GB741054A - Improvements in or relating to radial flow turbines and centrifugal compressors - Google Patents

Improvements in or relating to radial flow turbines and centrifugal compressors

Info

Publication number
GB741054A
GB741054A GB24751/52A GB2475152A GB741054A GB 741054 A GB741054 A GB 741054A GB 24751/52 A GB24751/52 A GB 24751/52A GB 2475152 A GB2475152 A GB 2475152A GB 741054 A GB741054 A GB 741054A
Authority
GB
United Kingdom
Prior art keywords
slot
blade
blades
rotor hub
plane
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
GB24751/52A
Inventor
John Charles Barr
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.)
Power Jets Research and Development Ltd
Original Assignee
Power Jets Research and Development 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 Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Priority to GB24751/52A priority Critical patent/GB741054A/en
Publication of GB741054A publication Critical patent/GB741054A/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
    • F01D5/04—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
    • F01D5/048—Form or construction
    • 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

741,054. Turbines and compressors. POWER JETS (RESEARCH & DEVELOPMENT), Ltd. Sept. 23, 1953 [Oct. 2, 1952], No. 24751/52. Classes 110(1) and 110(3) A rotor hub member for an inward or outward radial flow turbine or for a centrifugal compressor has slots in the surface thereof for the reception of the root portions of separately-fabricated blades, each slot being formed throughout its length upon an arc lying in a plane normal to the base of the slot. In Figs. 1a, 1b, 1c, the rotor 10 is formed with slots 17 having undercut recesses 16. The slot is formed by milling out an arcuate groove of radius 19 from the centre 20. The slot is formed with a taper increasing radius, the blade root being correspondingly shaped so that the blade becomes tightly locked during operation by means of centrifugal force. In a second embodiment, each blade root is formed with a projection at its radially inner end, the projection engaging a corresponding slot in the rotor hub to 'constitute a locking means against outward displacement. In a third embodiment, the invention is shown applied in the case of a rotor with skewed blades the arc upon which any blade root portion and the corresponding slot in the rotor hub are formed lying in a plane intersecting an axial plane of the rotor hub. In Fig. 4, blades 38 are attached to a single-sided rotor hub 37 and are locked against movement in both directions by flanges on the disc 44 and by a disc 43. Coolant fluid is supplied through a bore 45 in the shaft 33 and passes to the interior of the blades through passages 46, the fluid escaping through apertures 47 at the radially outer ends of the blades. A hollow sheet metal blade 48 is shown in Fig. 5, the 'blade comprising a separately-fabricated root portion 51 and having an internal cavity 49 for the passage of coolant fluid. The plane 52 of the blade does not coincide with the plane 53 normal to the base of the root slot.
GB24751/52A 1952-10-02 1952-10-02 Improvements in or relating to radial flow turbines and centrifugal compressors Expired GB741054A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB24751/52A GB741054A (en) 1952-10-02 1952-10-02 Improvements in or relating to radial flow turbines and centrifugal compressors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB24751/52A GB741054A (en) 1952-10-02 1952-10-02 Improvements in or relating to radial flow turbines and centrifugal compressors

Publications (1)

Publication Number Publication Date
GB741054A true GB741054A (en) 1955-11-23

Family

ID=10216676

Family Applications (1)

Application Number Title Priority Date Filing Date
GB24751/52A Expired GB741054A (en) 1952-10-02 1952-10-02 Improvements in or relating to radial flow turbines and centrifugal compressors

Country Status (1)

Country Link
GB (1) GB741054A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2354043A (en) * 1999-08-24 2001-03-14 Fred Starr Cooling radial flow turbine
US20130272882A1 (en) * 2012-04-11 2013-10-17 Honeywell International Inc. Axially-split radial turbines and methods for the manufacture thereof
US9115586B2 (en) 2012-04-19 2015-08-25 Honeywell International Inc. Axially-split radial turbine
US9476305B2 (en) 2013-05-13 2016-10-25 Honeywell International Inc. Impingement-cooled turbine rotor

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2354043A (en) * 1999-08-24 2001-03-14 Fred Starr Cooling radial flow turbine
US20130272882A1 (en) * 2012-04-11 2013-10-17 Honeywell International Inc. Axially-split radial turbines and methods for the manufacture thereof
US9033670B2 (en) * 2012-04-11 2015-05-19 Honeywell International Inc. Axially-split radial turbines and methods for the manufacture thereof
US9115586B2 (en) 2012-04-19 2015-08-25 Honeywell International Inc. Axially-split radial turbine
US9476305B2 (en) 2013-05-13 2016-10-25 Honeywell International Inc. Impingement-cooled turbine rotor

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