US3656862A - Segmented seal assembly - Google Patents

Segmented seal assembly Download PDF

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Publication number
US3656862A
US3656862A US51970A US3656862DA US3656862A US 3656862 A US3656862 A US 3656862A US 51970 A US51970 A US 51970A US 3656862D A US3656862D A US 3656862DA US 3656862 A US3656862 A US 3656862A
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US
United States
Prior art keywords
blade ring
turbine
segments
face
seal assembly
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
US51970A
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English (en)
Inventor
Thomas J Rahaim
George M Mierley Sr
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.)
Westinghouse Electric Corp
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Westinghouse Electric Corp
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 Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
Application granted granted Critical
Publication of US3656862A publication Critical patent/US3656862A/en
Anticipated expiration legal-status Critical
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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb

Definitions

  • ABSTRACT A light weight seal assembly divided into arcuate segments surrounds the tips of an annular row of rotating blades of an axial flowgas turbine. Each segment comprises formed sheet metal members brazed together and attached to the blade ring in the turbine casing. Leakage through expansion gaps between segments is prevented by sealing strips which bridge the gaps. Heat is transferred from the light weight seal structure into the relatively massive blade ring which is cooled by an external air supply. A soft wearable liner is brazed to the inside of the segment to insulate against heat transfer from the gas stream into the blade ring.
  • This invention relates, generally, to elastic fluid machines and, more particularly, to a segmented seal assembly for axial flow gas turbines.
  • annular seal assembly divided into a plurality of arcuate segments surrounds a row of rotating blades of an axial flow turbine.
  • Each segment comprises an axially extending member and a radially extending member of formed sheet metalbrazed together and attached to the blade ring in the stator casing of the turbine.
  • a honeycombed liner composed of a relatively soft wearable material is secured on the inner surface of each segment to insulate against heat transfer from the motive fluid into the blade ring. Leakage through expansion gaps between segments is prevented by sealing strips which bridge the gaps. Heat is transferred from the light weight seal structure into the relatively massive blade ring which is cooled by an external air supply.
  • FIG. 1 is a view, partly in axial section and partly in elevation, of a portion of an axial flow gas turbine with a segmented seal assembly constructed in accordance with principles of the present invention
  • FIG. 2 is an isometric view of one arcuate segment of the seal assembly
  • FIG. 3 is a view, in elevation taken along line IIIIII in FIG. 1, showing an expansion gap between adjacent seal segments;
  • FIG. 4 is a view, similar to FIG. 1, of a modified seal assembly.
  • the structure shown therein comprises 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 (not shown).
  • the outer shroud segments 12 are mounted in a stator blade ring 13 disposed inside a turbine casing (not shown) which is generally circular in cross section.
  • An annular row of rotor blades 14 is disposed immediately downstream from the stationary vanes 11.
  • the rotor blades 14 are suitably attached to the periphery of a rotor wheel (not shown) secured to a shaft (not shown) rotatably mounted in the turbine casing in a manner well known in the art.
  • the stationary blades 11 and the rotor blades 14 constitute the last stage of the turbine which includes other stationary and rotary blades disposed upstream from the blades 14, thereby providing a multi-stage 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 through the stationary vanes and the rotating blades, thereby driving the turbine shaft by energy extracted from the hot motive fluid in a manner well known in the art.
  • annular seal assembly 2l surrounds the row of rotating blades 14$.
  • the seal assembly 21 is divided into a plurality of arcuate segments 22 which are disposed end-to-end around the rotating blades 14.
  • the segments 22 are supported by the blade ring 13 in a manner which will be described more fully hereinafter.
  • each segment 22 comprises a generally axially disposed member 23 and a radially disposed member 2A which are preferably formed from relatively lightweight sheet metal and brazed together.
  • An angularly disposed brace member 25, also formed from sheet metal, may be secured to the members 23 and 24 to maintain the members in the desired angular relation.
  • Expansion gaps 26 are provided between adjacent segments to permit circumferential expansion due to heating of the segments. Leakage through the expansion gaps is prevented by sealing strips 27 which bridge the gaps between the members 23. Sealing strips 28 bridge the gaps between the radially extending members 24. The strips 27 and 26 may be secured to the members 23 and 24, respectively, as by brazing.
  • a honeycombed soft wearable liner 30 is secured to the inside of each arcuate member 23.
  • the liner 30 is preferably composed of a metal which is softer than the metal of which the blades 14 are composed, thereby permitting the liner to wear away if it is rubbed by the rotating blades.
  • the turbine may be constructed with relatively small cold tip clearance between the tips of the blades and the liner which provides a more eflicient stage and more horsepower output from the turbine.
  • the wearable material, which is secured to the member 23, as by brazing, will wear clear if rubbing occurs, thus permitting minimum possible tip clearance.
  • the honeycomb material insulates against heat transfer from the gas stream into the blade ring, thereby increasing the efiiciency of the turbine. Heat is transferred from the light weight seal structure into the relatively massive blade ring to reduce expansion of the seal members.
  • the blade ring 113 may be cooled by an external cool air supply in a manner known in the art, for example as disclosed in US. Pat. No. 3,427,000, issued Feb. II, 1969, to A. J. Scalzo and assigned to Westinghouse Electric Corporation, to decrease expansion of the blade ring during transient conditions.
  • the annular seal assembly 21 may consist of 36 segments 22.
  • the radially extending member 24 of each segment may be attached to a radially extending face 31 on the end of the blade ring 13 by means of a bolt 32 which is threaded into the blade ring 13.
  • An opening 33 is provided in the brace member 25 to permit access to the head of the bolt 32.
  • FIG. I Another advantage of the seal arrangement shown in FIG. I is that several inches of material have been removed from the rear end of the blade ring 113 as shown by the dot-dash line 34 which shows the prior contour of the blade ring. The removal of this material results in a lighter and less costly blade ring.
  • the seal mounting arrangement shown in FIG. I is suitable for use with the last stage of a multistage turbine.
  • the seal mounting arrangement shown in FIG. 4 is suitable for use with an intermediate stage of a multistage turbine.
  • an annular recess 35 is provided in the blade ring 13 to provide a radially extending face 31a on the blade ring to which the radially extending member 24 of each seal segment 22 is attached by means of a bolt 32.
  • the annular seal assembly may be utilized with an intermediate stage of the turbine without interferring with the mounting of the stationary vanes in the blade ring of the turbine.
  • a seal ring 36 is retained in position by an outwardly extending extension 37 on the member 23 to prevent leakage through the joint between members 12 and 13.
  • the ring 36 may be an On'ng divided into several sections.
  • the annular seal assembly may be utilized with the rotary blades of an intermediate stage as well as with the rotary blades of the last stage of a multi-stage turbine.
  • the invention provides a light weight seal assembly for use with the rotating blades of a turbine which makes it possible to maintain minimum tip clearance for the blades, thereby reducing leakage of the motive fluid around the turbine blades and increasing the efiiciency of the turbine.
  • Heat is transferred from the light weight seal structure into the relatively massive blade ring which supports the seal structure. Also, heat losses from the hot motive fluid are reduced by the honeycombed structure of the wearable liner utilized in the seal assembly.
  • stator blade ring having an annular array of stationary vanes mounted therein
  • annular seal assembly divided into a plurality of arcuate segments surrounding the row of rotor blades
  • each segment comprising a generally axially disposed member and a radially disposed member secured together
  • said segments being spaced circumferentially to provide expansion gaps between segments, and having sealing strips bridging said gaps
  • said blade ring having a radially disposed face thereon
  • threaded screw means attaching the radially disposed members to said face.
  • the radial face is on the end of the blade ring, and the seal assembly extends axially from the blade ring face in a cantilever fashion.
  • the blade ring has a second annular array of stationary vanes mounted thereto and forming a part of a succeeding stage
  • the blade ring has an annular recess between said arrays of vanes providing said face
  • the axially disposed member has an outwardly extending extension thcreon

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US51970A 1970-07-02 1970-07-02 Segmented seal assembly Expired - Lifetime US3656862A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US5197070A 1970-07-02 1970-07-02

Publications (1)

Publication Number Publication Date
US3656862A true US3656862A (en) 1972-04-18

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
US51970A Expired - Lifetime US3656862A (en) 1970-07-02 1970-07-02 Segmented seal assembly

Country Status (8)

Country Link
US (1) US3656862A (fr)
JP (1) JPS5020201B1 (fr)
BE (1) BE769254A (fr)
CH (1) CH541066A (fr)
DE (1) DE2131855A1 (fr)
FR (1) FR2103007A5 (fr)
GB (1) GB1306575A (fr)
NL (1) NL7109117A (fr)

Cited By (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3756741A (en) * 1971-12-17 1973-09-04 Jacuzzi Bros Inc Jet propulsion pump assembly
US3981609A (en) * 1975-06-02 1976-09-21 United Technologies Corporation Coolable blade tip shroud
US4101242A (en) * 1975-06-20 1978-07-18 Rolls-Royce Limited Matching thermal expansion of components of turbo-machines
US4222706A (en) * 1977-08-26 1980-09-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Porous abradable shroud with transverse partitions
US4346904A (en) * 1980-11-26 1982-08-31 Watkins Jr Shelton Honeycomb structure for use in abradable seals
US4553901A (en) * 1983-12-21 1985-11-19 United Technologies Corporation Stator structure for a gas turbine engine
US4643638A (en) * 1983-12-21 1987-02-17 United Technologies Corporation Stator structure for supporting an outer air seal in a gas turbine engine
US4687412A (en) * 1985-07-03 1987-08-18 Pratt & Whitney Canada Inc. Impeller shroud
US5001483A (en) * 1989-10-23 1991-03-19 Westinghouse Electric Corp. Digital to analog converter for an acoustic charge transport device
US5044881A (en) * 1988-12-22 1991-09-03 Rolls-Royce Plc Turbomachine clearance control
US5165848A (en) * 1991-07-09 1992-11-24 General Electric Company Vane liner with axially positioned heat shields
US5174714A (en) * 1991-07-09 1992-12-29 General Electric Company Heat shield mechanism for turbine engines
US5176495A (en) * 1991-07-09 1993-01-05 General Electric Company Thermal shielding apparatus or radiositor for a gas turbine engine
US5195868A (en) * 1991-07-09 1993-03-23 General Electric Company Heat shield for a compressor/stator structure
US5238365A (en) * 1991-07-09 1993-08-24 General Electric Company Assembly for thermal shielding of low pressure turbine
WO1994008143A1 (fr) * 1992-10-07 1994-04-14 University Of Alabama At Birmingham Joint d'etancheite pour degagement d'entree
US5524846A (en) * 1993-12-21 1996-06-11 The Boeing Company Fire protection system for airplanes
US6382905B1 (en) * 2000-04-28 2002-05-07 General Electric Company Fan casing liner support
GB2382380A (en) * 2001-11-24 2003-05-28 Rolls Royce Plc A removable abradable lining for the casing assembly of a gas turbine engine
US6682298B2 (en) 2002-05-17 2004-01-27 David George Demontmorency Rotating shaft confinement system
US20050089390A1 (en) * 2003-08-18 2005-04-28 Snecma Moteurs Abradable device on the blower casing of a gas turbine engine
US20050200080A1 (en) * 2004-03-10 2005-09-15 Siemens Westinghouse Power Corporation Seal for a turbine engine
US20070065277A1 (en) * 2005-09-19 2007-03-22 Ingersoll-Rand Company Centrifugal compressor including a seal system
US20070063449A1 (en) * 2005-09-19 2007-03-22 Ingersoll-Rand Company Stationary seal ring for a centrifugal compressor
US20070065276A1 (en) * 2005-09-19 2007-03-22 Ingersoll-Rand Company Impeller for a centrifugal compressor
US20080063508A1 (en) * 2006-09-08 2008-03-13 Barry Barnett Fan case abradable
US20120260670A1 (en) * 2011-04-18 2012-10-18 General Electric Company Apparatus to seal with a turbine blade stage in a gas turbine
EP2719869A1 (fr) * 2012-10-12 2014-04-16 MTU Aero Engines GmbH Étanchéification axiale dans une structure de boîtier pour une turbomachine
EP2796667A1 (fr) * 2013-04-24 2014-10-29 MTU Aero Engines GmbH Bague d'étanchéité glissante
US10018051B2 (en) 2013-09-25 2018-07-10 Siemens Aktiengesellschaft Gas turbine and mounting method
US10047626B2 (en) 2013-08-09 2018-08-14 Siemens Aktiengesellschaft Gas turbine and mounting method
US20190106996A1 (en) * 2014-08-13 2019-04-11 United Technologies Corporation Gas turbine engine blade containment system
US10494940B2 (en) * 2016-04-05 2019-12-03 MTU Aero Engines AG Seal segment assembly including mating connection for a turbomachine
CN116557080A (zh) * 2023-06-19 2023-08-08 东方电气集团东方汽轮机有限公司 一种汽轮机动叶片自带冠阻尼片结构及拆装方法

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2210673C2 (ru) * 2001-06-13 2003-08-20 Открытое акционерное общество "Ленинградский Металлический завод" Надбандажное уплотнение паровой турбины
RU2261994C1 (ru) * 2004-03-18 2005-10-10 Брянский государственный технический университет Способ регулирования демпфирующей силы в сотовом уплотнении для ротора турбомашин
RU2287063C1 (ru) * 2005-04-12 2006-11-10 Александр Федорович Ивах Лабиринтное уплотнение для паровой турбины
DE102019110671A1 (de) * 2019-04-25 2020-10-29 Man Energy Solutions Se Turbolader
CN110284929B (zh) * 2019-07-19 2021-10-22 中国航发沈阳发动机研究所 一种涡轮机匣封严结构

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA611004A (en) * 1960-12-20 S. Broffitt Wilgus Turbine nozzle
US2994472A (en) * 1958-12-29 1961-08-01 Gen Electric Tip clearance control system for turbomachines
US3056583A (en) * 1960-11-10 1962-10-02 Gen Electric Retaining means for turbine shrouds and nozzle diaphragms of turbine engines
US3126149A (en) * 1964-03-24 Foamed aluminum honeycomb motor
US3227418A (en) * 1963-11-04 1966-01-04 Gen Electric Variable clearance 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
US3314648A (en) * 1961-12-19 1967-04-18 Gen Electric Stator vane assembly

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA611004A (en) * 1960-12-20 S. Broffitt Wilgus Turbine nozzle
US3126149A (en) * 1964-03-24 Foamed aluminum honeycomb motor
US2994472A (en) * 1958-12-29 1961-08-01 Gen Electric Tip clearance control system for turbomachines
US3056583A (en) * 1960-11-10 1962-10-02 Gen Electric Retaining means for turbine shrouds and nozzle diaphragms of turbine engines
GB1020900A (en) * 1961-11-28 1966-02-23 Licentia Gmbh A seal between the rotor blades and the casing of axial-flow turbo-machines
US3314648A (en) * 1961-12-19 1967-04-18 Gen Electric Stator vane assembly
US3227418A (en) * 1963-11-04 1966-01-04 Gen Electric Variable clearance seal

Cited By (39)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3756741A (en) * 1971-12-17 1973-09-04 Jacuzzi Bros Inc Jet propulsion pump assembly
US3981609A (en) * 1975-06-02 1976-09-21 United Technologies Corporation Coolable blade tip shroud
US4101242A (en) * 1975-06-20 1978-07-18 Rolls-Royce Limited Matching thermal expansion of components of turbo-machines
US4222706A (en) * 1977-08-26 1980-09-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Porous abradable shroud with transverse partitions
US4346904A (en) * 1980-11-26 1982-08-31 Watkins Jr Shelton Honeycomb structure for use in abradable seals
US4553901A (en) * 1983-12-21 1985-11-19 United Technologies Corporation Stator structure for a gas turbine engine
US4643638A (en) * 1983-12-21 1987-02-17 United Technologies Corporation Stator structure for supporting an outer air seal in a gas turbine engine
US4687412A (en) * 1985-07-03 1987-08-18 Pratt & Whitney Canada Inc. Impeller shroud
US5044881A (en) * 1988-12-22 1991-09-03 Rolls-Royce Plc Turbomachine clearance control
US5001483A (en) * 1989-10-23 1991-03-19 Westinghouse Electric Corp. Digital to analog converter for an acoustic charge transport device
US5165848A (en) * 1991-07-09 1992-11-24 General Electric Company Vane liner with axially positioned heat shields
US5174714A (en) * 1991-07-09 1992-12-29 General Electric Company Heat shield mechanism for turbine engines
US5176495A (en) * 1991-07-09 1993-01-05 General Electric Company Thermal shielding apparatus or radiositor for a gas turbine engine
US5195868A (en) * 1991-07-09 1993-03-23 General Electric Company Heat shield for a compressor/stator structure
US5238365A (en) * 1991-07-09 1993-08-24 General Electric Company Assembly for thermal shielding of low pressure turbine
WO1994008143A1 (fr) * 1992-10-07 1994-04-14 University Of Alabama At Birmingham Joint d'etancheite pour degagement d'entree
US5524846A (en) * 1993-12-21 1996-06-11 The Boeing Company Fire protection system for airplanes
US6382905B1 (en) * 2000-04-28 2002-05-07 General Electric Company Fan casing liner support
GB2382380A (en) * 2001-11-24 2003-05-28 Rolls Royce Plc A removable abradable lining for the casing assembly of a gas turbine engine
US6682298B2 (en) 2002-05-17 2004-01-27 David George Demontmorency Rotating shaft confinement system
US20050089390A1 (en) * 2003-08-18 2005-04-28 Snecma Moteurs Abradable device on the blower casing of a gas turbine engine
US20050200080A1 (en) * 2004-03-10 2005-09-15 Siemens Westinghouse Power Corporation Seal for a turbine engine
US20070065277A1 (en) * 2005-09-19 2007-03-22 Ingersoll-Rand Company Centrifugal compressor including a seal system
US20070063449A1 (en) * 2005-09-19 2007-03-22 Ingersoll-Rand Company Stationary seal ring for a centrifugal compressor
US20070065276A1 (en) * 2005-09-19 2007-03-22 Ingersoll-Rand Company Impeller for a centrifugal compressor
US20080063508A1 (en) * 2006-09-08 2008-03-13 Barry Barnett Fan case abradable
US8998565B2 (en) * 2011-04-18 2015-04-07 General Electric Company Apparatus to seal with a turbine blade stage in a gas turbine
US20120260670A1 (en) * 2011-04-18 2012-10-18 General Electric Company Apparatus to seal with a turbine blade stage in a gas turbine
EP2719869A1 (fr) * 2012-10-12 2014-04-16 MTU Aero Engines GmbH Étanchéification axiale dans une structure de boîtier pour une turbomachine
US9605551B2 (en) 2012-10-12 2017-03-28 MTU Aero Engines AG Axial seal in a casing structure for a fluid flow machine
US20140321969A1 (en) * 2013-04-24 2014-10-30 MTU Aero Engines AG Slide ring seal
EP2796667A1 (fr) * 2013-04-24 2014-10-29 MTU Aero Engines GmbH Bague d'étanchéité glissante
US9835039B2 (en) * 2013-04-24 2017-12-05 MTU Aero Engines AG Slide ring seal
US10047626B2 (en) 2013-08-09 2018-08-14 Siemens Aktiengesellschaft Gas turbine and mounting method
US10018051B2 (en) 2013-09-25 2018-07-10 Siemens Aktiengesellschaft Gas turbine and mounting method
US20190106996A1 (en) * 2014-08-13 2019-04-11 United Technologies Corporation Gas turbine engine blade containment system
US10927687B2 (en) * 2014-08-13 2021-02-23 Raytheon Technologies Corporation Gas turbine engine blade containment system
US10494940B2 (en) * 2016-04-05 2019-12-03 MTU Aero Engines AG Seal segment assembly including mating connection for a turbomachine
CN116557080A (zh) * 2023-06-19 2023-08-08 东方电气集团东方汽轮机有限公司 一种汽轮机动叶片自带冠阻尼片结构及拆装方法

Also Published As

Publication number Publication date
JPS5020201B1 (fr) 1975-07-12
FR2103007A5 (fr) 1972-04-07
GB1306575A (en) 1973-02-14
CH541066A (fr) 1973-08-31
NL7109117A (fr) 1972-01-04
BE769254A (fr) 1971-12-29
DE2131855A1 (de) 1972-01-05

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