GB1233022A - - Google Patents

Info

Publication number
GB1233022A
GB1233022A GB4109768A GB1233022DA GB1233022A GB 1233022 A GB1233022 A GB 1233022A GB 4109768 A GB4109768 A GB 4109768A GB 1233022D A GB1233022D A GB 1233022DA GB 1233022 A GB1233022 A GB 1233022A
Authority
GB
United Kingdom
Prior art keywords
members
blades
parts
recesses
hub
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
GB4109768A
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 filed Critical
Publication of GB1233022A publication Critical patent/GB1233022A/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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,233,022. Turbomachine rotors. ROLLSROYCE Ltd. Aug.22, 1969 [Aug.28, 1968], No.41097/68. Heading F1T. The first stage rotor blades 21 of a gas turbine engine compressor are provided with annular members 25 which are normally freely floating within recesses 23 at the tips 24 of the blades so as not to transmit centrifugal forces to the latter. When however any exceptional torsional load is applied to a particular blade 21, e.g. as a result of a bird strike, the affected blade will engage the members 25 causing them to move and engage the remaining blades so as to distribute the exceptional load. Each of the members 25 is formed integrally with, or connected to, parts 26 which have surfaces 30, 31 which are closely spaced from the adjacent surfaces 32, 33 at the tips 24 of the blades. The parts 26 inter-connect the members 25 and thus assist in the transmission of the exceptional torsional load. The rotor hub 20, blades 21, members 25 and parts 26 are formed of resin impregnated fibrous material, e.g. carbon fibres impregnated with an expoxy resin, the blade roots 22 being bonded to the hub 20. The fibres in the hub 20 extend circumferentially thereof. The members 25 are formed by coating the recesses 23 with a releasing agent, winding resin coated fibres into these recesses and then curing the assembly. The parts 26 may be formed in situ after the surfaces 32, 33 have been coated with a releasing agent.
GB4109768A 1968-08-28 1968-08-28 Expired GB1233022A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4109768 1968-08-28

Publications (1)

Publication Number Publication Date
GB1233022A true GB1233022A (en) 1971-05-26

Family

ID=10418107

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4109768A Expired GB1233022A (en) 1968-08-28 1968-08-28

Country Status (6)

Country Link
US (1) US3601500A (en)
JP (1) JPS4815325B1 (en)
BE (1) BE737656A (en)
CH (1) CH501824A (en)
FR (1) FR2016486A1 (en)
GB (1) GB1233022A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2353826A (en) * 1999-08-30 2001-03-07 Mtu Muenchen Gmbh Aerofoil to platform transition in gas turbine blade/vane

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT975329B (en) * 1972-10-23 1974-07-20 Fiat Spa STRUCTURE OF STATIC OR ROTATING METALLIC AND NOM METALLIC PARTS FOR HIGH TEMPERATURE ENVIRONMENTS ESPECIALLY FOR ROTORS AND STATE OF GAS TURBINES
US4232996A (en) * 1978-10-06 1980-11-11 The United States Of America As Represented By The Secretary Of The Air Force Light weight fan assembly
JPS56139349A (en) * 1980-03-31 1981-10-30 Hideki Hayashi Wall construction and execution thereof
US4728255A (en) * 1985-02-25 1988-03-01 General Electric Company Removable stiffening disk
US6223524B1 (en) * 1998-01-23 2001-05-01 Diversitech, Inc. Shrouds for gas turbine engines and methods for making the same
TW446144U (en) * 1999-09-03 2001-07-11 Delta Electronics Inc Improved fan blade
US8894370B2 (en) * 2008-04-04 2014-11-25 General Electric Company Turbine blade retention system and method
DE102010041808B4 (en) * 2010-09-30 2014-10-23 Siemens Aktiengesellschaft Blade segment, turbomachinery and process for their preparation
US20140255174A1 (en) * 2012-12-21 2014-09-11 United Technologies Corporation Manufacture of full ring strut vane pack
JP2015227627A (en) * 2014-05-30 2015-12-17 株式会社東芝 Rotary machine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3095138A (en) * 1957-05-28 1963-06-25 Studebaker Corp Rotating shroud
GB835177A (en) * 1957-06-14 1960-05-18 Burton Albert Avery Vibration damping shroud for gas turbine engines
US3048365A (en) * 1959-12-22 1962-08-07 Curtiss Wright Corp Rotor blade shroud and vibration damping structure
US3034762A (en) * 1960-05-31 1962-05-15 United Aircraft Corp Blade damping means
GB1054608A (en) * 1965-09-16
GB1195012A (en) * 1966-06-21 1970-06-17 Rolls Royce Rotor for Bladed Fluid Flow Machines.

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2353826A (en) * 1999-08-30 2001-03-07 Mtu Muenchen Gmbh Aerofoil to platform transition in gas turbine blade/vane
US6478539B1 (en) 1999-08-30 2002-11-12 Mtu Aero Engines Gmbh Blade structure for a gas turbine engine
GB2353826B (en) * 1999-08-30 2003-07-23 Mtu Muenchen Gmbh Blade ring for a gas turbine

Also Published As

Publication number Publication date
US3601500A (en) 1971-08-24
JPS4815325B1 (en) 1973-05-14
BE737656A (en) 1970-02-02
CH501824A (en) 1971-01-15
FR2016486A1 (en) 1970-05-08
DE1943809B2 (en) 1971-07-01
DE1943809A1 (en) 1970-04-02

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLNP Patent lapsed through nonpayment of renewal fees