GB1318256A - Bladed rotors - Google Patents

Bladed rotors

Info

Publication number
GB1318256A
GB1318256A GB4064270A GB1318256DA GB1318256A GB 1318256 A GB1318256 A GB 1318256A GB 4064270 A GB4064270 A GB 4064270A GB 1318256D A GB1318256D A GB 1318256DA GB 1318256 A GB1318256 A GB 1318256A
Authority
GB
United Kingdom
Prior art keywords
blades
discs
vanes
integral
plates
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
GB4064270A
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB1318256A publication Critical patent/GB1318256A/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
    • 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
    • F01D5/021—Blade-carrying members, e.g. rotors for flow machines or engines with only one axial stage
    • 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
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc
    • 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

1318256 Turbomachine rotors GENERAL ELECTRIC CO 24 Aug 1970 40642/70 Heading FIT A turbine or compressor rotor 22 of a gas turbine engine comprises axially spaced parallel discs 30, 32 having integral radially extending vanes 34 therebetween, and blades 20 angularly spaced about the peripheries of the discs. The blades 20 are mounted by engagement of their roots between bulbous lugs 36 formed on the ends of vanes 34 radially outwardly and integral with the peripheries of discs 30, 32. The roots are retained axially in position by side plates 40, 42 having lips 46, 48 engaging shoulders on discs 30, 32, the plates being secured by bolts 44 passing through lugs 36. Plates 40, 42 extend outwardly to platforms 50 on blades 20, the upstream faces of the platforms having cutaway portions to receive fingers (51), Fig.3 (not shown) projecting from plate 40. Vanes 34 direct cooling air to the interiors of blades 20 and also serve to transmit, in shear, centrifugal loads on the blades to discs 30, 32, the vanes tapering in thickness in the radial inwards direction to give satisfactory stress distribution. The cooling air is directed to vanes 34 from chamber 54 by an assembly of blades 58 integral with rings 60, the assembly being held in position on the rotor by snap ring 62.
GB4064270A 1970-08-24 1970-08-24 Bladed rotors Expired GB1318256A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4064270 1970-08-24

Publications (1)

Publication Number Publication Date
GB1318256A true GB1318256A (en) 1973-05-23

Family

ID=10415908

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4064270A Expired GB1318256A (en) 1970-08-24 1970-08-24 Bladed rotors

Country Status (1)

Country Link
GB (1) GB1318256A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4203705A (en) * 1975-12-22 1980-05-20 United Technologies Corporation Bonded turbine disk for improved low cycle fatigue life
US4595339A (en) * 1983-09-21 1986-06-17 Societe Nationale D'etude Et De Construction De Meteurs D'aviation S.N.E.C.M.A. Centripetal accelerator for air exhaustion in a cooling device of a gas turbine combined with the compressor disc

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4203705A (en) * 1975-12-22 1980-05-20 United Technologies Corporation Bonded turbine disk for improved low cycle fatigue life
US4595339A (en) * 1983-09-21 1986-06-17 Societe Nationale D'etude Et De Construction De Meteurs D'aviation S.N.E.C.M.A. Centripetal accelerator for air exhaustion in a cooling device of a gas turbine combined with the compressor disc

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Legal Events

Date Code Title Description
PS Patent sealed
746 Register noted 'licences of right' (sect. 46/1977)
PCNP Patent ceased through non-payment of renewal fee