GB848465A - Rotors of multi-stage axial flow compressors or turbines - Google Patents

Rotors of multi-stage axial flow compressors or turbines

Info

Publication number
GB848465A
GB848465A GB18899/57A GB1889957A GB848465A GB 848465 A GB848465 A GB 848465A GB 18899/57 A GB18899/57 A GB 18899/57A GB 1889957 A GB1889957 A GB 1889957A GB 848465 A GB848465 A GB 848465A
Authority
GB
United Kingdom
Prior art keywords
holes
discs
projections
members
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
GB18899/57A
Inventor
Michael John Sutters
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.)
Napier Turbochargers Ltd
Original Assignee
D Napier and Son Ltd
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 D Napier and Son Ltd filed Critical D Napier and Son Ltd
Priority to GB18899/57A priority Critical patent/GB848465A/en
Priority to DEN15418A priority patent/DE1087746B/en
Priority to FR1201124D priority patent/FR1201124A/en
Priority to US753332A priority patent/US2988324A/en
Priority to BE570302A priority patent/BE570302A/xx
Publication of GB848465A publication Critical patent/GB848465A/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
    • F01D5/3069—Fixing blades to rotors; Blade roots ; Blade spacers between two discs or rings
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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

Abstract

848,465. Turbines. NAPIER & SON Ltd., D. July 25, 1958 [June 14, 1957], No. 18899/57. Class 110 (3). The rotor of an axial-flow compressor or turbine comprises at least two adjacent rings of blades 9 having root projections 11 which lie within holes in two parallel blade-supporting discs 5, 6, annular driving-members 15 extending between the nearer blade-supporting discs and provided with upstream and downstream projections 14 which lie within holes in the adjacent discs. The discs, which resist the centrifugal forces due to the rotating blades, are each provided near the rim with a row of holes, each comprising a narrow outer part 7 and a wider part 8. The blades are disposed between the discs and each root projection 11 fits closely within the part 7 of the hole in the adjacent disc. An intermediate driving-ring 12 is disposed between the discs and has projections 13 disposed along its edges at twice the pitch of the holes in the disc, the projections entering the parts 8 of alternate holes in the adjacent disc. The parts 8 of the other holes in each disc are occupied by projections 14 on the annular interblade-ring driving-members 15. Annular sealing-members are provided radially outboard of the members 15 and extend, at their edges, beneath the blade platforms 17.
GB18899/57A 1957-06-14 1957-06-14 Rotors of multi-stage axial flow compressors or turbines Expired GB848465A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
GB18899/57A GB848465A (en) 1957-06-14 1957-06-14 Rotors of multi-stage axial flow compressors or turbines
DEN15418A DE1087746B (en) 1957-06-14 1958-07-30 Runner for multi-stage axial compressors or turbines
FR1201124D FR1201124A (en) 1957-06-14 1958-08-05 Double support disc rotor for compressor
US753332A US2988324A (en) 1957-06-14 1958-08-05 Rotors for multi-stage axial flow compressors or turbines
BE570302A BE570302A (en) 1957-06-14 1958-08-12

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB18899/57A GB848465A (en) 1957-06-14 1957-06-14 Rotors of multi-stage axial flow compressors or turbines

Publications (1)

Publication Number Publication Date
GB848465A true GB848465A (en) 1960-09-14

Family

ID=10120318

Family Applications (1)

Application Number Title Priority Date Filing Date
GB18899/57A Expired GB848465A (en) 1957-06-14 1957-06-14 Rotors of multi-stage axial flow compressors or turbines

Country Status (3)

Country Link
BE (1) BE570302A (en)
FR (1) FR1201124A (en)
GB (1) GB848465A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2641573A1 (en) * 1989-01-11 1990-07-13 Snecma TURBOMACHINE ROTOR PROVIDED WITH A BLADE FIXING DEVICE
FR2660363A1 (en) * 1990-04-03 1991-10-04 Gen Electric STRUCTURE FOR FIXING THE INTERNAL END OF A TURBINE BLADE.
GB2272027A (en) * 1992-10-28 1994-05-04 Snecma Interlocking the ends of blades
EP1079070A3 (en) * 1999-08-26 2004-01-14 ALSTOM (Switzerland) Ltd Heatshield for a turbine rotor
EP3851635A3 (en) * 2020-01-17 2021-07-28 Raytheon Technologies Corporation Rotor assemblies for a gas turbine engine
EP3998408A1 (en) * 2021-02-26 2022-05-18 Lilium eAircraft GmbH Rotor assembly
US11401814B2 (en) 2020-01-17 2022-08-02 Raytheon Technologies Corporation Rotor assembly with internal vanes

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2834751B1 (en) * 2002-01-17 2004-09-10 Snecma Moteurs ROTOR ARRANGEMENT OF A TURBOMACHINE

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2641573A1 (en) * 1989-01-11 1990-07-13 Snecma TURBOMACHINE ROTOR PROVIDED WITH A BLADE FIXING DEVICE
EP0378474A1 (en) * 1989-01-11 1990-07-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbo machine rotor with means for blade fixing
US5018941A (en) * 1989-01-11 1991-05-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation"S.N.E.C.M.A. Blade fixing arrangement for a turbomachine rotor
FR2660363A1 (en) * 1990-04-03 1991-10-04 Gen Electric STRUCTURE FOR FIXING THE INTERNAL END OF A TURBINE BLADE.
GB2272027A (en) * 1992-10-28 1994-05-04 Snecma Interlocking the ends of blades
GB2272027B (en) * 1992-10-28 1996-04-10 Snecma System for interlocking the ends of blades
EP1079070A3 (en) * 1999-08-26 2004-01-14 ALSTOM (Switzerland) Ltd Heatshield for a turbine rotor
EP3851635A3 (en) * 2020-01-17 2021-07-28 Raytheon Technologies Corporation Rotor assemblies for a gas turbine engine
US11286781B2 (en) 2020-01-17 2022-03-29 Raytheon Technologies Corporation Multi-disk bladed rotor assembly for rotational equipment
US11401814B2 (en) 2020-01-17 2022-08-02 Raytheon Technologies Corporation Rotor assembly with internal vanes
EP3998408A1 (en) * 2021-02-26 2022-05-18 Lilium eAircraft GmbH Rotor assembly

Also Published As

Publication number Publication date
BE570302A (en) 1958-08-30
FR1201124A (en) 1959-12-28

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