GB762679A - Improvements in or relating to rotor assemblies for gas turbine engines - Google Patents

Improvements in or relating to rotor assemblies for gas turbine engines

Info

Publication number
GB762679A
GB762679A GB32311/53A GB3231153A GB762679A GB 762679 A GB762679 A GB 762679A GB 32311/53 A GB32311/53 A GB 32311/53A GB 3231153 A GB3231153 A GB 3231153A GB 762679 A GB762679 A GB 762679A
Authority
GB
United Kingdom
Prior art keywords
disc
cooling air
projections
gas turbine
blade
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
GB32311/53A
Inventor
Stanley George Hooker
Kenneth William Clark
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.)
Bristol Aeroplane Co Ltd
Original Assignee
Bristol Aeroplane Co 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 Bristol Aeroplane Co Ltd filed Critical Bristol Aeroplane Co Ltd
Priority to GB32311/53A priority Critical patent/GB762679A/en
Publication of GB762679A publication Critical patent/GB762679A/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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

762,679. Gas turbine rotors. BRISTOL AEROPLANE CO., Ltd. Nov. 5, 1954 [Nov. 20, 1953], No. 32311/53. Class 110 (3). A rotor assembly for a gas turbine engine comprises a blade-carrying disc 4 and a cooling air guiding disc 14, the two discs together defining a space 13 through which cooling air may flow from the centre towards the periphery. The cooling air guiding disc has a rim 15 bearing against an annular axially-directed surface 16 on the blade-carrying disc, and a central aperture by which it is drivingly mounted on a member 18 attached to the bladecarrying disc, which member is provided with passages through which cooling air can pass into the space. The blade-carrying disc 4 is secured by bolts 3 to a. flange 2 on the shaft 1, the member 18 also being secured to the flange 2 by the bolts 3. The member 18 is formed with spoke-like projections 19 on which the air guiding disc 14 is mounted, the projections 19 forining therebetween passages for the flow of cooling air. The projections may be formed as vanes to promote the flow of air into the space 13. The projections 19 could be formed on the outer periphery of the flange 2 instead of on a separate member such as 18. The member 18 may be a casting and the cooling air guide disc 14 may be a forging. The cooling air guiding disc may be shaped so that during rotation centrifugal force acting thereon tends to maintain the rim of the disc pressed against the axiallydirected surface 16 on the rotor disc 4.
GB32311/53A 1953-11-20 1953-11-20 Improvements in or relating to rotor assemblies for gas turbine engines Expired GB762679A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB32311/53A GB762679A (en) 1953-11-20 1953-11-20 Improvements in or relating to rotor assemblies for gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB32311/53A GB762679A (en) 1953-11-20 1953-11-20 Improvements in or relating to rotor assemblies for gas turbine engines

Publications (1)

Publication Number Publication Date
GB762679A true GB762679A (en) 1956-12-05

Family

ID=10336626

Family Applications (1)

Application Number Title Priority Date Filing Date
GB32311/53A Expired GB762679A (en) 1953-11-20 1953-11-20 Improvements in or relating to rotor assemblies for gas turbine engines

Country Status (1)

Country Link
GB (1) GB762679A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1106557B (en) * 1957-07-18 1961-05-10 Rolls Royce Gas turbine, the rotor blades of which have inner cooling ducts
GB2118629A (en) * 1982-04-21 1983-11-02 Rolls Royce Device for passing a fluid flow eg. cooling air through a barrier eg. bolted joint
GB2309269A (en) * 1982-03-23 1997-07-23 Snecma Cooling gas turbine rotor assemblies
CN104948237A (en) * 2015-07-09 2015-09-30 中国能建集团装备有限公司北京技术中心 Heat dissipation structure of turbine

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1106557B (en) * 1957-07-18 1961-05-10 Rolls Royce Gas turbine, the rotor blades of which have inner cooling ducts
GB2309269A (en) * 1982-03-23 1997-07-23 Snecma Cooling gas turbine rotor assemblies
GB2309269B (en) * 1982-03-23 1998-01-07 Snecma Gas turbine rotar cooling
GB2118629A (en) * 1982-04-21 1983-11-02 Rolls Royce Device for passing a fluid flow eg. cooling air through a barrier eg. bolted joint
US4551062A (en) * 1982-04-21 1985-11-05 Rolls-Royce Limited Device for passing a fluid flow through a barrier
CN104948237A (en) * 2015-07-09 2015-09-30 中国能建集团装备有限公司北京技术中心 Heat dissipation structure of turbine

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