GB1118954A - Bladed rotor assembly for gas turbine engine - Google Patents

Bladed rotor assembly for gas turbine engine

Info

Publication number
GB1118954A
GB1118954A GB1522267A GB1522267A GB1118954A GB 1118954 A GB1118954 A GB 1118954A GB 1522267 A GB1522267 A GB 1522267A GB 1522267 A GB1522267 A GB 1522267A GB 1118954 A GB1118954 A GB 1118954A
Authority
GB
United Kingdom
Prior art keywords
blades
rotor
disc
brazed
spacers
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
GB1522267A
Inventor
Richard Derby Beale
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 GB1522267A priority Critical patent/GB1118954A/en
Priority to FR1556913D priority patent/FR1556913A/fr
Publication of GB1118954A publication Critical patent/GB1118954A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/006—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine wheels
    • 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)

Abstract

1,118,954. Making bladed rotors. ROLLSROYCE Ltd. 3 April, 1967, No.. 15222/67. Heading B3A. [Also in Division F1] A rotor stage 18 having the blades 21 integral with a rotor disc 22 for a gas turbine engine is. made by cutting a plurality of slots in a billet to form a plurality of radially extending rotor blade blanks, which are subsequently formed into aerofoil-shaped. rotor blades and twisted to the required angle of incidence. The billet is formed into a disc shape either before or after the cutting step by machining or by chemical etching. After forming the blade blanks to a substantially aerofoil shape,. the. required final blade size is formed by chemical etching. Spacers 24 and angle section spacers 23 are positioned between the rotor stages 18, the spacers 23 being bolted or brazed to the disc portions 22 and brazed to each other around the blades 21, to form platforms 25. In order to double the number of blades 21 per stage; two bladed rings (29, 30) (Fig. 3, not shown) are angularly offset to each other and their disc portions 22 brazed to the opposite sides of an intermediate disc (28), the blades. 21 being twisted into substantially the same radial plane. More than two bladed rings may be secured together.
GB1522267A 1967-04-03 1967-04-03 Bladed rotor assembly for gas turbine engine Expired GB1118954A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB1522267A GB1118954A (en) 1967-04-03 1967-04-03 Bladed rotor assembly for gas turbine engine
FR1556913D FR1556913A (en) 1967-04-03 1968-03-25

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1522267A GB1118954A (en) 1967-04-03 1967-04-03 Bladed rotor assembly for gas turbine engine

Publications (1)

Publication Number Publication Date
GB1118954A true GB1118954A (en) 1968-07-03

Family

ID=10055208

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1522267A Expired GB1118954A (en) 1967-04-03 1967-04-03 Bladed rotor assembly for gas turbine engine

Country Status (2)

Country Link
FR (1) FR1556913A (en)
GB (1) GB1118954A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005024185A1 (en) * 2003-09-03 2005-03-17 Mtu Aero Engines Gmbh Method for the production of gas turbine rotors with integrated blading

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005024185A1 (en) * 2003-09-03 2005-03-17 Mtu Aero Engines Gmbh Method for the production of gas turbine rotors with integrated blading
US7900351B2 (en) 2003-09-03 2011-03-08 Mtu Aero Engines Gmbh Method for the production of gas turbine rotors having integrated blading

Also Published As

Publication number Publication date
FR1556913A (en) 1969-02-07

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