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GB877708A - Improvements in turbine rotors - Google Patents

Improvements in turbine rotors

Info

Publication number
GB877708A
GB877708A GB37093/59A GB3709359A GB877708A GB 877708 A GB877708 A GB 877708A GB 37093/59 A GB37093/59 A GB 37093/59A GB 3709359 A GB3709359 A GB 3709359A GB 877708 A GB877708 A GB 877708A
Authority
GB
United Kingdom
Prior art keywords
turbine
spacer
wheels
rings
flanges
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
GB37093/59A
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.)
Motors Liquidation Co
Original Assignee
General Motors 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 General Motors Corp filed Critical General Motors Corp
Publication of GB877708A publication Critical patent/GB877708A/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Abstract

877,708. Turbines. GENERAL MOTORS CORPORATION. Nov. 2, 1959 [Nov. 3, 1958], No. 37093/59. Class 110 (3). A bladed turbine rotor comprises rotor wheels to which blades are attached by blade roots lodged in undercut slots in the wheel rim, and spacer discs alternating with the wheels, each disc carrying on a channel-section rim a separate spacer ring having two radiallyinward flanges with projections which lodge in undercut slots in the respective walls of the channel-section rim. The rotor shown comprises a coaxial arrangement of rotor wheels 68, 70 and 72 with respective hub portions 82, 84 and 86 and spacer discs 92, 94 secured to a flange 88 on the turbine shaft 30 by bolts 90. The turbine blades 78 have roots 74 shaped to engage fir tree or under-cut slots 76 in the peripheries of the turbine wheels. The spacer discs 92, 94 are of channel-section at their peripheries. Fir tree or similar slots corresponding in number and dimension to those in the turbine wheels are formed in the peripheries of the discs 92, 94. Into each of the undercut slots is fitted a projection machined in radially inwardly-extending flanges 100 on a spacer ring 102. The ring 102 also has radially outwardly-extending flanges 104 and 106. A labyrinth seal assembly 120 has a rotating member 118 bolted to the first stage turbine wheel and bearing against a flange 126 on the blade platforms 80. The subsequent assembly of alternately spacer rings 102 and turbine blades 78 results in a series of abutments of flanges 104 and 106 with edges 108 and 110 of platforms 80. Axial movement in an upstream direction of turbine blades 78 and spacer rings 102 is prevented by tangs 112 and 113 and tangs 114 respectively. Axial movement in a downstream direction is prevented by a snap ring 134 securing together the tangs 113 on turbine blade 78 and a flange 132 on the third stage turbine wheel 72. The fixed member 122 of labyrinth seal assembly 120 is bolted to an annular bulkhead 64 and an annular stepped member 66 which are themselves joined to the main engine structure. The turbine outer casing is in three flanged portions 32, 34, 36 secured together by bolts 44. Shroud rings 46, 60 are secured to the section 32 by dowels 62. Further shroud rings 48, 50 are supported by external flanges in the casing sections 34, 36. Stator blades 52, fixed to stator shroud rings 46, 48, 50, have at their radially innermost ends circumferential ribs which co-operate with spacer rings 102 to form labyrinth seals.
GB37093/59A 1958-11-03 1959-11-02 Improvements in turbine rotors Expired GB877708A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US771337A US2972470A (en) 1958-11-03 1958-11-03 Turbine construction

Publications (1)

Publication Number Publication Date
GB877708A true GB877708A (en) 1961-09-20

Family

ID=25091487

Family Applications (1)

Application Number Title Priority Date Filing Date
GB37093/59A Expired GB877708A (en) 1958-11-03 1959-11-02 Improvements in turbine rotors

Country Status (2)

Country Link
US (1) US2972470A (en)
GB (1) GB877708A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2127906A (en) * 1982-09-29 1984-04-18 United Technologies Corp Rotor assembly e g for a gas turbine engine
GB2293628A (en) * 1994-09-27 1996-04-03 Europ Gas Turbines Ltd Turbomachine rotor

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3047268A (en) * 1960-03-14 1962-07-31 Stanley L Leavitt Blade retention device
DE3743253A1 (en) * 1987-12-19 1989-06-29 Mtu Muenchen Gmbh AXIAL FLOWED BLADE BLADES FOR COMPRESSORS OR TURBINES
DE102005059084A1 (en) * 2005-12-10 2007-06-14 Mtu Aero Engines Gmbh Turbomachine, in particular gas turbine
GB0814314D0 (en) * 2008-08-06 2008-09-10 Rolls Royce Plc A Method of assembling a multi-stage turbine or compressor
US9109457B2 (en) * 2010-09-03 2015-08-18 Siemens Energy, Inc. Axial locking seals for aft removable turbine blade
GB201309952D0 (en) * 2013-06-04 2013-07-17 Siemens Ag Shaft arrangement
US20150071771A1 (en) * 2013-09-12 2015-03-12 General Electric Company Inter-stage seal for a turbomachine
ITUB20160240A1 (en) * 2016-01-20 2017-07-20 Turboden Srl METHOD AND DEVICE TO REDUCE THE LEAKAGES OF TRAFILATION IN A TURBINE
US20170328203A1 (en) * 2016-05-10 2017-11-16 General Electric Company Turbine assembly, turbine inner wall assembly, and turbine assembly method
CN109723507B (en) * 2018-12-28 2023-09-12 中国船舶重工集团公司第七0三研究所 Helium stacking turbine mechanism

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US880479A (en) * 1907-03-15 1908-02-25 Charles D Wainwright Turbine-engine.
BE429026A (en) * 1937-07-07
GB586561A (en) * 1942-02-11 1947-03-24 Joseph Stanley Hall Improvements in high speed axial flow elastic fluid turbines, compressors, superchargers and like apparatus
GB612097A (en) * 1946-10-09 1948-11-08 English Electric Co Ltd Improvements in and relating to the cooling of gas turbine rotors
GB715044A (en) * 1952-07-29 1954-09-08 Rolls Royce Improvements in or relating to rotors of turbines and compressors
US2807434A (en) * 1952-04-22 1957-09-24 Gen Motors Corp Turbine rotor assembly
GB802476A (en) * 1955-09-29 1958-10-08 Rolls Royce Improvements in or relating to rotors of axial-flow fluid machines for example compressors and turbines

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2127906A (en) * 1982-09-29 1984-04-18 United Technologies Corp Rotor assembly e g for a gas turbine engine
GB2293628A (en) * 1994-09-27 1996-04-03 Europ Gas Turbines Ltd Turbomachine rotor
US5611669A (en) * 1994-09-27 1997-03-18 Eupopean Gas Turbines Limited Turbines with platforms between stages
EP0709548A3 (en) * 1994-09-27 1997-08-13 Europ Gas Turbines Ltd Interstice between stages of a rotor
GB2293628B (en) * 1994-09-27 1998-04-01 Europ Gas Turbines Ltd Turbines

Also Published As

Publication number Publication date
US2972470A (en) 1961-02-21

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