GB1053509A - - Google Patents

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Publication number
GB1053509A
GB1053509A GB1053509DA GB1053509A GB 1053509 A GB1053509 A GB 1053509A GB 1053509D A GB1053509D A GB 1053509DA GB 1053509 A GB1053509 A GB 1053509A
Authority
GB
United Kingdom
Prior art keywords
flow
passage
cross sectional
sectional area
constant rate
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.)
Active
Application number
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.)
Publication of GB1053509A publication Critical patent/GB1053509A/en
Active legal-status Critical Current

Links

Classifications

    • G—PHYSICS
    • G11—INFORMATION STORAGE
    • G11C—STATIC STORES
    • G11C11/00—Digital stores characterised by the use of particular electric or magnetic storage elements; Storage elements therefor
    • G11C11/21—Digital stores characterised by the use of particular electric or magnetic storage elements; Storage elements therefor using electric elements
    • G11C11/44—Digital stores characterised by the use of particular electric or magnetic storage elements; Storage elements therefor using electric elements using super-conductive elements, e.g. cryotron
    • 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
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/045—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type the wheel comprising two adjacent bladed wheel portions, e.g. with interengaging blades for damping vibrations
    • H—ELECTRICITY
    • H10—SEMICONDUCTOR DEVICES; ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
    • H10N—ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
    • H10N60/00—Superconducting devices
    • H10N60/10—Junction-based devices
    • H10N60/11—Single-electron tunnelling devices

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Computer Hardware Design (AREA)
  • Superconductor Devices And Manufacturing Methods Thereof (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1,053,509. Turbine rotors; centrifugal compressors. ROLLS-ROYCE Ltd. Aug.6, 1965, No.33872/65. Headings F1C and F1T. To reduce turbulence a radial flow turbine or compressor rotor 14 has the radially inner portions of each radially extending vane 16 thicker than the radially outer portions thereof so that the effective flow cross sectional area of each flow passage between adjacent vanes varies at a substantially constant rate from the inlet to the outlet of the passage. The rotor 14 is formed in two parts connected by dowels 17 and the vanes 16 are thickened within the dotted area C. In the case of a radial inward flow turbine, the flow cross sectional area of a flow passage decreases at a constant rate along the length of the passage from the inlet to the outlet, as illustrated by graph B, Fig. 7 (not shown). In the case of a compressor, the flow is radially outwards with a constant rate of increase of the flow cross sectional area. The rotor may be used in a gas turbine engine.
GB1053509D 1963-10-25 Active GB1053509A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB42218/63A GB1023509A (en) 1963-10-25 1963-10-25 Improvements in and relating to superconductive devices

Publications (1)

Publication Number Publication Date
GB1053509A true GB1053509A (en)

Family

ID=31898311

Family Applications (2)

Application Number Title Priority Date Filing Date
GB1053509D Active GB1053509A (en) 1963-10-25
GB42218/63A Expired GB1023509A (en) 1963-10-25 1963-10-25 Improvements in and relating to superconductive devices

Family Applications After (1)

Application Number Title Priority Date Filing Date
GB42218/63A Expired GB1023509A (en) 1963-10-25 1963-10-25 Improvements in and relating to superconductive devices

Country Status (1)

Country Link
GB (2) GB1023509A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012212896A1 (en) * 2012-07-24 2014-02-20 Continental Automotive Gmbh Impeller of an exhaust gas turbocharger
EP2960462A4 (en) * 2013-02-21 2016-04-06 Mitsubishi Heavy Ind Ltd Turbine rotor blade

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012212896A1 (en) * 2012-07-24 2014-02-20 Continental Automotive Gmbh Impeller of an exhaust gas turbocharger
US10253633B2 (en) 2012-07-24 2019-04-09 Continental Automotive Gmbh Rotor of an exhaust gas turbocharger
EP2960462A4 (en) * 2013-02-21 2016-04-06 Mitsubishi Heavy Ind Ltd Turbine rotor blade
US10006297B2 (en) 2013-02-21 2018-06-26 Mitsubishi Heavy Industries, Ltd. Turbine rotor blade

Also Published As

Publication number Publication date
GB1023509A (en) 1966-03-23

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