US3601500A - Rotor assembly for a fluid flow machine - Google Patents
Rotor assembly for a fluid flow machineInfo
- 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
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.
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)
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)
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 | Rotary machine |
Citations (6)
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 |
-
1968
- 1968-08-28 GB GB4109768A patent/GB1233022A/en not_active Expired
-
1969
- 1969-08-07 CH CH1199869A patent/CH501824A/en not_active IP Right Cessation
- 1969-08-12 US US849437A patent/US3601500A/en not_active Expired - Lifetime
- 1969-08-18 FR FR6928232A patent/FR2016486A1/fr not_active Withdrawn
- 1969-08-19 BE BE737656D patent/BE737656A/xx unknown
- 1969-08-27 JP JP44067240A patent/JPS4815325B1/ja active Pending
Patent Citations (6)
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)
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 |
---|---|
JPS4815325B1 (en) | 1973-05-14 |
DE1943809A1 (en) | 1970-04-02 |
CH501824A (en) | 1971-01-15 |
BE737656A (en) | 1970-02-02 |
DE1943809B2 (en) | 1971-07-01 |
GB1233022A (en) | 1971-05-26 |
FR2016486A1 (en) | 1970-05-08 |
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