GB1093568A - Improvements in or relating to bladed rotors such as compressor rotors - Google Patents

Improvements in or relating to bladed rotors such as compressor rotors

Info

Publication number
GB1093568A
GB1093568A GB49761/65A GB4976165A GB1093568A GB 1093568 A GB1093568 A GB 1093568A GB 49761/65 A GB49761/65 A GB 49761/65A GB 4976165 A GB4976165 A GB 4976165A GB 1093568 A GB1093568 A GB 1093568A
Authority
GB
United Kingdom
Prior art keywords
segments
blades
rotors
platform
recess
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
GB49761/65A
Inventor
William Harrison
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
Priority to GB49761/65A priority Critical patent/GB1093568A/en
Priority to US595101A priority patent/US3393862A/en
Priority to DE19661628359 priority patent/DE1628359A1/en
Priority to FR84609A priority patent/FR1501492A/en
Publication of GB1093568A publication Critical patent/GB1093568A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • 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

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

1,093,568. Compressor rotors. ROLLSROYCE Ltd. Nov.23, 1965, No.49761/65. Heading F1T. The blades 14 in an axial flow compressor rotor stage of a gas turbine engine are mounted in axial slots 17 in the rotor disc 13. A platform segment having a top face 15a with a recess 27 to accommodate the blade root 18 is mounted between adjacent blades 14, the segments abutting to form a complete annular platform. The segments are held in position by engagement of heads 23 of tongues 22 in a circumferential keyway 20 in the disc periphery. Recess 27 does not extend the full axial extent of each top face 15a so that each blade 14 is prevented from moving axially out of its slot 17 in the downstream direction. The platform segments and/or the blades are of synthetic resin material. The segments are assembled one by one through an assembly slot (24), Fig. 5 (not shown), prior to insertion of the blades. A nose cone member (28), Fig. 2 (not shown) completes the assembly.
GB49761/65A 1965-11-23 1965-11-23 Improvements in or relating to bladed rotors such as compressor rotors Expired GB1093568A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB49761/65A GB1093568A (en) 1965-11-23 1965-11-23 Improvements in or relating to bladed rotors such as compressor rotors
US595101A US3393862A (en) 1965-11-23 1966-11-17 Bladed rotors
DE19661628359 DE1628359A1 (en) 1965-11-23 1966-11-23 BUCKET ROTOR ARRANGEMENT AND PROCEDURE FOR ASSEMBLY
FR84609A FR1501492A (en) 1965-11-23 1966-11-23 Improvements to paddle wheels, in particular compressor wheels

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB49761/65A GB1093568A (en) 1965-11-23 1965-11-23 Improvements in or relating to bladed rotors such as compressor rotors

Publications (1)

Publication Number Publication Date
GB1093568A true GB1093568A (en) 1967-12-06

Family

ID=10453453

Family Applications (1)

Application Number Title Priority Date Filing Date
GB49761/65A Expired GB1093568A (en) 1965-11-23 1965-11-23 Improvements in or relating to bladed rotors such as compressor rotors

Country Status (4)

Country Link
US (1) US3393862A (en)
DE (1) DE1628359A1 (en)
FR (1) FR1501492A (en)
GB (1) GB1093568A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993021425A1 (en) * 1992-04-16 1993-10-28 Rolls-Royce Plc Rotors for gas turbine engines
US8292586B2 (en) 2008-02-18 2012-10-23 Rolls-Royce Plc Annulus filler

Families Citing this family (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3661475A (en) * 1970-04-30 1972-05-09 Gen Electric Turbomachinery rotors
CH581783A5 (en) * 1975-01-30 1976-11-15 Bbc Sulzer Turbomaschinen
US4005515A (en) * 1975-03-03 1977-02-01 United Technologies Corporation Method of manufacturing a closed channel disk for a gas turbine engine
US3970412A (en) * 1975-03-03 1976-07-20 United Technologies Corporation Closed channel disk for a gas turbine engine
FR2502690B1 (en) * 1981-03-27 1985-09-13 Snecma DEVICE FOR LOCKING BLOWER VANES AND FOR FIXING A FRONT HOOD OF A TURBO-JET
JPS5865999A (en) * 1981-10-12 1983-04-19 Nissan Motor Co Ltd Slant flow type fan
US4482296A (en) * 1981-11-16 1984-11-13 Terry Corporation Bladed rotor assembly and method of forming same
FR2585069B1 (en) * 1985-07-16 1989-06-09 Snecma DEVICE FOR LIMITING THE ANGULAR DEFLECTION OF BLADES MOUNTED ON A TURBOMACHINE ROTOR DISC
DE3743253A1 (en) * 1987-12-19 1989-06-29 Mtu Muenchen Gmbh AXIAL FLOWED BLADE BLADES FOR COMPRESSORS OR TURBINES
US4915587A (en) * 1988-10-24 1990-04-10 Westinghouse Electric Corp. Apparatus for locking side entry blades into a rotor
FR2639402B1 (en) * 1988-11-23 1990-12-28 Snecma TURBOMACHINE ROTOR WING DISC
US5030063A (en) * 1990-02-08 1991-07-09 General Motors Corporation Turbomachine rotor
US5222865A (en) * 1991-03-04 1993-06-29 General Electric Company Platform assembly for attaching rotor blades to a rotor disk
FR2679296B1 (en) * 1991-07-17 1993-10-15 Snecma SEPARATE INTER-BLADE PLATFORM FOR TURBOMACHINE ROTOR WING DISC.
FR2679599A1 (en) * 1991-07-24 1993-01-29 Snecma IMPROVEMENT IN BLADES OF TURBOMACHINES.
US5277548A (en) * 1991-12-31 1994-01-11 United Technologies Corporation Non-integral rotor blade platform
GB2268978B (en) * 1992-07-21 1995-11-08 Rolls Royce Plc Fan for a ducted fan gas turbine engine
FR2706528B1 (en) * 1993-06-10 1995-09-01 Snecma Separate inter-blade platform of turbine engine rotor blade disc.
JP3631271B2 (en) * 1993-11-19 2005-03-23 ユナイテッド テクノロジーズ コーポレイション Inner shroud integrated stator vane structure
FR2715975B1 (en) * 1994-02-10 1996-03-29 Snecma Turbomachine rotor with axial or inclined through blade grooves.
GB9405473D0 (en) * 1994-03-19 1994-05-04 Rolls Royce Plc A gas turbine engine fan blade assembly
DE19615549B8 (en) * 1996-04-19 2005-07-07 Alstom Device for thermal protection of a rotor of a high-pressure compressor
US5720596A (en) * 1997-01-03 1998-02-24 Westinghouse Electric Corporation Apparatus and method for locking blades into a rotor
GB0614518D0 (en) * 2006-07-21 2006-08-30 Rolls Royce Plc A fan blade for a gas turbine engine
US7976281B2 (en) * 2007-05-15 2011-07-12 General Electric Company Turbine rotor blade and method of assembling the same
FR2918409B1 (en) * 2007-07-05 2011-05-27 Snecma ROTATING PART OF TURBOMACHINE COMPRISING INTER-AUB SECTIONS FORMING PLATFORM FIXED ON A DISK
ES2571853T3 (en) * 2007-12-27 2016-05-27 Techspace Aero Platform for a turbomachine blade wheel, blade wheel and compressor or turbomachine comprising such blade wheel
US8277190B2 (en) * 2009-03-27 2012-10-02 General Electric Company Turbomachine rotor assembly and method
GB0914060D0 (en) * 2009-08-12 2009-09-16 Rolls Royce Plc A rotor assembly for a gas turbine
FR2993927B1 (en) * 2012-07-27 2014-08-22 Snecma PIECE FOR MODIFYING THE PROFILE OF AERODYNAMIC VEIN
RU2525376C1 (en) * 2013-03-28 2014-08-10 Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО "УМПО" Gas turbine axial compressor wheel

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB701263A (en) * 1950-08-03 1953-12-23 Rolls Royce Improvements in or relating to turbo-machines
US2857093A (en) * 1954-12-02 1958-10-21 Cincinnati Testing & Res Lab Stator casing and blade assembly
NL102164C (en) * 1956-11-30
US2974924A (en) * 1956-12-05 1961-03-14 Gen Electric Turbine bucket retaining means and sealing assembly
US3034763A (en) * 1959-08-20 1962-05-15 United Aircraft Corp Rotor construction
GB903176A (en) * 1960-01-18 1962-08-15 Rolls Royce Method of mounting a multi-blade set on a support member, for example to form a gas turbine compressor rotor
US3047268A (en) * 1960-03-14 1962-07-31 Stanley L Leavitt Blade retention device
US3294364A (en) * 1962-01-02 1966-12-27 Gen Electric Rotor assembly
US3309058A (en) * 1965-06-21 1967-03-14 Rolls Royce Bladed rotor

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993021425A1 (en) * 1992-04-16 1993-10-28 Rolls-Royce Plc Rotors for gas turbine engines
US5466125A (en) * 1992-04-16 1995-11-14 Rolls-Royce Plc Rotors for gas turbine engines
US8292586B2 (en) 2008-02-18 2012-10-23 Rolls-Royce Plc Annulus filler

Also Published As

Publication number Publication date
US3393862A (en) 1968-07-23
FR1501492A (en) 1967-11-10
DE1628359A1 (en) 1973-10-18

Similar Documents

Publication Publication Date Title
GB1093568A (en) Improvements in or relating to bladed rotors such as compressor rotors
GB1040825A (en) Improvements in rotor blades and/or stator blades for gas turbine engines
US3033519A (en) Turbine nozzle vane construction
GB1195012A (en) Rotor for Bladed Fluid Flow Machines.
GB1008526A (en) Axial flow bladed rotor, e.g. for a turbine
GB1287223A (en) Improvements in or relating to turbine blading
GB1088360A (en) Improvements in gas turbine ducted fan engine sealing means
GB1219994A (en) Turbine for a compressible medium
GB1249279A (en) Improvements relating to pivotal guide vanes
GB1020900A (en) A seal between the rotor blades and the casing of axial-flow turbo-machines
GB1487324A (en) Gas turbine engines
GB1095830A (en) Bladed rotor for a fluid flow machine such as a gas turbine engine
GB1078157A (en) Means for containing fragments which have become detached from a rotating bladed member
GB1270203A (en) Improvements in turbo machines
GB1217275A (en) Gas turbine engine axial flow multi-stage compressor
GB1217807A (en) Gas turbine engine
GB1222926A (en) Turbomachine rotor assembly
GB831412A (en) Improvements relating to axial-flow turbines
GB1043168A (en) Improvements in or relating to turbo-compressors
GB1127269A (en) By-pass gas turbine engine having a compressor and fan exit guide vane assembly
GB1058759A (en) Improvements in or relating to the bladed diaphragms of turbines
GB736835A (en) Improvements in or relating to blading for axial flow turbo-engines
GB1011718A (en) Hydraulic turbines or pumps
GB1236920A (en) Bladed fluid flow machine
GB1296791A (en)