GB953931A - A multi-stage axial-flow elastic-fluid turbine - Google Patents

A multi-stage axial-flow elastic-fluid turbine

Info

Publication number
GB953931A
GB953931A GB3467261A GB3467261A GB953931A GB 953931 A GB953931 A GB 953931A GB 3467261 A GB3467261 A GB 3467261A GB 3467261 A GB3467261 A GB 3467261A GB 953931 A GB953931 A GB 953931A
Authority
GB
United Kingdom
Prior art keywords
rings
support rings
centring
blade support
extensions
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
Application number
GB3467261A
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.)
Licentia Patent Verwaltungs GmbH
Original Assignee
Licentia Patent Verwaltungs GmbH
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 Licentia Patent Verwaltungs GmbH filed Critical Licentia Patent Verwaltungs GmbH
Publication of GB953931A publication Critical patent/GB953931A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

953,931. Turbine stator assemblies. LICENTIA PATENT-VERWALTUNGSG.m.b.H. Sept. 27, 1961 [Sept. 28, 1960; Feb. 1, 1961; March 7, 1961], No. 34672/61. Heading F1T. In a multi-stage, axial-flow steam or gas turbine, the stator blades of each stage are mounted in support rings which are divided into a plurity of segments, the segments being mounted for limited movement in a radial direction, the movement being limited by two fixed contact surfaces and the segments being urged towards the outwardly-facing contact surface by resilient means. Centring rings are disposed between the blade support rings, each centring ring being formed at its inner periphery with portions which extend axially at either side thereof, the extensions projecting into circumferentially extending recesses formed in the adjacent faces of the adjacent blade support rings. The fixed contact surfaces are constituted by the axially-extending faces of the extensions. The turbine rotor 6 carries rows of blades 62 which co-operate with stator blades 12 mounted in support rings 1, each ring being divided into segments 15. Centring rings 2 are disposed between each pair of adjacent blade support rings 1, the centring rings being formed at their inner periphery with extensions 21 which project axially at both sides, the extensions being received within circumferentially extending grooves 11 formed in the sides of the blade support rings. Spacing rings 3 of wholly circular form are disposed between the outer portions of the centring rings, and leaf-spring members 4 extend between the spacing rings 3 and the blade support rings 1 so as to urge the support rings into engagement with the radially outwardly facing surfaces on the axial extensions 21 of the centring rings 2. The leaf springs 4 are received in circumferential recesses 14 formed in the blade support rings 1. The assembly described is supported and spaced within the turbine casing 9 by means of keys 5 which are received in grooves formed in the centring rings 2 and spacing rings 3 and in the turbine casing 9. The centring rings 2 are locked against circumferential movement with respect to the blade support rings 1 by means of key portions 22, Fig. 2, formed on the centring rings which engage in recesses 12 formed in the support rings. Shroud bands carried by the rotor and stator blades have sealing fins which co-operate with circumferential recesses formed in the blade support rings and in the rotor respectively. In a second embodiment in place of the leafsprings 4, permanent magnets are disposed in the stator blade support rings and in the spacer rings 3 so as to urge the support rings radially inwardly into contact with the outwardly facing surfaces on the centring rings.
GB3467261A 1960-09-28 1961-09-27 A multi-stage axial-flow elastic-fluid turbine Expired GB953931A (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DEL37127A DE1138071B (en) 1960-09-28 1960-09-28 Multi-stage axial turbine
DEL38097A DE1140945B (en) 1960-09-28 1961-02-01 Multi-stage, axially loaded constant pressure or overpressure turbine
DEL38385A DE1140946B (en) 1960-09-28 1961-03-07 Multi-stage, axially loaded constant pressure or overpressure turbine

Publications (1)

Publication Number Publication Date
GB953931A true GB953931A (en) 1964-04-02

Family

ID=27211396

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3467261A Expired GB953931A (en) 1960-09-28 1961-09-27 A multi-stage axial-flow elastic-fluid turbine

Country Status (5)

Country Link
BE (1) BE608497A (en)
CH (1) CH395142A (en)
DE (3) DE1138071B (en)
GB (1) GB953931A (en)
NL (1) NL269161A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2182174A2 (en) * 2008-10-29 2010-05-05 General Electric Company Steam turbine with pressure activated sealing device
EP3339581A1 (en) * 2016-12-22 2018-06-27 Ansaldo Energia S.p.A. Sealing system for a rotating machine
CN109555564A (en) * 2019-01-25 2019-04-02 沈阳航空航天大学 The brush seal structure of brush wire bundle Yu rotor cover radial clearance is adjusted containing magnet

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1239889B (en) * 1963-06-28 1967-05-03 Licentia Gmbh Inlet guide vane ring for axial turbines, in particular axial gas turbines, with radially resiliently pressed ring segments
US4247248A (en) * 1978-12-20 1981-01-27 United Technologies Corporation Outer air seal support structure for gas turbine engine
US4643636A (en) * 1985-07-22 1987-02-17 Avco Corporation Ceramic nozzle assembly for gas turbine engine
FR2683851A1 (en) * 1991-11-20 1993-05-21 Snecma TURBOMACHINE EQUIPPED WITH MEANS TO FACILITATE THE ADJUSTMENT OF THE GAMES OF THE STATOR INPUT STATOR AND ROTOR.
US5320486A (en) * 1993-01-21 1994-06-14 General Electric Company Apparatus for positioning compressor liner segments
GB0319002D0 (en) * 2003-05-13 2003-09-17 Alstom Switzerland Ltd Improvements in or relating to steam turbines
USD873874S1 (en) 2012-09-28 2020-01-28 Dürr Systems Ag Axial turbine housing for a rotary atomizer for a painting robot

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR392896A (en) * 1907-08-09 1908-12-08 George Westinghouse Improvements in turbines operated by the pressure of an elastic fluid
DE1055548B (en) * 1956-06-08 1959-04-23 Siemens Ag Overpressure axial turbine with pot housing

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2182174A2 (en) * 2008-10-29 2010-05-05 General Electric Company Steam turbine with pressure activated sealing device
EP2182174A3 (en) * 2008-10-29 2012-03-14 General Electric Company Steam turbine with pressure activated sealing device
EP3339581A1 (en) * 2016-12-22 2018-06-27 Ansaldo Energia S.p.A. Sealing system for a rotating machine
CN108223027A (en) * 2016-12-22 2018-06-29 安萨尔多能源公司 For the sealing system of rotary machine
CN109555564A (en) * 2019-01-25 2019-04-02 沈阳航空航天大学 The brush seal structure of brush wire bundle Yu rotor cover radial clearance is adjusted containing magnet
CN109555564B (en) * 2019-01-25 2023-08-29 沈阳航空航天大学 Brush type sealing structure with magnet and adjustable radial gap between brush filament bundle and rotor surface

Also Published As

Publication number Publication date
BE608497A (en) 1962-01-15
DE1138071B (en) 1962-10-18
DE1140945B (en) 1962-12-13
DE1140946B (en) 1962-12-13
NL269161A (en)
CH395142A (en) 1965-07-15

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