GB771124A - Bladed rotor construction for compressors, turbines and like fluid flow machines - Google Patents

Bladed rotor construction for compressors, turbines and like fluid flow machines

Info

Publication number
GB771124A
GB771124A GB1935654A GB1935654A GB771124A GB 771124 A GB771124 A GB 771124A GB 1935654 A GB1935654 A GB 1935654A GB 1935654 A GB1935654 A GB 1935654A GB 771124 A GB771124 A GB 771124A
Authority
GB
United Kingdom
Prior art keywords
discs
roots
blade
disc
blades
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
GB1935654A
Inventor
Sydney William Henry Perry
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 GB1935654A priority Critical patent/GB771124A/en
Publication of GB771124A publication Critical patent/GB771124A/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
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

771,124. Turbine and compressor bladed rotors. POWER JETS (RESEARCH & DEVELOPMENT), Ltd. June 30, 1955 [July 1, 1954]. No. 19356/54. Class 110 (3). A turbine or compressor rotor comprises at least two coaxial, axially-spaced discs, a row of rotor blades having their roots lying between and engaging with the peripheries of the discs, and an annular member extending axially radially within the blade roots and being rigidly connected at its ends to the adjacent discs. A driving ring is secured to one of the discs radially inwardly of the blade roots and has parts engaging with the blade roots for transmitting drive from the disc to the blades. The axial-flow compressor rotor shown comprises eight discs 1 ... 8 and seven blade stages 11 ... 17. The first disc 1 is formed integrally with an axially-extending flange 1a having a radially-outwardly extending flange 1b at its end, the flange 1b being secured to the adjacent disc 2 by means of bolts 10. The blades 11 are disposed between the peripheries of the discs 1 and 2, and a driving ring in the form of an angle section flange 20 of sheet metal is secured by the bolts 10 to the rotor disc 2 and has teeth 20c in engagement with the blade roots. The blade rows 12 and 13 are mounted between the discs 2, 3 and 3, 4 respectively in a similar manner. The flanges 4a, 5a, 6a and 7a on the discs 4, 5, 6 and 7 are, however, provided with radially inwardly directed flanges 4b, 5b, 6b, 7b which are connected to the adjacent discs 5, 6, 7, 8 respectively. The roots of the rotor blades 14, 15, 16, 17 are engaged by driving dogs formed at the peripheries of the discs 5, 6, 7, 8.
GB1935654A 1954-07-01 1954-07-01 Bladed rotor construction for compressors, turbines and like fluid flow machines Expired GB771124A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1935654A GB771124A (en) 1954-07-01 1954-07-01 Bladed rotor construction for compressors, turbines and like fluid flow machines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1935654A GB771124A (en) 1954-07-01 1954-07-01 Bladed rotor construction for compressors, turbines and like fluid flow machines

Publications (1)

Publication Number Publication Date
GB771124A true GB771124A (en) 1957-03-27

Family

ID=10127986

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1935654A Expired GB771124A (en) 1954-07-01 1954-07-01 Bladed rotor construction for compressors, turbines and like fluid flow machines

Country Status (1)

Country Link
GB (1) GB771124A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5577887A (en) * 1994-07-06 1996-11-26 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Metallic lip seal and turbo jet engine equipped with said seal

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5577887A (en) * 1994-07-06 1996-11-26 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Metallic lip seal and turbo jet engine equipped with said seal

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