US3746462A - Stage seals for a turbine - Google Patents

Stage seals for a turbine Download PDF

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Publication number
US3746462A
US3746462A US00157900A US3746462DA US3746462A US 3746462 A US3746462 A US 3746462A US 00157900 A US00157900 A US 00157900A US 3746462D A US3746462D A US 3746462DA US 3746462 A US3746462 A US 3746462A
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US
United States
Prior art keywords
blades
rotor
turbine
stationary
casing
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
US00157900A
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English (en)
Inventor
S Fukuda
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.)
Mitsubishi Heavy Industries Ltd
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Mitsubishi Heavy Industries Ltd
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Filing date
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Application filed by Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
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Publication of US3746462A publication Critical patent/US3746462A/en
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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
    • F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
    • 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
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Definitions

  • ABSTRACT A plurality of ducts disposed in a stationary blade ring diaphragm of a steam turbine, the ducts have inlets disposed upstream of the last downstream fin of a labyrinth seal formed between the diaphragm and a rotor.
  • the ducts extend through a plurality of stationary blades disposed in the diaphragm, and have outlets on the downstream side of the diaphragm adjacent a casing, for reducing the total quantity of steam bypassing the stationary and rotating blades forming one stage of the turbine by directing steam, which passes through the labyrinth seal adjacent the rotor, to an area upstream of a labyrinth seal associated with a shroud ring encircling the rotatable blades of this stage of the turbine.
  • Labyrinth seals have been used to provide a seal between rotating parts of a turbine for decades; however, they do passa small amount of fluid.
  • a turbine operable by a motive fluid flowing therethrough when made in accordance with this invention, has an annular array of circumferentially spaced stationary blades disposed upstream of an annular array of circumferentially spaced rotatableblades, a rotor upon which the rotatable blades are mounted, and a casing encircling the blades and rotor.
  • the annular array of stationary blades comprises at least one duct extending from. a circumferential surface adjacent the rotor, through at least one stationary blade, and then to the downstream side of the stationary blades adjacent the casing.
  • the duct is also disposed as to allow a small portion of the motive sfluid flowing through a space between the circumferential surface and the rotor, to flow intothe duct, and throughthe duct to the downstream side of the stationaryblades adjacent the casing, and then to flow between the array of rotating blades and the casing, to reduce the total amount of motive fluid bypassing the blades and not doing useful work, thereby increasing the. efficiency of the turbine.
  • FIG. 1 is a longitudinal partial sectional view of an impulse stage of a steam turbine
  • FIG. 2 is a partial sectional view taken on line 1111 of FIG. 1;
  • FIG. 3 is a longitudinal partial sectional view of a reaction stage of a steam turbine.
  • FIGS. 1 and 3 each shows a longitudinal sectional view of one stage of a steam turbine 1 having a rotor 3,.andan annular array of circumferentially spaced rotatable blades 5 mounted on the rotor 3and an annulararray of circumferentially spaced stationary nozzle blades 7 mounted in a ring diaphragm 9 encircling the rotor 3.
  • the ring diaphragm-9 is formed from two semicircular arcuate segments each having .an :inner and outer ring 13 and 15, respectively.
  • the outerwring fits into a circumferential groove 16 disposed in a casing 17 encircling the rotor and blades 5 and 7.
  • a labyrinth seal 19 :18 disposed on the inner peripheral surface of the inner ring 13 ofthediaphragm 9 and as shown in FIGS. [and 3 comprises a gland ring 21 and a-fin 22 fastened directlyto .the diaphragm 9.
  • gland "ring 21 is a segmented circular ring whichfits into a T-shaped circumferential :groove 23 .in the diaphragm ring '9 and contains a plurality 90f fins .25 extending radially inwardlyfrom the sinner pierpheralasun face thereof.
  • the fins 25 are 'thin strips rolled the :hard
  • the rotor has a plurality of circumferential grooves27 and rings 29 which register with the fins 25 to provide a tortuous path for the steam, thus reducing the amount of steam passing between the ring diaphragm 9 and the rotor 3.
  • Springs bias the gland ring inwardly, so that if struck by the rotor 3 the gland ring will move outwardly to minimize damage to the labyrinth fins 25 and the rotor 3.
  • the rotable blades 5 are fastened to a disk wheel 31 extending radially outwardly from the rotor 3.
  • a shroud ring 33 encircles the tips of the rotating blades providing a generally continuous ring enclosing the rotatable blades.
  • Labyrinth stripsor fins 35 extend radially inwardly from the casing 17 and provide a labyrinth seal adjacent the casing 17 for the rotating blades.
  • a duct 37 has an outlet 39 adjacent the rotor and immediately upstream of the last downstream fin 22, which is fastened directly to the diaphragm ring 9.
  • the duct 37 extends through the inner ring 13 and the stationary, blade 7, and has an outlet41 on the downstream side of the outer ring 15 and of the diaphragm ring 9, adjacent. the casing 17.
  • T o optimize the efiiciency the flow through the duct 37 should substantially equal the flow through the labyrinth seal adjacent the casing 17.
  • the pressuredrop across the stationary blades 7 be greater than the pressure drop across the rotating blades 5, as the diameters .of the two seals differ by a large amount, so that the open area in the labyrinth seal associated with the rotatingblades is much greater than the open area of the labyrinth seal 19 associated with the stationary blades, and the flow through labtrinth seals is proportional to the open area and the differential pressure across the seals. Therefore, to equalize the flow, the seal :having the smallest openarea must have the largest pressure drop. This problem is compounded, as generally large diameters require greater running clearances, thus increasing the difference in the openareas atagreater rate than the variation in diameters.
  • the pressure drop across the stationary blades is normally very large, and there is a very low pressure drop across the rotating blades,while in reaction stages, as shown in FIG.I3,the pressure drop across thelstationary blades may be as :high or higherthan the pressure drop across the rotating blades. Therefore, to optimize the effi- .ciency of theturbine, it would be desirable to use reaction stages in which the pressure: drop across the stationary'blades 7 is-greaterthan the pressure drop across the rotating blades .5.
  • FIG..2 showsthatnotall of the stationary blades have :aduct 37 extending therethrough. 1n the preferred embodiment .a plurality of ducts would .be provided in each stage, 'the :exact number .being determined by the cross sectional area of each duct 37, and the available differential pressure between areas adjacent the inlets 39 and outlets 41 of the ducts 37.
  • a steam turbine having an annular array of circumferentially spaced stationary blades disposed upstream of an annular array of circumferentially spaced rotatable blades and said stationary blades having an inner shroud ring, a rotor upon which said rotatable blades are mounted, a casing encircling said blades and rotor, and a labyrinth seal between said shroud ring and said rotor having a plurality of circumferential axially spaced fins encircling the rotor, said annular array of stationary blades having at least one duct extending from a space immediately upstream of the last downstream fin forming the labyrinth seal, radially through at least one stationary blade, and then to a downstream side of said stationary blades adjacent said casing, said duct being disposed to allow a small portion of the steam which flows through said labyrinth seal to flow into said duct, and through said duct to said downstream side of said stationary blades adjacent said casing, and then to to

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US00157900A 1970-07-11 1971-06-29 Stage seals for a turbine Expired - Lifetime US3746462A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP45060314A JPS501646B1 (ja) 1970-07-11 1970-07-11

Publications (1)

Publication Number Publication Date
US3746462A true US3746462A (en) 1973-07-17

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ID=13138572

Family Applications (1)

Application Number Title Priority Date Filing Date
US00157900A Expired - Lifetime US3746462A (en) 1970-07-11 1971-06-29 Stage seals for a turbine

Country Status (7)

Country Link
US (1) US3746462A (ja)
JP (1) JPS501646B1 (ja)
CA (1) CA949997A (ja)
CH (1) CH529913A (ja)
DE (1) DE2134514C3 (ja)
FR (1) FR2100469A5 (ja)
GB (1) GB1342663A (ja)

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3897169A (en) * 1973-04-19 1975-07-29 Gen Electric Leakage control structure
JPS50128008A (ja) * 1974-03-21 1975-10-08
US3989410A (en) * 1974-11-27 1976-11-02 General Electric Company Labyrinth seal system
US4370094A (en) * 1974-03-21 1983-01-25 Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft Method of and device for avoiding rotor instability to enhance dynamic power limit of turbines and compressors
US4702670A (en) * 1985-02-12 1987-10-27 Rolls-Royce Gas turbine engines
US4815931A (en) * 1982-05-11 1989-03-28 Aktiengesellschaft Kuehnle, Kopp & Kausch Overhung radial-flow steam turbine wheel with toothed and bolted shaft connection
US4877373A (en) * 1988-02-08 1989-10-31 Dresser-Rand Company Vaned diffuser with small straightening vanes
GB2253442A (en) * 1991-03-02 1992-09-09 Rolls Royce Plc Multi-stage seal for an axial flow turbine
US5232338A (en) * 1990-09-13 1993-08-03 Gec Alsthom Sa Blade array for turbomachines comprising suction ports in the inner and/or outer wall and turbomachines comprising same
AU653805B2 (en) * 1991-04-19 1994-10-13 Gec Alsthom Sa An impulse turbine with a drum rotor, and improvements to such turbines
US5676521A (en) * 1996-07-22 1997-10-14 Haynes; Christopher J. Steam turbine with superheat retaining extraction
US20060237914A1 (en) * 2003-06-20 2006-10-26 Elliott Company Swirl-reversal abradable labyrinth seal
US20070224037A1 (en) * 2002-01-28 2007-09-27 Kabushiki Kaisha Toshiba Geothermal turbine
US20100196143A1 (en) * 2009-01-30 2010-08-05 Rolls-Royce Plc Axial compressor
US20100254802A1 (en) * 2009-04-01 2010-10-07 Rolls-Royce Plc Rotor arrangement
US20110058933A1 (en) * 2008-02-28 2011-03-10 Mtu Aero Engines Gmbh Device and method for redirecting a leakage current
US20110097198A1 (en) * 2009-10-27 2011-04-28 General Electric Company Turbo machine efficiency equalizer system
US20120247125A1 (en) * 2009-12-07 2012-10-04 Mitsubishi Heavy Industries, Ltd. Communicating structure between combustor and turbine portion and gas turbine
US20120321449A1 (en) * 2010-02-25 2012-12-20 Mitsubishi Heavy Industries, Ltd. Turbine
CN103097668A (zh) * 2010-10-29 2013-05-08 三菱重工业株式会社 涡轮机及涡轮机的制造方法
US20140154066A1 (en) * 2012-12-04 2014-06-05 General Electric Company Turbomachine nozzle having fluid conduit and related turbomachine
US20140205444A1 (en) * 2013-01-21 2014-07-24 General Electric Company Turbomachine having swirl-inhibiting seal
US9032733B2 (en) 2013-04-04 2015-05-19 General Electric Company Turbomachine system with direct header steam injection, related control system and program product
US9091170B2 (en) 2008-12-24 2015-07-28 Mitsubishi Hitachi Power Systems, Ltd. One-stage stator vane cooling structure and gas turbine
US11028695B2 (en) 2017-01-20 2021-06-08 Mitsubishi Power, Ltd. Steam turbine
US11092028B2 (en) * 2017-02-02 2021-08-17 General Electric Company Tip balance slits for turbines
US11215073B2 (en) * 2018-04-24 2022-01-04 MTU Aero Engines AG Stator vane for a turbine of a turbomachine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5311202A (en) * 1976-07-19 1978-02-01 Hitachi Ltd Steam turbine step-setting structure

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US935286A (en) * 1904-09-27 1909-09-28 Westinghouse Machine Co Elastic-fluid turbine.
US2332322A (en) * 1940-11-16 1943-10-19 Gen Electric Elastic fluid turbine arrangement
US2848155A (en) * 1950-11-22 1958-08-19 United Aircraft Corp Boundary layer control apparatus for compressors
GB1013835A (en) * 1961-11-02 1965-12-22 Licentia Gmbh Improvements in or relating to axial-flow turbines, compressors and exhausters

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US935286A (en) * 1904-09-27 1909-09-28 Westinghouse Machine Co Elastic-fluid turbine.
US2332322A (en) * 1940-11-16 1943-10-19 Gen Electric Elastic fluid turbine arrangement
US2848155A (en) * 1950-11-22 1958-08-19 United Aircraft Corp Boundary layer control apparatus for compressors
GB1013835A (en) * 1961-11-02 1965-12-22 Licentia Gmbh Improvements in or relating to axial-flow turbines, compressors and exhausters

Cited By (42)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3897169A (en) * 1973-04-19 1975-07-29 Gen Electric Leakage control structure
JPS50128008A (ja) * 1974-03-21 1975-10-08
US4370094A (en) * 1974-03-21 1983-01-25 Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft Method of and device for avoiding rotor instability to enhance dynamic power limit of turbines and compressors
JPS5949401B2 (ja) * 1974-03-21 1984-12-03 マシ−ネンフアブリ−ク アウグスブルク ニユルンベルク アクチエンゲゼルシヤフト タ−ビンおよび圧縮機の動的な出力限界を高める方法および装置
US3989410A (en) * 1974-11-27 1976-11-02 General Electric Company Labyrinth seal system
US4815931A (en) * 1982-05-11 1989-03-28 Aktiengesellschaft Kuehnle, Kopp & Kausch Overhung radial-flow steam turbine wheel with toothed and bolted shaft connection
US4702670A (en) * 1985-02-12 1987-10-27 Rolls-Royce Gas turbine engines
US4877373A (en) * 1988-02-08 1989-10-31 Dresser-Rand Company Vaned diffuser with small straightening vanes
US5232338A (en) * 1990-09-13 1993-08-03 Gec Alsthom Sa Blade array for turbomachines comprising suction ports in the inner and/or outer wall and turbomachines comprising same
GB2253442A (en) * 1991-03-02 1992-09-09 Rolls Royce Plc Multi-stage seal for an axial flow turbine
US5205706A (en) * 1991-03-02 1993-04-27 Rolls-Royce Plc Axial flow turbine assembly and a multi-stage seal
GB2253442B (en) * 1991-03-02 1994-08-24 Rolls Royce Plc An axial flow turbine assembly
AU653805B2 (en) * 1991-04-19 1994-10-13 Gec Alsthom Sa An impulse turbine with a drum rotor, and improvements to such turbines
US5676521A (en) * 1996-07-22 1997-10-14 Haynes; Christopher J. Steam turbine with superheat retaining extraction
US20070224037A1 (en) * 2002-01-28 2007-09-27 Kabushiki Kaisha Toshiba Geothermal turbine
US20060237914A1 (en) * 2003-06-20 2006-10-26 Elliott Company Swirl-reversal abradable labyrinth seal
US20110058933A1 (en) * 2008-02-28 2011-03-10 Mtu Aero Engines Gmbh Device and method for redirecting a leakage current
US8753070B2 (en) * 2008-02-28 2014-06-17 Mtu Aero Engines Gmbh Device and method for redirecting a leakage current
US9091170B2 (en) 2008-12-24 2015-07-28 Mitsubishi Hitachi Power Systems, Ltd. One-stage stator vane cooling structure and gas turbine
US20100196143A1 (en) * 2009-01-30 2010-08-05 Rolls-Royce Plc Axial compressor
US8308429B2 (en) * 2009-01-30 2012-11-13 Rolls-Royce, Plc Axial compressor
US8282341B2 (en) * 2009-04-01 2012-10-09 Rolls-Royce Plc Rotor arrangement
US20100254802A1 (en) * 2009-04-01 2010-10-07 Rolls-Royce Plc Rotor arrangement
US20110097198A1 (en) * 2009-10-27 2011-04-28 General Electric Company Turbo machine efficiency equalizer system
US8545170B2 (en) * 2009-10-27 2013-10-01 General Electric Company Turbo machine efficiency equalizer system
US20120247125A1 (en) * 2009-12-07 2012-10-04 Mitsubishi Heavy Industries, Ltd. Communicating structure between combustor and turbine portion and gas turbine
US9395085B2 (en) * 2009-12-07 2016-07-19 Mitsubishi Hitachi Power Systems, Ltd. Communicating structure between adjacent combustors and turbine portion and gas turbine
US20120321449A1 (en) * 2010-02-25 2012-12-20 Mitsubishi Heavy Industries, Ltd. Turbine
US9593587B2 (en) * 2010-02-25 2017-03-14 Mitsubishi Heavy Industries, Ltd. Turbine seal fin leakage flow rate control
CN103097668A (zh) * 2010-10-29 2013-05-08 三菱重工业株式会社 涡轮机及涡轮机的制造方法
CN103097668B (zh) * 2010-10-29 2016-02-10 三菱日立电力系统株式会社 涡轮机及涡轮机的制造方法
US9551224B2 (en) 2010-10-29 2017-01-24 Mitsubishi Hitachi Power Systems, Ltd. Turbine and method for manufacturing turbine
US9394797B2 (en) * 2012-12-04 2016-07-19 General Electric Company Turbomachine nozzle having fluid conduit and related turbomachine
US20140154066A1 (en) * 2012-12-04 2014-06-05 General Electric Company Turbomachine nozzle having fluid conduit and related turbomachine
KR101746256B1 (ko) 2012-12-04 2017-06-12 제너럴 일렉트릭 캄파니 증기 터빈 노즐, 터보머신 다이아프램 및 터보머신
US9394800B2 (en) * 2013-01-21 2016-07-19 General Electric Company Turbomachine having swirl-inhibiting seal
US20140205444A1 (en) * 2013-01-21 2014-07-24 General Electric Company Turbomachine having swirl-inhibiting seal
US9032733B2 (en) 2013-04-04 2015-05-19 General Electric Company Turbomachine system with direct header steam injection, related control system and program product
US11028695B2 (en) 2017-01-20 2021-06-08 Mitsubishi Power, Ltd. Steam turbine
DE112017006877B4 (de) 2017-01-20 2022-12-08 Mitsubishi Heavy Industries, Ltd. Dampfturbine
US11092028B2 (en) * 2017-02-02 2021-08-17 General Electric Company Tip balance slits for turbines
US11215073B2 (en) * 2018-04-24 2022-01-04 MTU Aero Engines AG Stator vane for a turbine of a turbomachine

Also Published As

Publication number Publication date
DE2134514C3 (de) 1973-11-22
GB1342663A (en) 1974-01-03
DE2134514A1 (de) 1972-01-27
FR2100469A5 (ja) 1972-03-17
DE2134514B2 (de) 1973-05-03
CA949997A (en) 1974-06-25
JPS501646B1 (ja) 1975-01-20
CH529913A (de) 1972-10-31

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