GB706730A - Improvements relating to turbine rotors - Google Patents

Improvements relating to turbine rotors

Info

Publication number
GB706730A
GB706730A GB26078/51A GB2607851A GB706730A GB 706730 A GB706730 A GB 706730A GB 26078/51 A GB26078/51 A GB 26078/51A GB 2607851 A GB2607851 A GB 2607851A GB 706730 A GB706730 A GB 706730A
Authority
GB
United Kingdom
Prior art keywords
discs
segments
spacer
blade
adjacent
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
GB26078/51A
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.)
Metropolitan Vickers Electrical Co Ltd
Original Assignee
Metropolitan Vickers Electrical Co Ltd
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 Metropolitan Vickers Electrical Co Ltd filed Critical Metropolitan Vickers Electrical Co Ltd
Publication of GB706730A publication Critical patent/GB706730A/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
    • F01D11/005—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
    • 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
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps

Abstract

706,730. Turbine rotors. METROPOLITANVICKERS ELECTRICAL CO., Ltd. Nov. 7, 1951 [April 11, 1951], No. 26078/51. Class 110 (3) A turbine rotor has at least two blade-carrying discs which are axially-spaced apart at their peripheries and a spacer disc is disposed between each pair of blade-carrying discs, the spacer disc either being flared at its rim, or provided with peripheral segments which are flared at their radially-outermost portions, in the axial direction on opposite sides of the disc to within a small clearance distance from the cylindrical or other surface of revolution formed by the root portions of the adjacent blades. In Fig. 1 the rotor discs 3, 4, 5 carry blades 9 mounted in axial slots, the discs having inter-engaging radial teeth 8 and being held together by bolts 6. Spacer discs 11 are mounted between adjacent bladecarrying discs by means of tongue and groove connections 12, 13 and carry segments 14 mounted in axial slots at their peripheries. The rims 14b of the segments 14 have axially-extending flanges which are flush with the cylindrical surfaces 9c formed by the platforms 9a of adjacent rows of rotor blades 9. The segments are spaced apart in the circumferential direction to allow expansion. In Fig. 3, the spacer discs 22 extend completely between adjacent bladecarrying discs 17, 18, 19 and have axiallyextending flange portions 26 integral therewith. The edges of the flanges 26 have ribs 28 which engage slots 29 in the adjacent blade platforms so as to afford support for the flanges 26. The blade-carrying discs and spacer discs have a rebated connection at 23 and are held together by bolts 24. In a further embodiment, the blade-carrying and spacer discs are formed integrally by machining from a single forging and the spacer discs carry segments mounted in axial slots at their peripheries. The slots for the blades and segments may both be axial and formed by a single broaching operation.
GB26078/51A 1951-04-11 1951-11-07 Improvements relating to turbine rotors Expired GB706730A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US706730XA 1951-04-11 1951-04-11

Publications (1)

Publication Number Publication Date
GB706730A true GB706730A (en) 1954-04-07

Family

ID=22096702

Family Applications (1)

Application Number Title Priority Date Filing Date
GB26078/51A Expired GB706730A (en) 1951-04-11 1951-11-07 Improvements relating to turbine rotors

Country Status (1)

Country Link
GB (1) GB706730A (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2931622A (en) * 1956-12-24 1960-04-05 Orenda Engines Ltd Rotor construction for gas turbine engines
US5611669A (en) * 1994-09-27 1997-03-18 Eupopean Gas Turbines Limited Turbines with platforms between stages
EP1371814A1 (en) * 2002-06-11 2003-12-17 ALSTOM (Switzerland) Ltd Sealing arrangement for a rotor of a turbomachine
EP1106780A3 (en) * 1999-11-30 2004-02-11 General Electric Company Turbine rotor torque transmission
DE102008008887A1 (en) * 2008-02-13 2009-08-27 Man Turbo Ag Multi-piece bladed rotor for a turbomachine
JP2010164054A (en) * 2009-01-14 2010-07-29 General Electric Co <Ge> Device and system for reducing secondary air flow in gas turbine
EP2884051A1 (en) * 2013-12-13 2015-06-17 Siemens Aktiengesellschaft Rotor for a turbo engine, turbo engine, axial compressor, gas turbine and method for producing a rotor of a turbo engine
EP3244022A1 (en) * 2016-05-10 2017-11-15 General Electric Company Turbine assembly, turbine inner wall assembly and turbine assembly method
CN110722334A (en) * 2019-11-26 2020-01-24 中国航发沈阳黎明航空发动机有限责任公司 Method for broaching deformation of large axial mortise notch and eliminating tool connecting edge

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2931622A (en) * 1956-12-24 1960-04-05 Orenda Engines Ltd Rotor construction for gas turbine engines
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 Inter-blade seal
GB2293628B (en) * 1994-09-27 1998-04-01 Europ Gas Turbines Ltd Turbines
EP1106780A3 (en) * 1999-11-30 2004-02-11 General Electric Company Turbine rotor torque transmission
WO2003104617A1 (en) * 2002-06-11 2003-12-18 Alstom (Switzerland) Ltd Sealing arrangement for a rotor of a turbomachine
EP1371814A1 (en) * 2002-06-11 2003-12-17 ALSTOM (Switzerland) Ltd Sealing arrangement for a rotor of a turbomachine
US7220099B2 (en) 2002-06-11 2007-05-22 Alstom Technology Ltd. Sealing arrangement for a rotor of a turbo machine
DE102008008887A1 (en) * 2008-02-13 2009-08-27 Man Turbo Ag Multi-piece bladed rotor for a turbomachine
JP2010164054A (en) * 2009-01-14 2010-07-29 General Electric Co <Ge> Device and system for reducing secondary air flow in gas turbine
EP2884051A1 (en) * 2013-12-13 2015-06-17 Siemens Aktiengesellschaft Rotor for a turbo engine, turbo engine, axial compressor, gas turbine and method for producing a rotor of a turbo engine
EP3244022A1 (en) * 2016-05-10 2017-11-15 General Electric Company Turbine assembly, turbine inner wall assembly and turbine assembly method
CN110722334A (en) * 2019-11-26 2020-01-24 中国航发沈阳黎明航空发动机有限责任公司 Method for broaching deformation of large axial mortise notch and eliminating tool connecting edge
CN110722334B (en) * 2019-11-26 2021-04-27 中国航发沈阳黎明航空发动机有限责任公司 Method for broaching deformation of large axial mortise notch and eliminating tool connecting edge

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