US3529906A - Static seal structure - Google Patents

Static seal structure Download PDF

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Publication number
US3529906A
US3529906A US771712A US3529906DA US3529906A US 3529906 A US3529906 A US 3529906A US 771712 A US771712 A US 771712A US 3529906D A US3529906D A US 3529906DA US 3529906 A US3529906 A US 3529906A
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US
United States
Prior art keywords
segments
housing
seal
link
seal structure
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.)
Expired - Lifetime
Application number
US771712A
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English (en)
Inventor
Leroy D Mclaurin
James H Borden
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CBS Corp
Original Assignee
Westinghouse Electric Corp
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Filing date
Publication date
Application filed by Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
Application granted granted Critical
Publication of US3529906A publication Critical patent/US3529906A/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D11/005—Sealing means between non relatively rotating elements

Definitions

  • An annular static seal structure is provided at the entrance to the stator of an axial flow turbine to minimize by-pass leakage around the first stage nozzle or stator vanes.
  • the seal structure includes a plurality of arcuate ring segments mounted end-toend in an annular seal housing and pressure loaded against the inner shroud of the first stage stator vanes. At the gaps between segments, one end of each segment is interconnected with one end of the adjacent segment by a radial link and a transverse key. The radial link prevents axial leakage and the transverse key prevents radial leakage which would otherwise by-pass the radial link.
  • This invention relates, generally, to elastic fluid machines and, more particularly, to static seals for axial flow gas turbines.
  • the first row vanes are usually manufactured in groups of 3 or 4 vanes, with clearance between each group for expansion. Due to unequal heating in the combustion system and hot spots in the vanes, each group may have a difierent radial expansion. Previous seal arrangements used on machines with lower pressure drops had gaps permitting axial leakage past the inner shroud on the stator vanes.
  • A11 object of this invention is to provide an effective sealing system for preventing by-pass leakage under the inner shroud of stator vanes in a turbine.
  • Another object of the invention is to provide a sealing system which prevents axial as well as radial leakage and has the ability to follow radial movement of each group of stator vanes without distorting the system in general.
  • a plurality of arcuate ring segments are slidably mounted end-to-end in a generally channel-shaped annular seal housing.
  • the segments are spring biased radially outwardly against the inner shroud of the first row of stator vanes in an axial flow gas turbine.
  • the ends of adjacent segments are intercounected by radial links and keys extending transversely to the links and disposed in intersecting grooves in the segments.
  • the clearances between members of the seal assembly are such that the seal segments can follow radial movement of an individual group of stator vanes.
  • FIG. 1 is a view, in axial section, of a portion of an axial flow gas turbine with an annular seal structure constructed in accordance with principles of the present inyention;
  • FIG. 2 is a view, in plan, of a portion of the seal iz tilcllule, looking in the direction of arrows II-II in FIG. 3 is a view, in elevation, of the portion of the seal structure shown in FIG. 2;
  • FIG. 4 is a fragmentary view, partly in section and partly in side elevation, showing one of the seal segments utilized in the seal structure.
  • FIG. 5 is an exploded view of the end portions of a pair of the seal segments and their associated seal link and seal key.
  • FIG. 1 there is shown therein a portion of an axial flow gas turbine 10 which includes an annular array of circumferentially spaced stationary blades or vanes 11 secured between arcuate outer shroud segments 12 and arcuate inner shroud segments 13.
  • the outer shroud segments 12 are mounted in a stator blade ring (not shown) disposed inside a turbine casing (not shown) which is generally circular in cross section.
  • An annular array of rotor blades 14 is disposed immediately down stream from the stationary blades 11.
  • the rotor blades 14- are suitably attached to the periphery of a rotor wheel secured to a shaft 16 rotatably mounted in the turbine casing.
  • the stationary blades 11 and the rotor blades 14 constitute the first stage of the turbine which may include other stationary and rotary blades disposed down stream from the blades 14, thereby increasing the number of stages in the turbine.
  • a hot motive gas is supplied to the turbine from suitable combustion chambers (not shown).
  • the hot motive gas flows from the combustion chambers to the blades 11 through a transition passageway 17 disposed between a transition cover plate 18 and an annular wall 19 of an air box or chamber 21.
  • the rotor 15 and the shaft 16 are driven by the energy extracted from the hot elastic fluid, in a manner well known in the art.
  • Compressed coolant fluid may, if desired, be introduced into the passageway 17 through a plurality of circumferentially spaced tubular shaped nozzle 22 extending through the annular wall 19 of the chamber 21 which is adapted to receive a flow of pressurized fluid, such as air, from a suitable source, such as a compressor (not shown).
  • a suitable source such as a compressor (not shown).
  • the chamber 21 is of annular shape and is formed between the wall 19 and a tubular wall 23 of a tube housing through which the shaft 16 extends.
  • a static seal structure 31 is provided to cooperte with the inner shroud segments 13 of the stator structure. As shown in FIGS.
  • the static seal structure 31 comprises an annular housing 33 which is generally channel-shaped in cross section and has an integrally formed disc-like portion 34 attached to a flange 35 on the tube wall 23 by means of a plurality of bolts 36
  • the housing 33 is supported inside the inner shroud segments 13, and the surface of an outer wall 49 of the housing has an annular groove 37 therein receiving an annular projection 38 on the end of the air chamber wall 19.
  • the housing 33 is in sealing relation with the wall 19, and the housing 33 with its integral disc portion 34 form a portion of the enclosure for the air chamber 21.
  • Indexing bolts 39 which extend through circumferentially spaced projections 41 on the chamber wall '19 are threaded into the housing 33, thereby locating the position of the wall 19 relative to the housing 33.
  • the seal structure 31 includes a plurality of arcuate seal ring segments 42 mounted end-to-end in the housing 33 with gaps 43 between adjacent ends of the ring segments.
  • internal shoulders 44 are provided on the inside walls of the housing 33 and projections 45 are provided on the segments 42, thereby slidably retaining the segments 42 between the walls of the housing 33 which is preferably made in two semi-circular portions.
  • each ring segment 42 is biased radially outwardly into contact with an inner shroud segment 13 by means of a leaf spring 46 disposed in a cavity 47 defined between the bottom 47 and side walls 49 and 51 of the channel shaped housing 33.
  • each spring 46 is retained in position in the cavity 47 and in a groove 50 in the segment 42 by means of a screw 52 which extends through the bottom of the housing 33, and through an opening 53 in the spring into a hole 54 in the segment 42.
  • the opening 53 and the hole 54 are slightly larger in diameter than the diameter of the screw 52 which is threaded into the housing 33.
  • the hole 54 extends in depth beyond the end of the screw 52.
  • each end of each ring segment 42 has a radial groove 55 in its periphery and an intersecting groove 56 extending transversely there to across the bottom of the groove 55.
  • a radial link 57 is disposed in a pair of grooves 55 in the adjacent ends of the two ring segments 42 and extends across the gap 43 between the ends of the segments.
  • the link 57 is retained in position by means of a screw 58 which is threaded into one end of the link 57 through an opening 59 in one end of each segment 42.
  • a transverse key 61 is disposed in the transverse groove 56 with the lower edge of the link 57 disposed in a slot 62 in the key 61.
  • the key 61 also bridges the gap 43 between the adjacent ends of two ring segments 42.
  • each segment is interconnected with the adjacent segment by the link 57 and the key 61.
  • the link 57 is effective to obstruct axial leakage and the key 61 is effective to obstruct radial leakage which would otherwise by-pass the link 57.
  • the seal members may be assembled in the following manner: A transverse key 61 is slid into the groove 56 in one of the segments 42 with the slot 62 in the key disposed in I means of the screw 58. Another segment 42 is then inthe mating grooves 55 and 56 in the end of that segment. The process is then repeated for another pair of seal ring segments.
  • the link is generally trapezoidal in shape and has a threaded hole 63 at the narrow end for receiving the screw 58.
  • the sloping surface between the wide end of the link and the narrow end is stepped at 64 for a purpose which will be explained more fully hereinafter.
  • the detail structure of the key 61 is generally of a dumbbell-shape having enlarged beveled end portions 65.
  • the beveled end portions permit the key 61 to rock in the ring segments 42, thereby permitting relative radial movement between adjacent ring segments without binding.
  • the ability of the seal structure to follow the radial movement of an individual stator group of vanes is insured by clearances C C and C as shown in FIG. 3.
  • the clearance C between the top of the link 57 and the outer peripheral surface of the ring segment 42 is provided by the step 64 in the sloping surface of the link 57.
  • clearance C is provided between the bottom edge of the link 57 and the bottom 66 of the vertical groove 55 in one end of each ring segment 42.
  • the bottom 67 of the groove 55 in the other end of each segment is slightly higher than bottom 66.
  • the clearance C between the bottom edge of the link 57 and the top of the key 61 is provided by the slot 62 in the key 61.
  • a plurality of openings 71 are provided in the wall 49 of the channel-shaped housing 33, as shown in FIGS. 1 and 4.
  • the openings 71 connect the air pressure chamber 21 with the cavity 47 underneath the seal ring segments 42.
  • a fluid pressure is maintained in the cavity 47.
  • the pressurized fluid is directed into the openings 71 by an annular flange 72 on the housing 33 and by the seal members 37 and 38 on the walls 49 and 19 previously described.
  • the pressurized fluid in the cavity 47 functions to prevent the hot motive fluid from bypassing the seal segments 42 through the cavity 47, thereby improving the efliciency of the seal structure.
  • the invention provides a seal structure which is particularly suitable for utilization in conjunction with the first row of stator vane segments in a gas turbine.
  • the present seal structure is not limited in its application to gas turbines, but may be utilized in elastic fluid machines of other types.
  • the seal structure is relatively simple to construct and assemble and is efficient in operation.
  • stator having an annular array of stationary vanes with inner shroud segments secured to the vanes, an annular housing disposed inside the inner shroud segments,
  • each end of each ring segment has a pair of intersecting grooves therein receiving an interconnecting link and a cooperating key.
  • annular housing is generally channel-shaped in cross section with the ring segments slidably disposed in the housing channel.
  • the resilient means includes leaf springs disposed in said cavity.
  • each key has a slot therein receiving a cooperating link.
  • each key is generally of a dumbbell-shape having rounded end portions permitting radial movement of the seal ring segments.
US771712A 1968-10-30 1968-10-30 Static seal structure Expired - Lifetime US3529906A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US77171268A 1968-10-30 1968-10-30

Publications (1)

Publication Number Publication Date
US3529906A true US3529906A (en) 1970-09-22

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US771712A Expired - Lifetime US3529906A (en) 1968-10-30 1968-10-30 Static seal structure

Country Status (7)

Country Link
US (1) US3529906A (de)
CH (1) CH498285A (de)
DE (1) DE1950812C3 (de)
FR (1) FR2021903A1 (de)
GB (1) GB1241358A (de)
NL (1) NL6916221A (de)
SE (1) SE362470B (de)

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4355952A (en) * 1979-06-29 1982-10-26 Westinghouse Electric Corp. Combustion turbine vane assembly
US4385864A (en) * 1979-08-04 1983-05-31 Motoren Und Turbinen Union Munchen Gmbh Sealing device for the free ends of variable stator vanes of a gas turbine
US4576548A (en) * 1984-01-17 1986-03-18 Westinghouse Electric Corp. Self-aligning static seal for gas turbine stator vanes
US4688988A (en) * 1984-12-17 1987-08-25 United Technologies Corporation Coolable stator assembly for a gas turbine engine
US4863343A (en) * 1988-05-16 1989-09-05 Westinghouse Electric Corp. Turbine vane shroud sealing system
US4916892A (en) * 1988-05-06 1990-04-17 General Electric Company High pressure seal
US5149250A (en) * 1991-02-28 1992-09-22 General Electric Company Gas turbine vane assembly seal and support system
US5284347A (en) * 1991-03-25 1994-02-08 General Electric Company Gas bearing sealing means
EP1033477A2 (de) * 1999-03-03 2000-09-06 Mitsubishi Heavy Industries, Ltd. Mantelring für Gasturbinen
US20050120718A1 (en) * 2003-12-03 2005-06-09 Lorin Markarian Gas turbine combustor sliding joint
US20060005529A1 (en) * 2004-07-09 2006-01-12 Penda Allan R Blade clearance control
US20070237628A1 (en) * 2006-04-07 2007-10-11 Adis William E Variable clearance positive pressure packing ring and carrier arrangement with coil type spring
US20070237623A1 (en) * 2006-04-07 2007-10-11 Adis William E Variable clearance positive pressure packing ring and carrier arrangement with leaf springs
US20090155068A1 (en) * 2007-12-13 2009-06-18 Eric Durocher Radial loading element for turbine vane
US20090269188A1 (en) * 2008-04-29 2009-10-29 Yves Martin Shroud segment arrangement for gas turbine engines
US20100236257A1 (en) * 2006-09-15 2010-09-23 Nicolas Grivas Gas turbine combustor exit duct and hp vane interface
US8684673B2 (en) 2010-06-02 2014-04-01 Siemens Energy, Inc. Static seal for turbine engine
US9097115B2 (en) 2011-07-01 2015-08-04 Alstom Technology Ltd Turbine vane
EP2905475A3 (de) * 2008-12-25 2015-12-16 Mitsubishi Hitachi Power Systems, Ltd. Statorschaufel-Anordnung und Gasturbine
US10513940B2 (en) * 2014-06-26 2019-12-24 Siemens Aktiengesellschaft Turbomachine with an outer sealing and use of the turbomachine

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE448757B (sv) * 1980-05-19 1987-03-16 Avco Corp Munstycke for en gasturbinmotor
JPS57134302U (de) * 1981-02-17 1982-08-21
US4897021A (en) * 1988-06-02 1990-01-30 United Technologies Corporation Stator vane asssembly for an axial flow rotary machine
GB2280935A (en) * 1993-06-12 1995-02-15 Rolls Royce Plc Cooled sealing strip for nozzle guide vane segments
GB2296295A (en) * 1994-12-23 1996-06-26 Rolls Royce Plc Sealing arrangement for a gas turbine engine

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE187838C (de) *
US2623357A (en) * 1945-09-06 1952-12-30 Birmann Rudolph Gas turbine power plant having means to cool and means to compress combustion products passing through the turbine
US2625367A (en) * 1949-08-27 1953-01-13 Armstrong Siddeley Motors Ltd Mounting of the stator blades of gaseous fluid turbines
US2651496A (en) * 1951-10-10 1953-09-08 Gen Electric Variable area nozzle for hightemperature turbines
US2919891A (en) * 1957-06-17 1960-01-05 Gen Electric Gas turbine diaphragm assembly
US3129922A (en) * 1961-11-27 1964-04-21 Frederick A Rosenthal Self centering ring seal
US3224194A (en) * 1963-06-26 1965-12-21 Curtiss Wright Corp Gas turbine engine
GB1020900A (en) * 1961-11-28 1966-02-23 Licentia Gmbh A seal between the rotor blades and the casing of axial-flow turbo-machines
US3383033A (en) * 1966-04-27 1968-05-14 Gen Electric Sealing means for axial flow compressor discharge
US3391904A (en) * 1966-11-02 1968-07-09 United Aircraft Corp Optimum response tip seal

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE187838C (de) *
US2623357A (en) * 1945-09-06 1952-12-30 Birmann Rudolph Gas turbine power plant having means to cool and means to compress combustion products passing through the turbine
US2625367A (en) * 1949-08-27 1953-01-13 Armstrong Siddeley Motors Ltd Mounting of the stator blades of gaseous fluid turbines
US2651496A (en) * 1951-10-10 1953-09-08 Gen Electric Variable area nozzle for hightemperature turbines
US2919891A (en) * 1957-06-17 1960-01-05 Gen Electric Gas turbine diaphragm assembly
US3129922A (en) * 1961-11-27 1964-04-21 Frederick A Rosenthal Self centering ring seal
GB1020900A (en) * 1961-11-28 1966-02-23 Licentia Gmbh A seal between the rotor blades and the casing of axial-flow turbo-machines
US3224194A (en) * 1963-06-26 1965-12-21 Curtiss Wright Corp Gas turbine engine
US3383033A (en) * 1966-04-27 1968-05-14 Gen Electric Sealing means for axial flow compressor discharge
US3391904A (en) * 1966-11-02 1968-07-09 United Aircraft Corp Optimum response tip seal

Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4355952A (en) * 1979-06-29 1982-10-26 Westinghouse Electric Corp. Combustion turbine vane assembly
US4385864A (en) * 1979-08-04 1983-05-31 Motoren Und Turbinen Union Munchen Gmbh Sealing device for the free ends of variable stator vanes of a gas turbine
US4576548A (en) * 1984-01-17 1986-03-18 Westinghouse Electric Corp. Self-aligning static seal for gas turbine stator vanes
US4688988A (en) * 1984-12-17 1987-08-25 United Technologies Corporation Coolable stator assembly for a gas turbine engine
US4916892A (en) * 1988-05-06 1990-04-17 General Electric Company High pressure seal
US4863343A (en) * 1988-05-16 1989-09-05 Westinghouse Electric Corp. Turbine vane shroud sealing system
EP0343361A1 (de) * 1988-05-16 1989-11-29 Westinghouse Electric Corporation Dichtungssystem eines Turbinenleitschaufelringes
US5149250A (en) * 1991-02-28 1992-09-22 General Electric Company Gas turbine vane assembly seal and support system
US5284347A (en) * 1991-03-25 1994-02-08 General Electric Company Gas bearing sealing means
EP1033477A2 (de) * 1999-03-03 2000-09-06 Mitsubishi Heavy Industries, Ltd. Mantelring für Gasturbinen
EP1033477A3 (de) * 1999-03-03 2002-05-29 Mitsubishi Heavy Industries, Ltd. Mantelring für Gasturbinen
US20050120718A1 (en) * 2003-12-03 2005-06-09 Lorin Markarian Gas turbine combustor sliding joint
WO2005054632A1 (en) * 2003-12-03 2005-06-16 Pratt & Whitney Canada Corp. Sliding joint between combustor wall and nozzle platform
US7000406B2 (en) 2003-12-03 2006-02-21 Pratt & Whitney Canada Corp. Gas turbine combustor sliding joint
US20060005529A1 (en) * 2004-07-09 2006-01-12 Penda Allan R Blade clearance control
US7596954B2 (en) 2004-07-09 2009-10-06 United Technologies Corporation Blade clearance control
US20070237623A1 (en) * 2006-04-07 2007-10-11 Adis William E Variable clearance positive pressure packing ring and carrier arrangement with leaf springs
US7704041B2 (en) * 2006-04-07 2010-04-27 General Electric Company Variable clearance positive pressure packing ring and carrier arrangement with coil type spring
US7384235B2 (en) * 2006-04-07 2008-06-10 General Electric Company Variable clearance positive pressure packing ring and carrier arrangement with leaf springs
US20070237628A1 (en) * 2006-04-07 2007-10-11 Adis William E Variable clearance positive pressure packing ring and carrier arrangement with coil type spring
US8166767B2 (en) 2006-09-15 2012-05-01 Pratt & Whitney Canada Corp. Gas turbine combustor exit duct and hp vane interface
US20100236257A1 (en) * 2006-09-15 2010-09-23 Nicolas Grivas Gas turbine combustor exit duct and hp vane interface
US7836702B2 (en) 2006-09-15 2010-11-23 Pratt & Whitney Canada Corp. Gas turbine combustor exit duct and HP vane interface
US20110023499A1 (en) * 2006-09-15 2011-02-03 Nicolas Grivas Gas turbine combustor exit duct and hp vane interface
US8096746B2 (en) * 2007-12-13 2012-01-17 Pratt & Whitney Canada Corp. Radial loading element for turbine vane
US20090155068A1 (en) * 2007-12-13 2009-06-18 Eric Durocher Radial loading element for turbine vane
US20090269188A1 (en) * 2008-04-29 2009-10-29 Yves Martin Shroud segment arrangement for gas turbine engines
US8240985B2 (en) * 2008-04-29 2012-08-14 Pratt & Whitney Canada Corp. Shroud segment arrangement for gas turbine engines
EP2905475A3 (de) * 2008-12-25 2015-12-16 Mitsubishi Hitachi Power Systems, Ltd. Statorschaufel-Anordnung und Gasturbine
US8684673B2 (en) 2010-06-02 2014-04-01 Siemens Energy, Inc. Static seal for turbine engine
US9097115B2 (en) 2011-07-01 2015-08-04 Alstom Technology Ltd Turbine vane
US10513940B2 (en) * 2014-06-26 2019-12-24 Siemens Aktiengesellschaft Turbomachine with an outer sealing and use of the turbomachine

Also Published As

Publication number Publication date
CH498285A (de) 1970-10-31
DE1950812A1 (de) 1970-06-18
GB1241358A (en) 1971-08-04
SE362470B (de) 1973-12-10
DE1950812C3 (de) 1978-12-21
FR2021903A1 (de) 1970-07-24
NL6916221A (de) 1970-05-04
DE1950812B2 (de) 1977-09-29

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