GB802476A - Improvements in or relating to rotors of axial-flow fluid machines for example compressors and turbines - Google Patents

Improvements in or relating to rotors of axial-flow fluid machines for example compressors and turbines

Info

Publication number
GB802476A
GB802476A GB27796/55A GB2779655A GB802476A GB 802476 A GB802476 A GB 802476A GB 27796/55 A GB27796/55 A GB 27796/55A GB 2779655 A GB2779655 A GB 2779655A GB 802476 A GB802476 A GB 802476A
Authority
GB
United Kingdom
Prior art keywords
plate
lugs
projections
blade
rotor disc
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
GB27796/55A
Inventor
Lionel Haworth
James Alexander Petrie
Frederick Moss
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 GB27796/55A priority Critical patent/GB802476A/en
Priority to US608458A priority patent/US2998959A/en
Priority to FR1158244D priority patent/FR1158244A/en
Publication of GB802476A publication Critical patent/GB802476A/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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates

Landscapes

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

Abstract

802,476. Turbine and compressor bladed rotors. ROLLS-ROYCE, Ltd. Sept. 4, 1956 [Sept. 29, 1955], No. 27796/55. Class 110 (3). In an axial-flow turbine or compressor, rotor blades 12 are mounted by their roots 14 in axial slots formed in the rim 11 of the rotor disc 10 and means are provided to retain the root portions against displacement in the slots. The blades shown are formed with blade platforms 13, with fir-tree root portions 14 and with narrow stem portions 16 between the platform and root portions. Each blade platform is provided with an inwardly-facing groove 20, the grooves of the blade assembly together forming a continuous annular groove. The face of the rotor disc corresponding to that on which the grooves 20 are disposed is formed with an inwardly-facing circumferential groove 21, also with an interrupted circumferential land 11a and with spaced projections 22, 23. A flat annular plate 25 is provided to prevent displacement of the blades to the right (as seen in Fig. 4), the plate 25 having a gap 26 at one point so that it may be contracted in diameter, and when so contracted it is placed adjacent the side of the rotor disc and blade root portions. When allowed to expand, the rim portion 28 of the plate 25 engages the circumferential groove 20 formed on the under-surfaces of the blade platforms 13 and the flange 30 at the inner periphery of the plate 25 engages the circumferential groove 21 in the rotor disc. The plate 25 is also formed with inwardly-extending lugs 31, 32 which correspond to the projections 22, 23 on the rotor disc, and upon assembly the plate is so positioned that the lugs 31, 32 are in the positions shown at 31a, 32a in Fig. 2. After the plate 25 has been allowed to expand to engage the grooves 20, 21, it is rotated so that the lugs 31, 32 are radially aligned with the projections 22, 23. A block 34 is then entered between the projections 32 and lugs 23, the block having a flange to engage in the groove 21. A pin 35 is engaged in holes in the block 34 and lugs 32, the ends of the pin being bent over to prevent its disengagement. The gap 26 in the plate 25 is arranged to be disposed adjacent one of the blade stems 16 so as to prevent leakage between adjacent blade stems. The land 11a is provided so that the edge of the plate 25 and the flange 30 are sprung into good sealing contact with the grooves 20 on the blade platforms and with the side of the groove 21 respectively. In a second embodiment, Fig. 7, the plate 25 does not have to be displaced circumferentially upon assembly, the lugs 131 on the plate 25 being cut back as indicated at 131a so that the lugs 131 may be passed over the projections 22 when the plate is contracted. Filler pieces 134 are inserted into the spaces between the projections 22 and the lugs 131 after the plate has been allowed to expand, and tabs 134a on the filler pieces are bent up so as to lie on either side of each lug 131. A lug is disposed on the plate 25 opposite the gap 26, the lug being positioned between a pair of projections formed on the rotor disc so as to prevent rotation of the plate 25 in operation.
GB27796/55A 1955-09-29 1955-09-29 Improvements in or relating to rotors of axial-flow fluid machines for example compressors and turbines Expired GB802476A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB27796/55A GB802476A (en) 1955-09-29 1955-09-29 Improvements in or relating to rotors of axial-flow fluid machines for example compressors and turbines
US608458A US2998959A (en) 1955-09-29 1956-09-07 Bladed rotor of axial-flow fluid machine with means to retain blades in position on rotor
FR1158244D FR1158244A (en) 1955-09-29 1956-09-24 Rotor improvements for axial flow fluid machines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB27796/55A GB802476A (en) 1955-09-29 1955-09-29 Improvements in or relating to rotors of axial-flow fluid machines for example compressors and turbines

Publications (1)

Publication Number Publication Date
GB802476A true GB802476A (en) 1958-10-08

Family

ID=10265438

Family Applications (1)

Application Number Title Priority Date Filing Date
GB27796/55A Expired GB802476A (en) 1955-09-29 1955-09-29 Improvements in or relating to rotors of axial-flow fluid machines for example compressors and turbines

Country Status (3)

Country Link
US (1) US2998959A (en)
FR (1) FR1158244A (en)
GB (1) GB802476A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3070351A (en) * 1959-02-06 1962-12-25 Gen Motors Corp Blade retention
DE1212108B (en) * 1962-07-11 1966-03-10 Gen Electric Single-edged axial flow machine impeller
US3455537A (en) * 1967-09-27 1969-07-15 Continental Aviat & Eng Corp Air-cooled turbine rotor self-sustaining shroud plate
DE2542428A1 (en) * 1974-10-29 1976-05-13 United Technologies Corp TURBINE RUNNER
DE2908242A1 (en) * 1978-03-08 1979-09-13 Snecma RING-SHAPED FLANGE FOR A RUNNER OF A FLOW MACHINE
GB2244100A (en) * 1990-05-16 1991-11-20 Rolls Royce Plc Retaining gas turbine rotor blades
EP0761930A1 (en) * 1995-08-24 1997-03-12 ROLLS-ROYCE plc Seal and retention segments for the blades of an axial turbomachine
US10975714B2 (en) * 2018-11-22 2021-04-13 Pratt & Whitney Canada Corp. Rotor assembly with blade sealing tab

Families Citing this family (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2972470A (en) * 1958-11-03 1961-02-21 Gen Motors Corp Turbine construction
GB928349A (en) * 1960-12-06 1963-06-12 Rolls Royce Improvements in or relating to bladed rotors of fluid flow machines
US3295825A (en) * 1965-03-10 1967-01-03 Gen Motors Corp Multi-stage turbine rotor
US3700354A (en) * 1971-05-03 1972-10-24 Us Navy Compressor blade root seal
DE2140816A1 (en) * 1971-08-14 1973-03-01 Motoren Turbinen Union ROTOR FOR FLOW MACHINERY
BE792286A (en) * 1971-12-06 1973-03-30 Gen Electric BOLTLESS AUBA RETAINER FOR TURBOMACHIN ROTOR
US3814539A (en) * 1972-10-04 1974-06-04 Gen Electric Rotor sealing arrangement for an axial flow fluid turbine
US3936227A (en) * 1973-08-02 1976-02-03 General Electric Company Combined coolant feed and dovetailed bucket retainer ring
US3887298A (en) * 1974-05-30 1975-06-03 United Aircraft Corp Apparatus for sealing turbine blade damper cavities
GB1479332A (en) * 1974-11-06 1977-07-13 Rolls Royce Means for retaining blades to a disc or like structure
US4011718A (en) * 1975-08-01 1977-03-15 United Technologies Corporation Gas turbine construction
US4171930A (en) * 1977-12-28 1979-10-23 General Electric Company U-clip for boltless blade retainer
US4344740A (en) * 1979-09-28 1982-08-17 United Technologies Corporation Rotor assembly
US4669959A (en) * 1984-07-23 1987-06-02 United Technologies Corporation Breach lock anti-rotation key
US4767276A (en) * 1986-12-19 1988-08-30 General Electric Company Retainer ring
GB8705216D0 (en) * 1987-03-06 1987-04-08 Rolls Royce Plc Rotor assembly
FR2639063A1 (en) * 1988-11-17 1990-05-18 Snecma STOP AND SEGMENT SEGMENT OF A SET OF AUBES MOUNTED ON A TURBOMACHINE ROTOR DISK
US4890981A (en) * 1988-12-30 1990-01-02 General Electric Company Boltless rotor blade retainer
FR2694046B1 (en) * 1992-07-22 1994-09-23 Snecma Sealing and retention device for a rotor notched with pinouts receiving blade roots.
GB9925261D0 (en) * 1999-10-27 1999-12-29 Rolls Royce Plc Locking devices
EP1284339A1 (en) * 2001-08-14 2003-02-19 Siemens Aktiengesellschaft Annular cover plate system for gas turbine rotors
DE102004036389B4 (en) * 2004-07-27 2013-04-25 Rolls-Royce Deutschland Ltd & Co Kg Turbine blade root with multiple radius groove for axial blade attachment
US8128371B2 (en) * 2007-02-15 2012-03-06 General Electric Company Method and apparatus to facilitate increasing turbine rotor efficiency
FR2913064B1 (en) * 2007-02-22 2009-04-10 Snecma Sa ANNULAR SEALING FLASK FOR ROTOR DISC IN TURBOMACHINE
EP2011969A1 (en) * 2007-07-03 2009-01-07 Siemens Aktiengesellschaft Turbine assembly and method of fixing a mounting element
US9366151B2 (en) * 2012-05-07 2016-06-14 General Electric Company System and method for covering a blade mounting region of turbine blades
EP2975219A1 (en) * 2014-07-17 2016-01-20 Siemens Aktiengesellschaft Wheel disc assembly
KR102537955B1 (en) * 2018-08-02 2023-05-31 지멘스 에너지 글로벌 게엠베하 운트 코. 카게 A rotor comprising a rotor component disposed between two rotor disks
FR3085994B1 (en) * 2018-09-18 2020-08-28 Safran Aircraft Engines BLADE AXIAL RETENTION RING FOR MOBILE TURBOMACHINE WHEEL, PREFERRED FOR AIRCRAFT

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB699582A (en) * 1950-11-14 1953-11-11 Rolls Royce Improvements in or relating to gas-turbine engines
GB712112A (en) * 1951-07-13 1954-07-21 Bristol Aeroplane Co Ltd Improvements in or relating to blade-locking means for turbine and the like rotor assemblies

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3070351A (en) * 1959-02-06 1962-12-25 Gen Motors Corp Blade retention
DE1212108B (en) * 1962-07-11 1966-03-10 Gen Electric Single-edged axial flow machine impeller
US3455537A (en) * 1967-09-27 1969-07-15 Continental Aviat & Eng Corp Air-cooled turbine rotor self-sustaining shroud plate
DE2542428A1 (en) * 1974-10-29 1976-05-13 United Technologies Corp TURBINE RUNNER
DE2908242A1 (en) * 1978-03-08 1979-09-13 Snecma RING-SHAPED FLANGE FOR A RUNNER OF A FLOW MACHINE
GB2244100A (en) * 1990-05-16 1991-11-20 Rolls Royce Plc Retaining gas turbine rotor blades
EP0761930A1 (en) * 1995-08-24 1997-03-12 ROLLS-ROYCE plc Seal and retention segments for the blades of an axial turbomachine
US10975714B2 (en) * 2018-11-22 2021-04-13 Pratt & Whitney Canada Corp. Rotor assembly with blade sealing tab
US12070811B2 (en) 2018-11-22 2024-08-27 Pratt & Whitney Canada Corp. Method of manufacturing a rotor disc for a turbine engine
US12467375B2 (en) 2018-11-22 2025-11-11 Pratt & Whitney Canada Corp. Blade for a rotor assembly of a turbine engine

Also Published As

Publication number Publication date
FR1158244A (en) 1958-06-12
US2998959A (en) 1961-09-05

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