine types. This is generally different from the significant real estate required to hold the traditional packing segments at the rotor interface.
  • the proposed carrier would facilitate the more advanced seals, i.e., brush seals, shingle type seals or abradable seals.
  • This carrier could also be coated with abradable spray prior to assembly and the small seal welds could be machined away for ring removal when a repair (re-coat) is required.
  • the inner seal carrier ring 152 carries a brush-type seal structure 162.
  • FIGURE 4 shows an alternate inner seal carrier ring 252, having a laminated-type seal 262.
  • a keyed interface 258/260 is provided between the seal carrier ring 252 and the inner sidewalls 232.
  • low heat ring welds (seal welds) 254, 256 are provided upstream and downstream, as illustrated, to fix the inner seal carrier ring 252 to the inner sidewalls 232 of the respective series of singlet nozzles.
  • FIGURE 5 depicts yet another embodiment of the inner carrier ring 352 that is retained axially as in the embodiments of FIGURES 3 and 4 by the interface of the inner seal carrier ring 352 with a keyed cutout 360 of the inner sidewall 332.
  • the seal carrier ring 352 has radial bolts 364 into the inner sidewall 332 and airfoil 330 to hold the carrier ring 352 in place with respect to the singlet nozzles.
  • the seal carrier ring 352 incorporates a brush-type seal 362, although the illustrated radial fastening could be incorporated in other inner ring structures without departing from this invention.
  • FIGURE 6 illustrates yet a further alternate embodiment of the invention wherein a key ring 452 is provided but the seal carrier aspect is omitted in its entirety.
  • the nozzle inner sidewalls each have a key notch or groove 460 defined circumferentially therethrough and the key ring 452 is seated in the circumferential groove 460 and welded in place with a low heat ring welds (seal welds) 454, 456.
  • the welded key ring thus circumferentially integrates the nozzle singlets with both a welded and mechanical interlock.
  • FIGURE 7 shows a further alternate embodiment wherein the singlet nozzle outer sidewall 534 is welded to a solid outer ring 538 is using small axial welds forward and aft 566, 568. The assembly of the singlet nozzle and outer ring is then seated in a corresponding groove 542 of the nozzle carrier 540.
  • the nozzle assembly (outer ring 538 and nozzle(s) welded thereto) are not welded to the carrier; the nozzle assembly can move radially in the carrier groove 542.
  • the carrier 540 does not have circumferential grooves as is typical in a reaction turbine design that uses slid-in nozzles.
  • the mechanical features of the interface between the singlet and the outer ring 538 are used as an assembly and alignment feature and allow for improved reliability and risk abatement.
  • the mechanical lock between the ring and nozzle(s) means that, in the even of failure of an airfoil, the rings and nozzles cannot go downstream as there is a mechanical interference preventing the assembly from failing due to the pressure.
  • the mechanical lock serves the purpose of a pre-determined and repeatable weld stop. In this regard, the weld beam (assuming an EB weld) would stop when it hits the radial interlock interface.
  • a further advantage of the FIGURE 7 embodiment is that the radially outer face of the nozzle outer sidewall is configured as a flat end instead of a more costly circumferentially cut end as in the embodiment of FIGURE 2.
  • FIGURE 7 has an inner ring 552 that is mechanically locked and braised or welded to the nozzle inner sidewall 532, as in the embodiments of FIGURES 2-4 and 6, or just mechanically locked to the nozzle, as in the embodiment of FIGURE 5.
  • FIGURES 8 and 9 depict yet a further example embodiment of the invention. More particularly, FIGURE 8 shows a side view of the singlet nozzle welded as in the FIGURE 7 embodiment to an outer ring 538 at the radially outer sidewall 534. On the radially inner end, however, rather than providing a ring seal 552 as in the FIGURE 7 embodiment, the inner sidewall 632 endfaces 670 are welded to each other. Thus, FIGURE 9 shows in an axial view the inner sidewall endwalls/slashfaces respectively welded together. It is envisioned that this weld would be a low heat input weld similar to a butt weld done with a Laser weld or Electron Beam weld (EBW).
  • EBW Electron Beam weld
  • This interface could also be considered for a braise joint should it be considered more economical.
  • the goal of this radial weld is to create the continuous coupling of the inner sidewall. This weld does not necessarily need to be a structural weld but more to cause zero gap between the nozzle segment inner sidewalls (endfaces).
  • the typical singlet nozzle outer wall interface is a circumferentially cut end
  • the singlet nozzle outer sidewall interface may be machined as a flat end which is less costly than a circumferential cut end.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07114373A 2006-08-23 2007-08-15 Singlet welded nozzle hybrid design for a turbine Withdrawn EP1898053A2 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/508,170 US20080050222A1 (en) 2006-08-23 2006-08-23 Singlet welded nozzle hybrid design for a turbine

Publications (1)

Publication Number Publication Date
EP1898053A2 true EP1898053A2 (en) 2008-03-12

Family

ID=38457865

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07114373A Withdrawn EP1898053A2 (en) 2006-08-23 2007-08-15 Singlet welded nozzle hybrid design for a turbine

Country Status (5)

Country Link
US (1) US20080050222A1 (zh)
EP (1) EP1898053A2 (zh)
JP (1) JP2008051105A (zh)
KR (1) KR20080018118A (zh)
CN (1) CN101131100A (zh)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2348194A3 (en) * 2010-01-25 2013-05-22 Rolls-Royce plc Sealing arrangement for a gas turbine engine
US8562292B2 (en) 2010-12-02 2013-10-22 General Electric Company Steam turbine singlet interface for margin stage nozzles with pinned or bolted inner ring
US8684697B2 (en) 2010-12-13 2014-04-01 General Electric Company Steam turbine singlet nozzle design for breech loaded assembly
US10436047B2 (en) 2015-08-18 2019-10-08 General Electric Company Method for repair of a diaphragm of a rotary machine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8070429B2 (en) * 2009-03-11 2011-12-06 General Electric Company Turbine singlet nozzle assembly with mechanical and weld fabrication
US9011078B2 (en) * 2012-01-09 2015-04-21 General Electric Company Turbine vane seal carrier with slots for cooling and assembly

Family Cites Families (12)

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Publication number Priority date Publication date Assignee Title
US1998951A (en) * 1933-11-15 1935-04-23 Gen Electric Nozzle diaphragm
US3529905A (en) * 1966-12-12 1970-09-22 Gen Motors Corp Cellular metal and seal
DE1551193A1 (de) * 1967-05-16 1970-03-12 Licentia Gmbh Schnellstartturbine
US3501246A (en) * 1967-12-29 1970-03-17 Westinghouse Electric Corp Axial fluid-flow machine
US4889470A (en) * 1988-08-01 1989-12-26 Westinghouse Electric Corp. Compressor diaphragm assembly
US5622475A (en) * 1994-08-30 1997-04-22 General Electric Company Double rabbet rotor blade retention assembly
US5584654A (en) * 1995-12-22 1996-12-17 General Electric Company Gas turbine engine fan stator
JP3477347B2 (ja) * 1997-07-30 2003-12-10 三菱重工業株式会社 ガスタービン段間部シール装置
JP4040922B2 (ja) * 2001-07-19 2008-01-30 株式会社東芝 組立式ノズルダイアフラムおよびその組立方法
US6896482B2 (en) * 2003-09-03 2005-05-24 General Electric Company Expanding sealing strips for steam turbines
US7160078B2 (en) * 2004-09-23 2007-01-09 General Electric Company Mechanical solution for rail retention of turbine nozzles
US7287956B2 (en) * 2004-12-22 2007-10-30 General Electric Company Removable abradable seal carriers for sealing between rotary and stationary turbine components

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2348194A3 (en) * 2010-01-25 2013-05-22 Rolls-Royce plc Sealing arrangement for a gas turbine engine
US8562292B2 (en) 2010-12-02 2013-10-22 General Electric Company Steam turbine singlet interface for margin stage nozzles with pinned or bolted inner ring
US8684697B2 (en) 2010-12-13 2014-04-01 General Electric Company Steam turbine singlet nozzle design for breech loaded assembly
US10436047B2 (en) 2015-08-18 2019-10-08 General Electric Company Method for repair of a diaphragm of a rotary machine

Also Published As

Publication number Publication date
JP2008051105A (ja) 2008-03-06
CN101131100A (zh) 2008-02-27
US20080050222A1 (en) 2008-02-28
KR20080018118A (ko) 2008-02-27

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