GB1238434A - - Google Patents

Info

Publication number
GB1238434A
GB1238434A GB1238434DA GB1238434A GB 1238434 A GB1238434 A GB 1238434A GB 1238434D A GB1238434D A GB 1238434DA GB 1238434 A GB1238434 A GB 1238434A
Authority
GB
United Kingdom
Prior art keywords
ring
rings
blades
discs
hub
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
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 filed Critical
Publication of GB1238434A publication Critical patent/GB1238434A/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
    • F01D5/028—Blade-carrying members, e.g. rotors the rotor disc being formed of sheet laminae

Abstract

1,238,434. Turbomachine rotors. GENERAL MOTORS CORP. Feb. 5, 1970 [May 13,1969], No. 5584/70. Heading F1T. A turbine or compressor rotor comprises outer and inner concentric rings 9, 10 having blades mounted on at least one of the rings and extending radially outwardly of the outer ring 9 and tension spokes 34 extending between the rings, the spokes having an inward component of direction from the point of attachment at each ring so as to put both rings in compression and thus oppose centrifugal forces on the rings. As shown, the rings 9, 10 respectively support in dovetail slots the roots 19, 13 of blades 18, 11, the latter blades extending outwardly through apertures in the ring 9. This ring comprises forward and rearward portions 22, 23 connected by a circumferential tenon joint 25 so that the ring can be assembled around the blades 11. The ring portions 22, 23 are integral with respective discs 26, 29 and hubs 27, 30, the discs providing a barrier against flow of working fluid axially between the rings 9, 10. One of the discs may be omitted. Each spoke 34 has a ball end (43), Fig. 4 (not shown), seated against the outer surface of the inner ring 10 and a threaded end (45) receiving a nut (46) which bears against the outer surface of the outer ring 9 to permit adjustment of the spoke tension. In a modification, Fig. 3 (not shown), the inner ring (60) has an integral disc (61) and hub (62) at its forward end, the forward disc (66) of the outer ring (59) being sealed to the hub (62) by a piston ring seal (67).
GB1238434D 1969-05-13 1970-02-05 Expired GB1238434A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US82407769A 1969-05-13 1969-05-13

Publications (1)

Publication Number Publication Date
GB1238434A true GB1238434A (en) 1971-07-07

Family

ID=25240540

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1238434D Expired GB1238434A (en) 1969-05-13 1970-02-05

Country Status (2)

Country Link
US (1) US3572969A (en)
GB (1) GB1238434A (en)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT1182448B (en) * 1985-02-19 1987-10-05 Agusta Aeronaut Costr METAL HUB FOR A HELICOPTER ROTOR
CN101151457B (en) * 2005-03-30 2013-01-16 轻风株式会社 Windmill
FR2949091B1 (en) * 2009-08-17 2015-06-26 Snecma METHOD FOR PRODUCING A HOLLOW MONOBLOCK HOLLOW DISC
US9080448B2 (en) 2009-12-29 2015-07-14 Rolls-Royce North American Technologies, Inc. Gas turbine engine vanes
RU2446311C2 (en) * 2010-07-02 2012-03-27 Открытое Акционерное Общество "Государственный Ракетный Центр Имени Академика В.П. Макеева" Rotor of wind-power plant
DE102014219046A1 (en) * 2014-09-22 2016-03-24 Mahle International Gmbh fan

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1115162A (en) * 1908-08-11 1914-10-27 Emile Berliner Aeromobile.
US1010337A (en) * 1910-10-11 1911-11-28 Alfred Wunderlich Screw-propeller for flying-machines.
US1046385A (en) * 1911-09-21 1912-12-03 Herbert F Hawes Aerial propeller.
US1184300A (en) * 1913-05-10 1916-05-23 Bayley Mfg Co Centrifugal fan.
FR927913A (en) * 1946-04-19 1947-11-13 Method and devices for the construction and assembly of blades of rotating machines
DE819078C (en) * 1949-06-02 1951-10-29 Friedrich Koester High-speed wind turbine with a large torque
US2844354A (en) * 1954-04-08 1958-07-22 Cincinnati Testing & Res Lab Rotor blade and method of making same
US2855179A (en) * 1955-01-05 1958-10-07 John K Brown High temperature ceramic turbine
US2857094A (en) * 1955-07-19 1958-10-21 John R Erwin Integral plastic rotors
US3032317A (en) * 1958-10-24 1962-05-01 Robert G Frank Jet turbine bucket wheel
GB1090721A (en) * 1964-01-15 1967-11-15 Rolls Royce Method of making a bladed rotor for a fluid flow machine, e.g. a gas turbine engine
US3403844A (en) * 1967-10-02 1968-10-01 Gen Electric Bladed member and method for making

Also Published As

Publication number Publication date
US3572969A (en) 1971-03-30

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLNP Patent lapsed through nonpayment of renewal fees