US3880435A - Sealing ring for turbo machines - Google Patents

Sealing ring for turbo machines Download PDF

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Publication number
US3880435A
US3880435A US426311A US42631173A US3880435A US 3880435 A US3880435 A US 3880435A US 426311 A US426311 A US 426311A US 42631173 A US42631173 A US 42631173A US 3880435 A US3880435 A US 3880435A
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US
United States
Prior art keywords
sectors
sheet
strip
sealing ring
sealing
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
US426311A
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English (en)
Inventor
Per Gosta Thornbald
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.)
ABB Stal AB
Original Assignee
Stal Laval Turbin AB
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Filing date
Publication date
Application filed by Stal Laval Turbin AB filed Critical Stal Laval Turbin AB
Application granted granted Critical
Publication of US3880435A publication Critical patent/US3880435A/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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/44—Free-space packings
    • F16J15/445—Free-space packings with means for adjusting the clearance
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S277/00—Seal for a joint or juncture
    • Y10S277/93—Seal including heating or cooling feature

Definitions

  • the present invention is directed toward a novel improved construction of the aforementioned sealing and screening elements, and provides a sealing device in the form of ring segments, or blocks", arranged around the stator housing with small peripheral gaps for expansion between segments.
  • Each sealing block comprises a stack of flat sheet metal layers mounted on a corrugated metal strip, which in turn is supported on a smooth metal strip facing the turbine rotor. Suitable cooling air passages are provided within this assembly to counteract the heat from the turbine gas.
  • the novel construction incorporated into these block segments supplies flexibility and at the same time satisfactory cooling of both the sealing ring and the surrounding stator parts.
  • FIG. I is a sectional view through part of a turbo machine utilizing a sealing ring constructed in accordance with this invention.
  • FIG. 2 is an enlarged, more detailed view of the sealing ring block and its mounting shown in FIG. I;
  • FIG. 3 is a developed view of a sealing ring block seen in axial direction, and with successive layers removed to show the inner construction
  • FIG. 4 is a view of the sealing ring block of FIG. 3 as seen in radial direction from the outside;
  • FIG. 5 is a view similar to FIG. 3 but showing an alternate embodiment of the sealing ring structure of this invention.
  • FIG. 1 part of turbine rotor disc I0 is shown with a vane ll projecting radially therefrom.
  • Guide vane 12 is secured at its head 13 to a flange 14 in stator housing 15.
  • Turbine disc 10 is circumferentially encompassed by the sealing ring 16 of this invention, to ensure that a minimum of gas or steam leaks between rotor disc 10 and stator housing I5, and therefore to maintain a gap 17 between vanes 11 and sealing ring 16 as small as possible consistent with avoiding any contact or catching of vanes II by sealing ring 16.
  • sealing ring 16 is constructed of arcuate stacks of sheet metal plates with provisions for cooling, as will be more fully described hereinafter.
  • Attachment ring I8 secured to head 13 of guide vane 12, maintains sealing ring 16 in position, as shown in fuller detail in FIG. 2.
  • Attachment ring 18 has flanges l9 and 20 which, in combination with rivets 21, hold together the stacks of sheet metal plates 3, 4 and 5 of sealing ring I6.
  • Each stack of plates forms a block or segment; a plurality of these blocks, arranged circumferentially between flanges 19 and 20 of attachment ring 18 and held in place by rivets 21, together form sealing ring 16 and are spaced from each other with a slight gap to permit peripheral expansion.
  • the block segments of sealing ring 16 are cooled by air which is forced inwardly through a cooling channel 22 formed in attachment ring 18 and is then distributed over and through each block.
  • FIGS. 3 and 4 clearly illustrate the construction of block segments which form sealing ring 16.
  • FIG. 3 is shown as a developed straight view, but in reality each block segment is arcu ately curved so that it forms one sector of ring I6.
  • the main body of each sealing block comprises a bundle of parallel flat sheet metal plates oriented perpendicularly to the turbine shaft, the outermost layer on each side of the bundle being a series of substantially rectangular cover plates 5. Between the two cover layers 5, alternate layers of differing plates 3 and 4 (to be described below) are sandwiched to complete the bundle or stack.
  • the radially innermost end of each sealing block of ring 16, adjacent to rotor 10 is faced with a smooth metal strip 1, on which a sinuously corrugated metal strip 2 is superposed. Strips l and 2 are attached to each other along their lines of contact by such conventional means as, for example, point welding.
  • Plates 3 and 4 are shaped at their inner edges to follow generally the curvature of corrugated strip 2.
  • outer cover plates 5 are substantially rectangular and extend the entire height of the block.
  • Behind the cover layer 5 is a layer of plates 3, each shaped with a peak extending into and secured to one of the radially inward depressions of corrugated strip 2, preferably by point welding. Except for these secured peaks. the inner edges of plates 3 are spaced from corrugated strip 2, providing cooling gaps 6 therebetween.
  • next successive layer of plates 4 are shaped to contact and be secured in the same manner to the radially outward peaks of corrugated strip 2, while the remaining inner edge surfaces of plates 4 are spaced from strip 2, thus also forming cooling gaps 6.
  • the interruption of cooling gaps 6 by welded contact points forces cooling air on its way along corrugated strip 2 to cross over constantly between the metal layers 3 and 4, ensuring efficient cooling of strip 2 and the inner portions of plates 3 and 4.
  • the cooling air emerges from cooling gap 6 into space 7 between adjacent sealing blocks.
  • plates 3 are omitted from their layers in the area of air introduction channel 22, so that a transverse connection between distribution channels 8 is created. as well as openings 9 down through the sealing block for direct communication with cooling gaps 6 along corrugated strip 2.
  • a groove 23 in attachment ring 18 may be provided in order to assist in the distribution of air from channel 22 to the sealing block segmeat.
  • each sealing block segment is in reality arcuate, constituting a sector of sealing ring 16.
  • plates 3 and 4 may be shaped with nonparallel converging side edges so that they automati cally form a ring sector when the plates for each layer are fitted together.
  • it is possible to make all the plates with parallel edges so that narrow wedgeshaped spaces formed between the plates in any layer will permit cooling air to pass from distribution channels 8 toward cooling gaps 6. The latter arrangement makes it possible to use the same plates for sealing rings of different diameters.
  • Each block segment of sealing ring 18 is formed by providing the sheet layer 3, 4 and 5 with holes to accept rivets 21, and its shape when mounted is determined by the curvature of flanges 19 and 20 of attachment ring 18.
  • each block segment is defined by the height of plates 3. Since plates 3, attachment ring 18 and stator housing 15 are all cooled to a certain known temperature, only the temperature expansion of rotor 10 need be considered when determining the size of gap 17 between vanes I1 and sealing ring 16.
  • FIG. 5 illustrates an alternate embodiment of a sealing block segment. in which plates 4' correspond to plates 4 but have full height.
  • the sealing block segment stretches peripherally due to the expansion of strip 1, it shrinks radially. since, as corrugated strip 2 is stretched and straightened. high plate layers 4' are pulled down between low plate layers 3'.
  • this feature can be exploited to predetermine the width of gap 17 between stator sealing l6 and rotor vane II, and thus to maintain gap 17 at a constant minimum value with varying temperature and load in the turbo machine.
  • the cooling of the block segments of sealing ring 16 is preferably accomplished by providing compressed air to channel 22, whereas for steam turbines, cool steam of suitable pressure may be employed.
  • Sealing ring for a turbo machine for limiting and defining the radial clearance between the outer edges of the vanes of a turbine rotor disc and the corresponding stator housing, the sealing ring being composed of a plurality of sealing block segments which are mounted circumferentially on the stator housing, spaced from each other by peripheral gaps, cooled by air flowing through them, and which comprise:
  • Sealing ring according to claim 1. further comprising:
  • a pair of sheet layers for each sealing block segment each divided into sectors. positioned as a cover layer on either side of said sheet stack and extending radially outwardly from said smooth metallic strip to the outer periphery of the sealing block, thereby sealing the block and said cooling channel on both sides.
  • Sealing rings according to claim 1 wherein cooling air is supplied to each sealing block segment through an air introduction channel in the stator. and wherein said sectors of the layers of said sheet stack in an axial zone adjacent to said air introduction channel are formed with reduced radial height, to distribute cooling air over each sealing block.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)
US426311A 1973-01-05 1973-12-19 Sealing ring for turbo machines Expired - Lifetime US3880435A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SE7300158A SE369539B (ja) 1973-01-05 1973-01-05

Publications (1)

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US3880435A true US3880435A (en) 1975-04-29

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US426311A Expired - Lifetime US3880435A (en) 1973-01-05 1973-12-19 Sealing ring for turbo machines

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SE (1) SE369539B (ja)

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2468741A1 (fr) * 1979-10-26 1981-05-08 Snecma Perfectionnements aux anneaux a joint d'etancheite refroidi par l'air pour roues de turbine a gaz
US4460311A (en) * 1980-05-24 1984-07-17 MTU Motogren-Und Turbinen-Union Apparatus for minimizing and maintaining constant the blade tip clearance of axial-flow turbines in gas turbine engines
US4652209A (en) * 1985-09-13 1987-03-24 Rockwell International Corporation Knurled turbine tip seal
US4767267A (en) * 1986-12-03 1988-08-30 General Electric Company Seal assembly
US5031922A (en) * 1989-12-21 1991-07-16 Allied-Signal Inc. Bidirectional finger seal
US5042823A (en) * 1989-12-21 1991-08-27 Allied-Signal Inc. Laminated finger seal
US5071138A (en) * 1989-12-21 1991-12-10 Allied-Signal Inc. Laminated finger seal
US5108116A (en) * 1991-05-31 1992-04-28 Allied-Signal Inc. Laminated finger seal with logarithmic curvature
US6224329B1 (en) 1999-01-07 2001-05-01 Siemens Westinghouse Power Corporation Method of cooling a combustion turbine
US20090081033A1 (en) * 2007-09-21 2009-03-26 Siemens Power Generation, Inc. Stacked Lamellae Ceramic Gas Turbine Ring Segment Component
US20090087307A1 (en) * 2007-09-28 2009-04-02 Honeywell International, Inc. Reduced pressure load finger seal assembly
CN102213112A (zh) * 2010-04-09 2011-10-12 通用电气公司 用于涡轮围带的轴向定向的单元密封结构和相关方法
EP2336497A3 (en) * 2009-12-17 2014-03-05 United Technologies Corporation Blade outer air seal formed of stacked panels
US20150118040A1 (en) * 2013-10-25 2015-04-30 Ching-Pang Lee Outer vane support ring including a strong back plate in a compressor section of a gas turbine engine
US20170051834A1 (en) * 2015-08-18 2017-02-23 Rolls-Royce Plc Sealing arrangements
US10519806B2 (en) * 2015-11-06 2019-12-31 Calsonic Kansei Corporation Turbine housing
US10570779B2 (en) * 2015-03-23 2020-02-25 Calsonic Kansei Corporation Turbine housing
US11713694B1 (en) 2022-11-30 2023-08-01 Rolls-Royce Corporation Ceramic matrix composite blade track segment with two-piece carrier
US11732604B1 (en) 2022-12-01 2023-08-22 Rolls-Royce Corporation Ceramic matrix composite blade track segment with integrated cooling passages
US11773751B1 (en) 2022-11-29 2023-10-03 Rolls-Royce Corporation Ceramic matrix composite blade track segment with pin-locating threaded insert
US11840936B1 (en) 2022-11-30 2023-12-12 Rolls-Royce Corporation Ceramic matrix composite blade track segment with pin-locating shim kit
US11885225B1 (en) 2023-01-25 2024-01-30 Rolls-Royce Corporation Turbine blade track with ceramic matrix composite segments having attachment flange draft angles
US12031443B2 (en) 2022-11-29 2024-07-09 Rolls-Royce Corporation Ceramic matrix composite blade track segment with attachment flange cooling chambers

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2963268A (en) * 1957-03-25 1960-12-06 Gen Electric Pressurized seal
US3046648A (en) * 1959-04-13 1962-07-31 Aircraft Prec Products Inc Method of manufacturing replaceable labyrinth type seal assembly
US3082010A (en) * 1958-01-20 1963-03-19 Rolls Royce Labyrinth seals
US3583824A (en) * 1969-10-02 1971-06-08 Gen Electric Temperature controlled shroud and shroud support
US3603599A (en) * 1970-05-06 1971-09-07 Gen Motors Corp Cooled seal
US3719365A (en) * 1971-10-18 1973-03-06 Gen Motors Corp Seal structure
US3720419A (en) * 1971-01-21 1973-03-13 Westinghouse Electric Corp Fabricated labyrinth seal structure
US3728039A (en) * 1966-11-02 1973-04-17 Gen Electric Fluid cooled porous stator structure

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2963268A (en) * 1957-03-25 1960-12-06 Gen Electric Pressurized seal
US3082010A (en) * 1958-01-20 1963-03-19 Rolls Royce Labyrinth seals
US3046648A (en) * 1959-04-13 1962-07-31 Aircraft Prec Products Inc Method of manufacturing replaceable labyrinth type seal assembly
US3728039A (en) * 1966-11-02 1973-04-17 Gen Electric Fluid cooled porous stator structure
US3583824A (en) * 1969-10-02 1971-06-08 Gen Electric Temperature controlled shroud and shroud support
US3603599A (en) * 1970-05-06 1971-09-07 Gen Motors Corp Cooled seal
US3720419A (en) * 1971-01-21 1973-03-13 Westinghouse Electric Corp Fabricated labyrinth seal structure
US3719365A (en) * 1971-10-18 1973-03-06 Gen Motors Corp Seal structure

Cited By (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2468741A1 (fr) * 1979-10-26 1981-05-08 Snecma Perfectionnements aux anneaux a joint d'etancheite refroidi par l'air pour roues de turbine a gaz
EP0028554A1 (fr) * 1979-10-26 1981-05-13 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Anneaux à joint d'étanchéité refroidi et turbine à gaz équipée d'un tel anneau
US4392656A (en) * 1979-10-26 1983-07-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Air-cooled sealing rings for the wheels of gas turbines
US4460311A (en) * 1980-05-24 1984-07-17 MTU Motogren-Und Turbinen-Union Apparatus for minimizing and maintaining constant the blade tip clearance of axial-flow turbines in gas turbine engines
US4652209A (en) * 1985-09-13 1987-03-24 Rockwell International Corporation Knurled turbine tip seal
US4767267A (en) * 1986-12-03 1988-08-30 General Electric Company Seal assembly
US5031922A (en) * 1989-12-21 1991-07-16 Allied-Signal Inc. Bidirectional finger seal
US5042823A (en) * 1989-12-21 1991-08-27 Allied-Signal Inc. Laminated finger seal
US5071138A (en) * 1989-12-21 1991-12-10 Allied-Signal Inc. Laminated finger seal
US5108116A (en) * 1991-05-31 1992-04-28 Allied-Signal Inc. Laminated finger seal with logarithmic curvature
US6224329B1 (en) 1999-01-07 2001-05-01 Siemens Westinghouse Power Corporation Method of cooling a combustion turbine
US20090081033A1 (en) * 2007-09-21 2009-03-26 Siemens Power Generation, Inc. Stacked Lamellae Ceramic Gas Turbine Ring Segment Component
US8128350B2 (en) * 2007-09-21 2012-03-06 Siemens Energy, Inc. Stacked lamellae ceramic gas turbine ring segment component
US20090087307A1 (en) * 2007-09-28 2009-04-02 Honeywell International, Inc. Reduced pressure load finger seal assembly
EP2336497A3 (en) * 2009-12-17 2014-03-05 United Technologies Corporation Blade outer air seal formed of stacked panels
US20110248452A1 (en) * 2010-04-09 2011-10-13 General Electric Company Axially-oriented cellular seal structure for turbine shrouds and related method
CN102213112A (zh) * 2010-04-09 2011-10-12 通用电气公司 用于涡轮围带的轴向定向的单元密封结构和相关方法
EP2375003A3 (en) * 2010-04-09 2014-06-11 General Electric Company Axially-oriented cellular seal structure for turbine shrouds
CN102213112B (zh) * 2010-04-09 2016-01-20 通用电气公司 在支承于机器转子上的动叶排与周围固定壳体之间的密封系统
US8444371B2 (en) * 2010-04-09 2013-05-21 General Electric Company Axially-oriented cellular seal structure for turbine shrouds and related method
US20150118040A1 (en) * 2013-10-25 2015-04-30 Ching-Pang Lee Outer vane support ring including a strong back plate in a compressor section of a gas turbine engine
US9206700B2 (en) * 2013-10-25 2015-12-08 Siemens Aktiengesellschaft Outer vane support ring including a strong back plate in a compressor section of a gas turbine engine
US10570779B2 (en) * 2015-03-23 2020-02-25 Calsonic Kansei Corporation Turbine housing
US20170051834A1 (en) * 2015-08-18 2017-02-23 Rolls-Royce Plc Sealing arrangements
US10519806B2 (en) * 2015-11-06 2019-12-31 Calsonic Kansei Corporation Turbine housing
US11773751B1 (en) 2022-11-29 2023-10-03 Rolls-Royce Corporation Ceramic matrix composite blade track segment with pin-locating threaded insert
US12031443B2 (en) 2022-11-29 2024-07-09 Rolls-Royce Corporation Ceramic matrix composite blade track segment with attachment flange cooling chambers
US11713694B1 (en) 2022-11-30 2023-08-01 Rolls-Royce Corporation Ceramic matrix composite blade track segment with two-piece carrier
US11840936B1 (en) 2022-11-30 2023-12-12 Rolls-Royce Corporation Ceramic matrix composite blade track segment with pin-locating shim kit
US11732604B1 (en) 2022-12-01 2023-08-22 Rolls-Royce Corporation Ceramic matrix composite blade track segment with integrated cooling passages
US11885225B1 (en) 2023-01-25 2024-01-30 Rolls-Royce Corporation Turbine blade track with ceramic matrix composite segments having attachment flange draft angles

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Publication number Publication date
SE369539B (ja) 1974-09-02

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