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GB755841A - Improvements in or relating to rotors for axial-flow compressors and turbines - Google Patents

Improvements in or relating to rotors for axial-flow compressors and turbines

Info

Publication number
GB755841A
GB755841A GB1482453A GB1482453A GB755841A GB 755841 A GB755841 A GB 755841A GB 1482453 A GB1482453 A GB 1482453A GB 1482453 A GB1482453 A GB 1482453A GB 755841 A GB755841 A GB 755841A
Authority
GB
United Kingdom
Prior art keywords
shell
blades
disc
rotors
discs
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
GB1482453A
Inventor
Nelson Hector Kent
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB1482453A priority Critical patent/GB755841A/en
Publication of GB755841A publication Critical patent/GB755841A/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
    • F01D5/063—Welded rotors
    • 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
    • F01D5/3061—Fixing blades to rotors; Blade roots ; Blade spacers by welding, brazing

Landscapes

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

Abstract

755,841. Turbine and compressor rotors. ROLLS-ROYCE, Ltd. May 19, 1954 [May 27, 1953], No. 14824/53. Class 110(3) [Also in Group XXII] A bladed rotor for an axial flow compressor or turbine comprises a row of blades 4, an annular shell 2 having a ring of circumferentially-spaced apertures 6 in its periphery to receive the inner ends of the blades, and a disc 5 disposed co-axially within the shell with its periphery engaging the shell radially inwardly of the inner end surfaces of the blades. The shell, disc and blades are brazed together. The rotor shown has several rows of blades 4 and the shell is thickened by annular lands 7 in the region of the apertures. The shell is externally of conical form and the co-operating surfaces of the discs and shell are parallel thereto. In a second embodiment, Fig. 2, the co-operating surfaces of the disc and shell are cylindrical and a radial abutment surface 8 is formed on the shell. The blades, shell and discs may be formed of aluminium alloy and the parts brazed together by an aluminium brazing operation. Alternatively the parts may be formed of steel.
GB1482453A 1953-05-27 1953-05-27 Improvements in or relating to rotors for axial-flow compressors and turbines Expired GB755841A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1482453A GB755841A (en) 1953-05-27 1953-05-27 Improvements in or relating to rotors for axial-flow compressors and turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1482453A GB755841A (en) 1953-05-27 1953-05-27 Improvements in or relating to rotors for axial-flow compressors and turbines

Publications (1)

Publication Number Publication Date
GB755841A true GB755841A (en) 1956-08-29

Family

ID=10048121

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1482453A Expired GB755841A (en) 1953-05-27 1953-05-27 Improvements in or relating to rotors for axial-flow compressors and turbines

Country Status (1)

Country Link
GB (1) GB755841A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2958322A1 (en) * 2010-04-01 2011-10-07 Snecma GAS TURBINE ENGINE ROTOR COMPRISING A ROTOR DRUM AND ROTOR CROWN
US8408446B1 (en) 2012-02-13 2013-04-02 Honeywell International Inc. Methods and tooling assemblies for the manufacture of metallurgically-consolidated turbine engine components
US9033670B2 (en) 2012-04-11 2015-05-19 Honeywell International Inc. Axially-split radial turbines and methods for the manufacture thereof

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2958322A1 (en) * 2010-04-01 2011-10-07 Snecma GAS TURBINE ENGINE ROTOR COMPRISING A ROTOR DRUM AND ROTOR CROWN
US8757980B2 (en) 2010-04-01 2014-06-24 Snecma Rotor for a gas turbine engine comprising a rotor spool and a rotor ring
US8408446B1 (en) 2012-02-13 2013-04-02 Honeywell International Inc. Methods and tooling assemblies for the manufacture of metallurgically-consolidated turbine engine components
US9033670B2 (en) 2012-04-11 2015-05-19 Honeywell International Inc. Axially-split radial turbines and methods for the manufacture thereof
US9726022B2 (en) 2012-04-11 2017-08-08 Honeywell International Inc. Axially-split radial turbines

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