US3647311A - Turbine interstage seal assembly - Google Patents

Turbine interstage seal assembly Download PDF

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Publication number
US3647311A
US3647311A US31120A US3647311DA US3647311A US 3647311 A US3647311 A US 3647311A US 31120 A US31120 A US 31120A US 3647311D A US3647311D A US 3647311DA US 3647311 A US3647311 A US 3647311A
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US
United States
Prior art keywords
segments
rotor
seal assembly
housing member
disposed
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
US31120A
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English (en)
Inventor
Horace Wootton
George M Mierley Sr
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Westinghouse Electric Corp
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Westinghouse Electric Corp
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Publication date
Application filed by Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
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Publication of US3647311A publication Critical patent/US3647311A/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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters

Definitions

  • ABSTRACT lnterstage leakage around the inner shrouds of the stationary [73] Assignee: Westinghouse Electric Corporation, Pittsburgh, Pa.
  • the operating temperatures of gas turbines are being increased to increase their output.
  • the increase in operating temperature without exceeding the permissible temperature of the materials is attained by the introduction of a cooling fluid, such as air, into the turbine hot components such as the rotor blades and blade roots, and the stationary vane structure. It is desirable to conserve the cooling air and to direct its flow toward the hottest components of the turbine. Also, it is desirable to decrease the cost of a turbine by simplifying its structure.
  • clearances between stationary members of a turbine interstage seal assembly and points on the turbine rotor are reduced by utilizing radially disposed layers of thin sheet metal segments which cooperate with an annular seal housing member encircling the rotor to define an annular chamber between the rotor and the stator vane inner shroud segments.
  • the sheet metal segments are separated from the hot vanes and are supported by the housing member which is cooled by air supplied through the hollow stator vanes.
  • the pressure in the chamber is maintained at a value slightly higher than the pressure ahead of the stage so that there will be a positive flow of relatively cool air through relatively narrow passages between the seal members and the rotor.
  • the metal segments are attached to the housing member by means of bolts and spacers and the housing member is held concentric with the rotor axis by means of radial keys on the lower half of the housing member.
  • the keys are adjustable in radial slots in the shroud segments by means of eccentric bushings on certain of the bolts which attach the metal segments to the housing member.
  • FIG. 1 is a view, in axial section, taken along the line II in FIG. 2, of a portion of an axial flow gas turbine having an interstage seal assembly constructed in accordance with principles of the invention;
  • FIG. 2 is a reduced view, partly in elevation and partly in section, taken along the line lI-II in FIG. 1, and
  • FIG. 3 is a detail view, in section, showing the key arrangement for holding the seal housing member concentric with the rotor axis.
  • the structure shown therein comprises a portion of an axial flow gas turbine which includes an annular array of circumferentially spaced stationary blades or vanes 11 secured between arcuate outer shroud segments (not shown) and arcuate inner shroud segments 13.
  • the outer shroud segments 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 row of rotor blades 14 is disposed immediately downstream from the stationary blades 11.
  • the rotor blades are suitably attached to the periphery of a rotor wheel 15 secured to a shaft having an axis 16 and rotatably mounted in the turbine casing.
  • the stationary blades 11 and the rotor blades 14 constitute one stage of the turbine which may include other stationary and rotary blades similar to the ones shown, thereby providing a multistage 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 into the turbine through a suitable transition passageway (not shown) and then through the stationary vanes and the rotor blades of the stages of the turbine.
  • the rotor 15 is driven by energy extracted from the hot elastic fluid in a manner well known in the art.
  • Compressed coolant fluid may be introduced into the turbine through the stationary vanes 11, which are of a hollow construction and thence through an opening 17 in the shroud segment 13.
  • the coolant fluid such as air, may be supplied from a suitable source such as a compressor (not shown).
  • a seal assembly 21 is provided in the space between rotor wheels or discs 15 of the turbine.
  • the seal assembly 21 is so constructed that it defines a substantially enclosed annular chamber 22 between the rotor 15 and the stator vane inner shroud segments 13 for receiving the coolant fluid.
  • the pres sure of the coolant fluid inside the chamber 22 is maintained at a value slightly higher than the pressure of the motive fluid immediately upstream from the stationary vanes 11.
  • the hot motive fluid is prevented from entering the chamber 22 and leakage of the hot motive fluid around the stationary vanes 11 is minimized.
  • the clearance at points A and B has necessarily been large because the stationary members which control this clearance have been integral with the vane segments and expand inwardly toward the rotor as the turbine comes up to operating temperature.
  • the clearance at points A and B can be much smaller because the members of the seal assembly 21 are separated from the hot vanes 11 and are supported by a seal housing member 23 which is cooled by the coolant fluid.
  • the annular seal housing member 23 has an axially extending portion 24 disposed in sealing relation with the rotor 15 and a radially extending flange 25 disposed in sealing relation with an inwardly extending projection 26 on the shroud segment 13.
  • the projection 26 has a seal face 27 engaged by a seal face 28 on the flange 25.
  • a labyrinth seal 29 may be provided between the portion 24 of the housing member 23 and the rotor 15.
  • Radially disposed relatively thin sheet metal segments 31 cooperate with the seal housing member 23 to define the substantially enclosed chamber 22 and to form a barrier to reduce loss of cooling air from the chamber. As shown, the segments 31 engage a seal surface 32 on the inner shroud segment 13 and the segments 31 are spaced a relatively small distance from an annular surface 33 on the rotor 15 to restrict the flow of cooling air through the annular passage at B.
  • the segments 31 are disposed in two layers with expansion joints between segments staggered to prevent leakage between the ends of the segments. The gaps between the ends of the segments permit circumferential expansion of the segments due to rise in temperature.
  • Additional thin sheet metal segments 34 are disposed to engage a seal face 35 on the seal housing member 23 and a seal face 36 on the projection 26 on the shroud segment 13. As shown in FIG. 2, the segments 34 are disposed in two layers with expansion joints between layers staggered in the same manner as the segments 31. The segments 34 have an axially extending portion 37 spaced from a projection 38 on the rotor wheel 15 to maintain a relatively small clearance at point A.
  • coolant fluid which leaks through the labyrinth seal 29 into the space 39 is restricted at point A.
  • coolant fluid is directed through an opening 41 in a sideplate 42 on the rotor wheel to cool the root portions of the rotor blades 14 in a manner fully described in a copending application Ser. No. 739,274, filed June 24, 1968 by A. J. Scalzo and Andrew Zabrodsky and assigned to the Westinghouse Electric Corporation.
  • the seal segments 34 also cooperate with the seal housing member 23 to prevent loss of cooling air from the chamber 22 at the seal surfaces 27 and 28.
  • the seal segments 31 and 34 are attached to the flange 25 by two bolts 43 per segment.
  • the segments 31 are spaced from the flange 25 by pipe spacing members 44 which engage a shoulder 45 at the head of each bolt.
  • Resilient means such as a Belleville spring washer 46, is disposed around the shoulder 45 between the end of the pipe spacer 44 and the segments 31 to control the clamping action on the metal segments 31. In this manner the loading on the segments is limited so that the segments can slide under the boltheads without danger of buckling.
  • the seal segments 34 are spaced from the flange 25 by means of pipe spacers 47 disposed between the flange 25 and a shoulder 48 on a nut 49 threaded onto each bolt 43.
  • a Belleville washer 46 is disposed around the shoulder 48 to control the pressure applied on the segments 34 in the manner hereinbefore described.
  • elongated holes 51 are provided in the segments 34 for the bolts 43 to allow for circumferential growth while retaining positive positioning of the segments in a radial direction.
  • elongated holes 51 are provided in the segments 31 for the bolts 43.
  • the seal housing member 23 is held concentric with the rotor axis 16 by means of 6 radial keys 52 disposed in radial slots 53 in the projections 26 on the shroud segments 13.
  • the keys 52 are provided in the lower half only of the seal housing member 23.
  • the keys 52 are adjustable by means of eccentric bushings 54 on the bolts 43, thereby assuring proper alignment of the seal housing member 23.
  • the keys 52 and eccentric bushings 54 take the place of the pipe spacers 47 on the bolts on which the keys are mounted. In this manner the seal segments 34 are maintained in spaced relation with the seal housing member 25, and the desired pressure on the seal segments is maintained.
  • the keys 52 are provided in only the lower half of the seal housing member 23 and the key may be spaced in the manner shown in FIG. 2.
  • the bolts 43 and pipe spacers 47 are provided between the keys 52 in the lower half of the seal housing member 23.
  • seal segment plates 31 permits an initial cold spring pressure between surfaces at 32, thereby assuring that the joint between the seal segments 31 and the shroud segment 13 stays tight.
  • the segments 34 cooperate with the seal housing member 23 and the shroud segment 13 to prevent leakage of the cooling air through the joint between seal surfaces 27 and 28.
  • the invention provides a seal assembly which makes it possible to reduce clearances between stationary and rotating parts of a turbine since the members of the seal assembly are separated from hot portions of the turbine and they are supported on a member which is cooled by cooling air introduced into the turbine.
  • the seal assembly conserves the cooling air and directs its flow in a manner to cool otherwise hot portions of the turbine. Furthermore, the seal assembly minimizes leakage of the hot motive fluid around the stationary vanes of the turbine.
  • stator having an annular array of stator vanes with inner shroud segments secured to the vanes
  • a rotor having an annular row of rotor blades disposed downstream from the stator vanes, an annular seal housing member enclrclrng the rotor up stream from the rotor blades,
  • said housing member having an axially extending portion disposed in sealing relation with said rotor and a radially extending flange disposed in sealing relation with said inner shroud segments, and
  • the attaching means includes bolts extending through said flange and spacing members disposed between the metal segments and the flange to apply a clamping action on the segments.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US31120A 1970-04-23 1970-04-23 Turbine interstage seal assembly Expired - Lifetime US3647311A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US3112070A 1970-04-23 1970-04-23

Publications (1)

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US3647311A true US3647311A (en) 1972-03-07

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Application Number Title Priority Date Filing Date
US31120A Expired - Lifetime US3647311A (en) 1970-04-23 1970-04-23 Turbine interstage seal assembly

Country Status (8)

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US (1) US3647311A (enrdf_load_stackoverflow)
JP (1) JPS4826089B1 (enrdf_load_stackoverflow)
CA (1) CA919209A (enrdf_load_stackoverflow)
CH (1) CH538048A (enrdf_load_stackoverflow)
DE (1) DE2117475A1 (enrdf_load_stackoverflow)
FR (1) FR2086275B1 (enrdf_load_stackoverflow)
GB (1) GB1295025A (enrdf_load_stackoverflow)
NL (1) NL7105492A (enrdf_load_stackoverflow)

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3865504A (en) * 1972-09-08 1975-02-11 Bbc Sulzer Turbomaschinen Axial compressor
US3999883A (en) * 1975-07-02 1976-12-28 General Motors Corporation Variable turbomachine stator
US4286921A (en) * 1979-12-13 1981-09-01 Westinghouse Electric Corp. Locking structure for an alignment bushing of a combustion turbine engine
US4648793A (en) * 1985-05-31 1987-03-10 General Electric Company Turbine wheel key and keyway ventilation
US4668161A (en) * 1985-05-31 1987-05-26 General Electric Company Ventilation of turbine components
US5161945A (en) * 1990-10-10 1992-11-10 Allied-Signal Inc. Turbine engine interstage seal
US5233824A (en) * 1990-10-10 1993-08-10 Allied-Signal Inc. Turbine engine interstage seal
US5284347A (en) * 1991-03-25 1994-02-08 General Electric Company Gas bearing sealing means
RU2133345C1 (ru) * 1998-04-14 1999-07-20 Багдасарян Вазген Сергеевич Газотурбинная установка с аэродинамическим лабиринтовинтовым уплотнением
US6217279B1 (en) * 1997-06-19 2001-04-17 Mitsubishi Heavy Industries, Ltd. Device for sealing gas turbine stator blades
US6558114B1 (en) * 2000-09-29 2003-05-06 Siemens Westinghouse Power Corporation Gas turbine with baffle reducing hot gas ingress into interstage disc cavity
EP1235010A3 (en) * 2001-02-21 2004-01-21 General Electric Company Repositionable brush seal for turbomachinery
US6695575B1 (en) * 1999-08-27 2004-02-24 Siemens Aktiengesellschaft Turbine method for discharging leakage fluid
EP1978265A1 (en) * 2007-04-02 2008-10-08 Ansaldo Energia S.P.A. A maintenance method of a gas turbine unit and gas turbine unit
US20080253878A1 (en) * 2006-09-15 2008-10-16 Aisan Kogyo Kabushiki Kaisha Fuel pump
US20100048340A1 (en) * 2007-04-25 2010-02-25 Toyota Jidosha Kabushiki Kaisha Automatic transmission damper mechanism
US20100074731A1 (en) * 2008-09-25 2010-03-25 Wiebe David J Gas Turbine Sealing Apparatus
US20100074732A1 (en) * 2008-09-25 2010-03-25 John Joseph Marra Gas Turbine Sealing Apparatus
US20100074730A1 (en) * 2008-09-25 2010-03-25 George Liang Gas turbine sealing apparatus
US20100074733A1 (en) * 2008-09-25 2010-03-25 Siemens Energy, Inc. Ingestion Resistant Seal Assembly
US20100158700A1 (en) * 2008-12-18 2010-06-24 Honeywell International Inc. Turbine blade assemblies and methods of manufacturing the same
US8419356B2 (en) 2008-09-25 2013-04-16 Siemens Energy, Inc. Turbine seal assembly
EP2594743A1 (en) 2011-11-21 2013-05-22 Siemens Aktiengesellschaft Eccentric diaphragm adjusting pins for a gas turbine engine
US8534673B2 (en) 2010-08-20 2013-09-17 Mitsubishi Power Systems Americas, Inc. Inter stage seal housing having a replaceable wear strip
US20130251500A1 (en) * 2012-03-23 2013-09-26 Kin-Leung Cheung Gas turbine engine case with heating layer and method
US9017014B2 (en) 2013-06-28 2015-04-28 Siemens Energy, Inc. Aft outer rim seal arrangement
CN109751238A (zh) * 2019-02-22 2019-05-14 郑州沃华机械有限公司 一种熔体齿轮泵及其密封结构
US10337344B2 (en) 2014-05-27 2019-07-02 Siemens Aktiengesellschaft Turbomachine with an ingestion shield and use of the turbomachine
US10337345B2 (en) 2015-02-20 2019-07-02 General Electric Company Bucket mounted multi-stage turbine interstage seal and method of assembly
CN114341533A (zh) * 2019-09-04 2022-04-12 舍弗勒技术股份两合公司 具有轴密封件的冷却剂调节器

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5399403U (enrdf_load_stackoverflow) * 1977-01-18 1978-08-11
US4127357A (en) * 1977-06-24 1978-11-28 General Electric Company Variable shroud for a turbomachine
US4332133A (en) * 1979-11-14 1982-06-01 United Technologies Corporation Compressor bleed system for cooling and clearance control
SE448757B (sv) * 1980-05-19 1987-03-16 Avco Corp Munstycke for en gasturbinmotor
EP0144842B1 (en) * 1983-12-05 1988-07-27 Westinghouse Electric Corporation Cascaded air supply for gas turbine cooling
EP0815353B1 (en) * 1995-03-15 2000-01-26 United Technologies Corporation Wear resistant gas turbine engine airseal assembly
DE102022124401A1 (de) * 2022-09-22 2024-03-28 MTU Aero Engines AG Modul für eine strömungsmaschine
DE102023117910A1 (de) * 2023-07-06 2025-01-09 MTU Aero Engines AG Modul für eine strömungsmaschine

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2741455A (en) * 1950-06-29 1956-04-10 Rolls Royce Gas-turbine engines and nozzle-guidevane assemblies therefor
US2917276A (en) * 1955-02-28 1959-12-15 Orenda Engines Ltd Segmented stator ring assembly
US3529904A (en) * 1968-10-28 1970-09-22 Westinghouse Electric Corp Diaphragm seal structure

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2741455A (en) * 1950-06-29 1956-04-10 Rolls Royce Gas-turbine engines and nozzle-guidevane assemblies therefor
US2917276A (en) * 1955-02-28 1959-12-15 Orenda Engines Ltd Segmented stator ring assembly
US3529904A (en) * 1968-10-28 1970-09-22 Westinghouse Electric Corp Diaphragm seal structure

Cited By (43)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3865504A (en) * 1972-09-08 1975-02-11 Bbc Sulzer Turbomaschinen Axial compressor
US3999883A (en) * 1975-07-02 1976-12-28 General Motors Corporation Variable turbomachine stator
US4286921A (en) * 1979-12-13 1981-09-01 Westinghouse Electric Corp. Locking structure for an alignment bushing of a combustion turbine engine
US4648793A (en) * 1985-05-31 1987-03-10 General Electric Company Turbine wheel key and keyway ventilation
US4668161A (en) * 1985-05-31 1987-05-26 General Electric Company Ventilation of turbine components
US5233824A (en) * 1990-10-10 1993-08-10 Allied-Signal Inc. Turbine engine interstage seal
US5161945A (en) * 1990-10-10 1992-11-10 Allied-Signal Inc. Turbine engine interstage seal
US5284347A (en) * 1991-03-25 1994-02-08 General Electric Company Gas bearing sealing means
US6217279B1 (en) * 1997-06-19 2001-04-17 Mitsubishi Heavy Industries, Ltd. Device for sealing gas turbine stator blades
RU2133345C1 (ru) * 1998-04-14 1999-07-20 Багдасарян Вазген Сергеевич Газотурбинная установка с аэродинамическим лабиринтовинтовым уплотнением
US6695575B1 (en) * 1999-08-27 2004-02-24 Siemens Aktiengesellschaft Turbine method for discharging leakage fluid
US6558114B1 (en) * 2000-09-29 2003-05-06 Siemens Westinghouse Power Corporation Gas turbine with baffle reducing hot gas ingress into interstage disc cavity
EP1235010A3 (en) * 2001-02-21 2004-01-21 General Electric Company Repositionable brush seal for turbomachinery
US20080253878A1 (en) * 2006-09-15 2008-10-16 Aisan Kogyo Kabushiki Kaisha Fuel pump
US8523513B2 (en) * 2006-09-15 2013-09-03 Aisan Kogyo Kabushiki Kaisha Fuel pump
US8443514B2 (en) 2007-04-02 2013-05-21 Ansaldo Energia S.P.A. Maintenance method of a gas turbine unit and gas turbine unit
US20100126013A1 (en) * 2007-04-02 2010-05-27 Ansaldo Energia S.P.A. Maintenance method of a gas turbine unit and gas turbine unit
EP1978265A1 (en) * 2007-04-02 2008-10-08 Ansaldo Energia S.P.A. A maintenance method of a gas turbine unit and gas turbine unit
RU2461742C2 (ru) * 2007-04-02 2012-09-20 Ансальдо Энергия С.П.А. Способ технического обслуживания газотурбинного устройства и газотурбинное устройство
WO2008119806A1 (en) * 2007-04-02 2008-10-09 Ansaldo Energia S.P.A. A maintenance method of a gas turbine unit and gas turbine unit
US20100048340A1 (en) * 2007-04-25 2010-02-25 Toyota Jidosha Kabushiki Kaisha Automatic transmission damper mechanism
US20100074733A1 (en) * 2008-09-25 2010-03-25 Siemens Energy, Inc. Ingestion Resistant Seal Assembly
US20100074730A1 (en) * 2008-09-25 2010-03-25 George Liang Gas turbine sealing apparatus
US8075256B2 (en) 2008-09-25 2011-12-13 Siemens Energy, Inc. Ingestion resistant seal assembly
US8162598B2 (en) 2008-09-25 2012-04-24 Siemens Energy, Inc. Gas turbine sealing apparatus
US20100074732A1 (en) * 2008-09-25 2010-03-25 John Joseph Marra Gas Turbine Sealing Apparatus
US20100074731A1 (en) * 2008-09-25 2010-03-25 Wiebe David J Gas Turbine Sealing Apparatus
US8376697B2 (en) 2008-09-25 2013-02-19 Siemens Energy, Inc. Gas turbine sealing apparatus
US8388309B2 (en) 2008-09-25 2013-03-05 Siemens Energy, Inc. Gas turbine sealing apparatus
US8419356B2 (en) 2008-09-25 2013-04-16 Siemens Energy, Inc. Turbine seal assembly
US20100158700A1 (en) * 2008-12-18 2010-06-24 Honeywell International Inc. Turbine blade assemblies and methods of manufacturing the same
US8292587B2 (en) * 2008-12-18 2012-10-23 Honeywell International Inc. Turbine blade assemblies and methods of manufacturing the same
US8534673B2 (en) 2010-08-20 2013-09-17 Mitsubishi Power Systems Americas, Inc. Inter stage seal housing having a replaceable wear strip
US10633997B2 (en) 2010-08-20 2020-04-28 Mitsubishi Hitachi Power Systems Americas, Inc. Inter stage seal housing having a replaceable wear strip
EP2594743A1 (en) 2011-11-21 2013-05-22 Siemens Aktiengesellschaft Eccentric diaphragm adjusting pins for a gas turbine engine
WO2013075898A1 (en) 2011-11-21 2013-05-30 Siemens Aktiengesellschaft Eccentric diaphragm adjusting pins for a gas turbine engine
US20130251500A1 (en) * 2012-03-23 2013-09-26 Kin-Leung Cheung Gas turbine engine case with heating layer and method
US9017014B2 (en) 2013-06-28 2015-04-28 Siemens Energy, Inc. Aft outer rim seal arrangement
US10337344B2 (en) 2014-05-27 2019-07-02 Siemens Aktiengesellschaft Turbomachine with an ingestion shield and use of the turbomachine
US10337345B2 (en) 2015-02-20 2019-07-02 General Electric Company Bucket mounted multi-stage turbine interstage seal and method of assembly
CN109751238A (zh) * 2019-02-22 2019-05-14 郑州沃华机械有限公司 一种熔体齿轮泵及其密封结构
CN109751238B (zh) * 2019-02-22 2024-03-08 郑州沃华机械有限公司 一种熔体齿轮泵及其密封结构
CN114341533A (zh) * 2019-09-04 2022-04-12 舍弗勒技术股份两合公司 具有轴密封件的冷却剂调节器

Also Published As

Publication number Publication date
GB1295025A (enrdf_load_stackoverflow) 1972-11-01
FR2086275B1 (enrdf_load_stackoverflow) 1975-04-18
JPS4826089B1 (enrdf_load_stackoverflow) 1973-08-06
CA919209A (en) 1973-01-16
FR2086275A1 (enrdf_load_stackoverflow) 1971-12-31
NL7105492A (enrdf_load_stackoverflow) 1971-10-26
CH538048A (de) 1973-06-15
DE2117475A1 (de) 1971-11-11

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