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US3601500A - Rotor assembly for a fluid flow machine - Google Patents

Rotor assembly for a fluid flow machine

Info

Publication number
US3601500A
US3601500A US849437A US3601500DA US3601500A US 3601500 A US3601500 A US 3601500A US 849437 A US849437 A US 849437A US 3601500D A US3601500D A US 3601500DA US 3601500 A US3601500 A US 3601500A
Authority
US
United States
Prior art keywords
rotor
blades
rotor assembly
load
rotor blades
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 - Lifetime
Application number
US849437A
Inventor
Jack Palfreyman
Henry Edward Middleton
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Application granted granted Critical
Publication of US3601500A publication Critical patent/US3601500A/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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

A rotor assembly for a fluid flow machine comprising a rotor hub member provided with a plurality of angularly spaced apart rotor blades, and at least one load-distributing member which transmits predetermined torsional loads between the various rotor blades, the load-distributing member being free to move with respect to all the rotor blades but engaging the latter to distribute the load whenever any rotor blade, as a result of the application thereto of such a predetermined torsional load, moves with respect to the remaining rotor blades.

Claims (6)

1. A rotor assembly for a fluid flow machine comprising: a rotor hub member, a plurality of angularly spaced apart rotor blades bonded on said rotor hub member, said rotor blades having radially outwardly opening recesses in the tips thereof, and at least one load-distributing member engageable with said blades to transmit predetermined torsional loads therebetween, said loaddistributing member being mounted for limited free radial movement in said recesses and being normally free to move with respect to all said rotor blades on said rotor hub to avoid transfer to any of said blades of centrifugal forces from the load-distributing member.
2. A rotor assembly as claimed in claim 1 in which the load-distributing member comprises an annular member which is concentric with the rotor hub member.
3. A rotor assembly as claimed in claim 2 in which the annular member is a floating member which is mounted for limited circumferential movement within aligned recesses in the rotor blades.
4. A rotor assembly as claimed in claim 2 in which the annular member is connected to parts which extend throughout at least a portion of the angular distances between adjacent rotor blades which are closely spaced from the latter.
5. A rotor assembly as claimed in claim 2 in which there are a plurality of interconnected annular members.
6. A rotor assembly as claimed in claim 2 in which the annular member is formed of resin-impregnated fibrous material which has been wound in situ to form the annular member.
US849437A 1968-08-28 1969-08-12 Rotor assembly for a fluid flow machine Expired - Lifetime US3601500A (en)

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
US3601500A true US3601500A (en) 1971-08-24

Family

ID=10418107

Family Applications (1)

Application Number Title Priority Date Filing Date
US849437A Expired - Lifetime US3601500A (en) 1968-08-28 1969-08-12 Rotor assembly for a fluid flow machine

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 (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3857650A (en) * 1972-10-23 1974-12-31 Fiat Spa Vaned rotor for 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
US4728255A (en) * 1985-02-25 1988-03-01 General Electric Company Removable stiffening disk
WO1999037888A1 (en) * 1998-01-23 1999-07-29 Diversitech, Inc. Shrouds for gas turbine engines and methods for making the same
US6481963B1 (en) * 1999-09-03 2002-11-19 Delta Electronics Axial-flow fan having an air gap generation member
US20090252610A1 (en) * 2008-04-04 2009-10-08 General Electric Company Turbine blade retention system and method
US20140255174A1 (en) * 2012-12-21 2014-09-11 United Technologies Corporation Manufacture of full ring strut vane pack

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS56139349A (en) * 1980-03-31 1981-10-30 Hideki Hayashi Wall construction and execution thereof
DE19941134C1 (en) * 1999-08-30 2000-12-28 Mtu Muenchen Gmbh Blade crown ring for gas turbine aircraft engine has each blade provided with transition region between blade surface and blade platform having successively decreasing curvature radii
DE102010041808B4 (en) * 2010-09-30 2014-10-23 Siemens Aktiengesellschaft Blade segment, turbomachinery and process for their preparation
JP2015227627A (en) * 2014-05-30 2015-12-17 株式会社東芝 Rotating machine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB835177A (en) * 1957-06-14 1960-05-18 Burton Albert Avery Vibration damping shroud for gas turbine engines
US3034762A (en) * 1960-05-31 1962-05-15 United Aircraft Corp Blade damping means
US3048365A (en) * 1959-12-22 1962-08-07 Curtiss Wright Corp Rotor blade shroud and vibration damping structure
US3095138A (en) * 1957-05-28 1963-06-25 Studebaker Corp Rotating shroud
US3377050A (en) * 1966-06-21 1968-04-09 Bristol Siddeley Engines Ltd Shrouded rotor blades
US3393436A (en) * 1965-09-16 1968-07-23 Rolls Royce Method of securing a blade assembly in a casing, e. g., a gas turbine engine rotor casing

Patent Citations (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
US3393436A (en) * 1965-09-16 1968-07-23 Rolls Royce Method of securing a blade assembly in a casing, e. g., a gas turbine engine rotor casing
US3377050A (en) * 1966-06-21 1968-04-09 Bristol Siddeley Engines Ltd Shrouded rotor blades

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3857650A (en) * 1972-10-23 1974-12-31 Fiat Spa Vaned rotor for 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
US4728255A (en) * 1985-02-25 1988-03-01 General Electric Company Removable stiffening disk
WO1999037888A1 (en) * 1998-01-23 1999-07-29 Diversitech, Inc. Shrouds for gas turbine engines and methods for making the same
US6223524B1 (en) 1998-01-23 2001-05-01 Diversitech, Inc. Shrouds for gas turbine engines and methods for making the same
US6481963B1 (en) * 1999-09-03 2002-11-19 Delta Electronics Axial-flow fan having an air gap generation member
US20090252610A1 (en) * 2008-04-04 2009-10-08 General Electric Company Turbine blade retention system and method
US8894370B2 (en) * 2008-04-04 2014-11-25 General Electric Company Turbine blade retention system and method
US20140255174A1 (en) * 2012-12-21 2014-09-11 United Technologies Corporation Manufacture of full ring strut vane pack

Also Published As

Publication number Publication date
FR2016486A1 (en) 1970-05-08
JPS4815325B1 (en) 1973-05-14
GB1233022A (en) 1971-05-26
BE737656A (en) 1970-02-02
CH501824A (en) 1971-01-15
DE1943809A1 (en) 1970-04-02
DE1943809B2 (en) 1971-07-01

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