GB766839A - Turbine rotor disc and blade assembly - Google Patents

Turbine rotor disc and blade assembly

Info

Publication number
GB766839A
GB766839A GB26750/54A GB2675054A GB766839A GB 766839 A GB766839 A GB 766839A GB 26750/54 A GB26750/54 A GB 26750/54A GB 2675054 A GB2675054 A GB 2675054A GB 766839 A GB766839 A GB 766839A
Authority
GB
United Kingdom
Prior art keywords
blade
disc
slot
slits
slots
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
GB26750/54A
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of GB766839A publication Critical patent/GB766839A/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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • F01D5/3069—Fixing blades to rotors; Blade roots ; Blade spacers between two discs or rings

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

766,839. Turbine rotor and blade assembly. PURVIS, J. T., and SACHS, R. M. Sept. 15, 1954 [Sept. 17, 1953], No. 26750/54. Class 110(3). In a turbine rotor disc and blade assembly in which blades are mounted in axial slots or in a circumferential slot in the rotor disc, the disc has axially-disposed open slits extending for the full thickness of the disc and communicating with the slots or slot to allow for expansion and contraction. A locking member is disposed in each slit and has one end projecting outwardly into the blade slot to engage the blade root so as to prevent sliding of the blade in the blade slot. In Figs. 2, 3 and 5 blades 18 are mounted in axially-directed slots in the disc 16 and slits 22 extend inwardly from the bottoms of the blade root slots. An inclined bore 24 of greater diameter than the thickness of each slit extends in the plane of the slit from one side of the rotor disc to the bottom of the blade root slot, and a locking pin 26 is passed through the bore to engage in a recess 25 at the bottom of the blade root. The pin is formed of resilient material and is hollow and open along its length, the portion which engages a blade root being formed with a transverse slot 27. In a second embodiment, the blade roots are mounted in a circumferential groove formed between a pair of spaced rotor discs, both discs being formed with aligned expansion slits. Inclined bores are formed in the slits of one disc, and locking pins passed through the bores engage recesses formed at the bottoms of the blade roots thereby locking the blades against circumferential movement. In both embodiments the locking pins prevent the passage of working fluid through the slits from one side of the disc to the other.
GB26750/54A 1953-09-17 1954-09-15 Turbine rotor disc and blade assembly Expired GB766839A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US766839XA 1953-09-17 1953-09-17

Publications (1)

Publication Number Publication Date
GB766839A true GB766839A (en) 1957-01-23

Family

ID=22133590

Family Applications (1)

Application Number Title Priority Date Filing Date
GB26750/54A Expired GB766839A (en) 1953-09-17 1954-09-15 Turbine rotor disc and blade assembly

Country Status (1)

Country Link
GB (1) GB766839A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3053505A (en) * 1958-06-11 1962-09-11 Gen Motors Corp Pinned blade shrouding
EP2230382A3 (en) * 2009-03-19 2014-03-12 Honeywell International Inc. Gas turbine rotor stage
GB2520412A (en) * 2013-10-01 2015-05-20 Snecma Device for connecting a fixed portion of a turbine engine and a distributor foot of a turbine engine turbine

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3053505A (en) * 1958-06-11 1962-09-11 Gen Motors Corp Pinned blade shrouding
EP2230382A3 (en) * 2009-03-19 2014-03-12 Honeywell International Inc. Gas turbine rotor stage
GB2520412A (en) * 2013-10-01 2015-05-20 Snecma Device for connecting a fixed portion of a turbine engine and a distributor foot of a turbine engine turbine
GB2520412B (en) * 2013-10-01 2020-09-09 Snecma Device for connecting a fixed portion of a turbine engine and a distributor foot of a turbine engine turbine

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