GB1524108A - Rotor for fluid flow machine - Google Patents

Rotor for fluid flow machine

Info

Publication number
GB1524108A
GB1524108A GB51553/76A GB5155376A GB1524108A GB 1524108 A GB1524108 A GB 1524108A GB 51553/76 A GB51553/76 A GB 51553/76A GB 5155376 A GB5155376 A GB 5155376A GB 1524108 A GB1524108 A GB 1524108A
Authority
GB
United Kingdom
Prior art keywords
rotor
discs
flow
blades
inner member
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
GB51553/76A
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.)
MTU Aero Engines GmbH
Original Assignee
MTU Motoren und Turbinen Union Muenchen 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 MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of GB1524108A publication Critical patent/GB1524108A/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
    • F01D5/02—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
    • 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
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1524108 Bladed rotors for axial-flow machines MOTOREN UND TURBINEN UNION MUNCHEN GmbH 9 Dec 1976 [12 Dec 1975] 51553/76 Heading F1T A rotor for a fluid-flow machine such as an axial-flow compressor comprises a series of rotor discs 1, 2 each carrying a row of blades 8, 9 at its periphery, each blade being formed with a platform portion 6, 7, the rotor discs being axially spaced apart and being inter-connected by intermediate rings. The intermediate ring comprises an inner portion 4 which is secured by welding to adjacent rotor discs 1, 2 and an outer member 5 disconnectably mounted on the inner member 4 for rotation therewith, the outer member comprising a plurality of part-annular segments which are individually detectable from the inner member 4 and which co-operate with the platforms of the rotor blades on the adjacent rotor discs so as to define the inner wall of the flow duct of the machine. The detectable connection between the part-annular members 5 and the inner member 4 may be similar to the mounting of the rotor blades on the discs e.g. by fir-tree, hammerhead or dovetail type mounting. The object of the invention is to facilitate removal and replacement of a damaged blade without complete disassembly of the rotor. Specification 1395957 is referred to.
GB51553/76A 1975-12-12 1976-12-09 Rotor for fluid flow machine Expired GB1524108A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19752555911 DE2555911A1 (en) 1975-12-12 1975-12-12 ROTOR FOR FLOW MACHINES, IN PARTICULAR GAS TURBINE JETS

Publications (1)

Publication Number Publication Date
GB1524108A true GB1524108A (en) 1978-09-06

Family

ID=5964155

Family Applications (1)

Application Number Title Priority Date Filing Date
GB51553/76A Expired GB1524108A (en) 1975-12-12 1976-12-09 Rotor for fluid flow machine

Country Status (3)

Country Link
DE (1) DE2555911A1 (en)
FR (1) FR2334818A1 (en)
GB (1) GB1524108A (en)

Cited By (8)

* 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
GB2312254A (en) * 1996-04-19 1997-10-22 Asea Brown Boveri Thermal protection of compressor rotor
FR2895021A1 (en) * 2005-12-16 2007-06-22 Snecma Sa Turbomachine e.g. low pressure turbine, for aircraft`s jet engine, has rotor composed of disks that are reunited by annular connecting part, and sealing unit arranged between blades of each disks and crown of diffuser blade
CN101818661A (en) * 2009-02-13 2010-09-01 通用电气公司 Catenary turbine seal systems
CN101845996A (en) * 2009-01-14 2010-09-29 通用电气公司 Interstage seal for gas turbine and corresponding gas turbine
EP2236767A3 (en) * 2009-04-02 2014-04-23 General Electric Company Gas turbine inner flowpath coverpiece
CN104564173A (en) * 2013-10-28 2015-04-29 通用电气公司 Sealing component for reducing secondary airflow in turbine system
EP3244022A1 (en) * 2016-05-10 2017-11-15 General Electric Company Turbine assembly, turbine inner wall assembly and turbine assembly method

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4659289A (en) * 1984-07-23 1987-04-21 United Technologies Corporation Turbine side plate assembly
GB2293628B (en) * 1994-09-27 1998-04-01 Europ Gas Turbines Ltd Turbines
US7186079B2 (en) * 2004-11-10 2007-03-06 United Technologies Corporation Turbine engine disk spacers
US8177495B2 (en) * 2009-03-24 2012-05-15 General Electric Company Method and apparatus for turbine interstage seal ring

Cited By (13)

* 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
GB2312254A (en) * 1996-04-19 1997-10-22 Asea Brown Boveri Thermal protection of compressor rotor
GB2312254B (en) * 1996-04-19 1999-05-05 Asea Brown Boveri Rotor assembly for a high-pressure compressor
FR2895021A1 (en) * 2005-12-16 2007-06-22 Snecma Sa Turbomachine e.g. low pressure turbine, for aircraft`s jet engine, has rotor composed of disks that are reunited by annular connecting part, and sealing unit arranged between blades of each disks and crown of diffuser blade
CN101845996B (en) * 2009-01-14 2015-04-01 通用电气公司 Device and system for reducing second air flow in gas turbine
CN101845996A (en) * 2009-01-14 2010-09-29 通用电气公司 Interstage seal for gas turbine and corresponding gas turbine
EP2208860A3 (en) * 2009-01-14 2012-12-05 General Electric Company Interstage seal for a gas turbine and corresponding gas turbine
EP2218879A3 (en) * 2009-02-13 2012-12-05 General Electric Company Rotor assembly with interstage seal
CN101818661A (en) * 2009-02-13 2010-09-01 通用电气公司 Catenary turbine seal systems
EP2236767A3 (en) * 2009-04-02 2014-04-23 General Electric Company Gas turbine inner flowpath coverpiece
CN104564173A (en) * 2013-10-28 2015-04-29 通用电气公司 Sealing component for reducing secondary airflow in turbine system
CN104564173B (en) * 2013-10-28 2018-06-05 通用电气公司 For reducing the containment member of the secondary air streams in turbine system
EP3244022A1 (en) * 2016-05-10 2017-11-15 General Electric Company Turbine assembly, turbine inner wall assembly and turbine assembly method

Also Published As

Publication number Publication date
DE2555911A1 (en) 1977-06-23
FR2334818A1 (en) 1977-07-08

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee